Q-FANSTM for general aviation aircraft — NASA-CR-114665 (1973)

APPENDIX B

APPENDIX B GENERAI,IZED METHOD OF Q-FAN FAR-FIELD NOISE ESTIMATION FOR GENERAL AVIATION AIRCRA FT Q-Fan noise at 66 knots (34 m/s) can be estimated using this generalized proc_:- dure from the follm_ng design and operating parameters.

I. Diameter 2. RPM or tip speed 3. Thrust at 66 knots (34 m/s) 4. Total activity factor (activity factor per blade x number of blades) It should be noted that the method is predicated on using for a specific total activity factor the number of blades, 'activity factor per blade combination to minimize noise.

PERFORMANCE CALCULATION PROCEDURE With the diameter, rpm, thrust, and total activity factor defined, the procedures as outlined on the sample computation sheet (fig. B-l) is as follows: The English u.nits will be used and the SI units will be included in parenthesis.

A. From the knova, data, complete the top of the computation sheet. Identify the airplane, engine, gear ratio (G. R. ), number of Q-Fans and distance (observer field point).

B. Determine items 1 through 7 from the Q-Fan, airplane and engine conditions which have been selected for analysis as explained below.

1. Diameter D-rotor diameter, ft (m) I00,000 17/b_x 3dx 2. Activity factor/Blade AF

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8co Where b/D - ratio blade width/blade dismeter x - fraction of blade tip radius 3. No. of blades B - total number of blades in Q-Fan 4. Engine rpm N e - rpm 5. Velocity 66 knots (34 m/s) 6. Thrust T - Q-Fan thrust, lb (N_ at 66 knots (34 m/s) 7. Distance Observer fieldpoint, ft (m) Rotor speed - Ne x G.R.

Rotor tip speed (K4) ND 60 fc Where K4 = rr (10. 31) 10. TAF AFxB 11. Check Read no. of blades for proper TAF and tip speed from figure B-2.

Be assured that proper selection is made before the calculation is con- tinued.

12. T/D 2 Comp_e 13. L1 Noise levei for 5.0 ft (1.52 m) diameter Q-Fan. Read from figures B-3, B-4, _-5, B-6. Interpolate, if necessary, 14. L2 Diameter adjustment (fig. B-7).

15. L3 4.5 PNdB due to acoustical treatment 16.. L4- Spherical spreading of the sound to if the location of interest (fig. B-8) 17. L5 Adjustment for number of Q-Fans as i follows: FIGURE 1B AIRPLANE: Hypothetical CALC. NO. I00 NO. OF Q-FANS 1 ENGINE: DATE: 3/13/73 Hypothetical

G.R. 0,812

CALC. BY R.W.

CHECKED BY: AB 1. Diameter, ft 3.0 2. Activity factor 233.0 3. No. of blades 9.0 4. Engine rpm 5000. 0 5. Velocity, kts 66.0 6. Thrust, Ibs. S80.0 7. Distance, ft 500. 0 8. N 4060.0 9. T.S. 640.0 10. TAF 2097.0 11. Check O, K.

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179/180 - _ _ -- _- " 'u ...... 1 t,._,:'_-': -. "................. -_ - l/ .... .'_-:"--':':'li_", #..,--x-_. ,_ APPE NDLK C ENGINE MODELS This appendix includes the weight, dimension and cost data used in this study to predict the weight and Size characteristics and engine prices for horizontally-opposed piston engines, rotary combustion engines, and turboprop/turboshaft engines. The method used to estimate piston engine part power and altitude performance is also in- cluded. All costs are given as 1970 original equipment manufacturer (OEM) costs.

Horizontally-Opposed Piston Engines This model is to be used to predict the weight, dimensions, performance, and cost of horizontally-opposed piston, internal combustion engines currently being used in general aviation. The data ur, ed for this study are tabulated in Tables I-V. They represent a cross-section of engines being produced by Avco-Lycoming and Teledyne- Continental with several Franklin engines also included. All data were taken from "Janes All the Worldts Aircraft," 1970-71, and engines are grouped into the following classifications: (1) Non-supercharged, direct drive.

(2) Non-supercharged, geared drive.

(3) Turbosuperchttrged, direct drive.

(4) Turbosupercharged, geared drive.

Nomenclature and performance equations used for 4-stroke piston engines are given in Table VI.

Engine Weight - Engine specific weight is defined as the ratio of engine dry weight to maximum rated power at sea level. This ratio is plotted against maximum sea level power in figure C-1 for non-supercharged, direct drive engines. The data correlate rea- sonably well showing a decrease in specific weight for increasing power up to 200 horse- power (149 kw) an_', then a constant specific weight of about 1.5 lb/hp (0.9 kg/kw) at higher levels of rated power. It is felt that the key technology parameter tha*. affects engine specific weight is._*he horsepower per unit bore area. This parameter is the product of the piston speed (rpm x stroke) and the brake mean effective pressure (BMEP). Use of the power per unit bore area leads to the conclusion that increasing the engine open will not necessarily result in reduced engine specific weight unless it results in a higher l i piston speed and thus higher displacement per cyclc. The data from figure C-1 are re- plotted in figure C-2 with the engine specific weight normalized to a BMEP of 140 psi (100 N/cm2) and a piston speed of 1800 fpm (549 m/m). This combination results in a horsepower per unit bore area of 1.98 hp/in 2 (0.23 kw/m2).

The specific weight of the remai_xing three classes of engines is plotted in figure C-3. There is considerable scatter in the data, particularly when the new Continental Tiara engine models, which are designed for much higher eng_[ne speeds, are included.

(Note that the Tiara engines are cla:ssed as geared engines because of the 2:1 reduction in speed from the engine to the out mt shaft. ) The correlations are much improved when the specific weight is normalized to fixed values of BMEP and piston speed as shown in figure C-4, Increases in piston speed are the result of either increased piston stroke or higher RPM. However, the output speed of the engine must be matched to an efficient propel- ler RPM and engines with high piston speeds are usually geared. Likewise, engines with high BMEP are usually supercharged to boost the pressure entering the cylinder.

The piston speeds and BMEP levels of the different engine classes are approximated by the regions separated by the dotted lines in figure C-5.

Strict application of the normalized specific weight parameter would lead to con- tinued reductions in engine specific weight at higher ratios of horsepower per unit bore area. However, structural and material limitations are bound to affect this trend.

Figure C-6 plots engine specific weight against the horsepower-bore area ratio for two classes of engines. Only engines rated between 150 (112) and 300 (224) sea level horse- power (kw) are used in this figure to eliminate scale effects on the specific weight.

For both classes shown, the data indicate that the specific weight approaches a minimum value at higher values of horsepower/bore area. The obvious conclusion is that care- ful judgement should be applied in using the normalized specific weight correlations given m figures C-2 and C-4.

En[ine Dimensions - The dtmensfons of the engine are defined as maximum width, and length. The most consistent dim,:nsion is the engine width which is determined pri- marily by the ,,dze of an opposed pair of cylinders. Figure C-7 shows that engine width varies very little over a wide range of rated horsepower, and tha_ the width decreases slightly at a giver, horsepower as the number of cylinders is increased.

The other two dimensions depend on whether the engine is geared or has a s,,per- charger, and they are influenced by the location of engine accessories. Height can be traded for length and vice versa. This is shown in figures C-8 and C-9 which are cor- relations of the engine width-length ratio with the engine width-height ratio for the four different classes of engines. To drtermine the values of engine height and length, the engine width-height ratio' must be specified.

i I 182 i ._ _'¢'_'_,_;,7,:_';_-_:, Engine Cost - The selling price of horizontally-opposed piston engines was investi- gated in a study conducted by the Lockheed Georgia Company (ref. 2). Figure C-11 is taken from that study and it distinguishes between the different classes of engines de- fined earlier. Note that the price to an original equipment manufacturer (OEM price) shown on figure C-11 is approximately 60-65_ of the selling price usually quoted.

Engine Performance - A simplified general model for engine performance includes part throttle horsepower, full throttle horsepower at altitude and the specific fuel con- sumption. Figure C-10a is a generalized curve of the fraction of maximum rated horse- power with the fraction of maximum throttle setting. The throttle setting represents reduced speed for non-supercharged engines or reduced manifold pressure for super- charged engines. The curve is not linear because most engines have better volumetric efficiency at part throttle settings for better cruise fuel economy. Specific engines may deviate by as much as =L0.03 in fraction of rated horsepower at throttle settings of 0.9 and below.

Power at altitude is shown in figure C-I0b for non-supercharged engines at 100% throttle setting. The parameters $ and a are the non-dimensionalized values of ambient pressure and temperature as defined in the figure. For supercharged engines the rated sea level power is assumed constant up to a specified altitude--generally 15,000 (4580) to 20,000 ft (6100m).

There were not stffficient data available to correlate specific fuel consumption (SFC), but at maxinmm rated power the SFC is generally 0.5 (0.3) to 0.55 lb/hr/hp (0.33 kg/hr/l_i). This value can be assumed constant for a 100% throttle setting at al- titude, but at part power the SFC is reduced. Typical cruise values of SFC at cruise (65-75% power) are 0.42 (0.26) - 0.48 lb/hr/hp (0.29 kg/hr/kw).

Rotary Combustion Engines To date there are no rotary combustion aircraft engines in production. However, the Curtiss Wright Corporation, sole North American licensee for aircraft rotary en- gines (Wankel design), is developing water cooled rotary engines for light aircraft; ancl they supplied engine weight and dimension data for use in this study. No engine per- formance is included in this section because it is assumed that engine power at altitude and fuel consumption are identical to piston engine performance.

For the:study, Curtiss Wright supplied data for two levGls of engine technology: near term, 1975-1980; and far term, post-1980. Only near term data is presented in this appendix. An indication of the post-1980 improvements in engine specific weight is given in Table X of the main text.

Engine Weight - As with piston engines, rotary engine specific weight is reduced at increasing rated power, as shown on figure C-12. It is apparent that specific weight approaches a minimum value at some rated power above that shown on the figure. In- creasing the number of rotors for a given rated power reduces engine specific weight sigrlficantly.

Engine Dimensions - The increases in engine diameter and length with increasing rated power are shown in figure C-13. At a given power level, these dimensions can be varied considerably as the number of rotors is changed from 2 to 6.

El_._ne Cost - Curtiss Wright estimates of rotary engines costs, given in reference 2, are shov, u in figure C-l'. Distinction is made between near term engine costs and the reduced costs that can be expected for future engines.

Supercharger Effects - All previous data are for non-supercharged engines. Super- chargers can easily be adapted to rotary engines and they will affect engine specific weight, length and cost. An estimate of the specific weight of a supercharger (super- charger v/eight/rated horsepower) is given in the following table: Rated Horsepower (kw) 100(75) 200(150) 300(225) 400(300) 500(375) Supercharger Specific Weight lb/hp (kg/kw) 0.4(0.25) O. 35(0.21) 0.28(0.17) O. 25(0.15) O. 25(0. 15) The engine length is affected significantly by the addition of a supercharger, par- ticularly if the installation is constrained not to increase the envelope diameter. In this event, the engine length is estimated to increase by twice the engine diameter. To account for the cost of the supercharger, engine specific cost (OEM cost/rated horse- power) is estimated to increase by 30% for turbosupercharged rotary engines.

Turboprop and Turboshaf:. Engines The distinction between turboprop and turboshaft engines is the addition of a gear- box supplied with a turboprop engine which affects engine length and specific weight.

Distinction must also be made between engines designed with axial compressor stages and/or centrifugal compressor stages since this will affect the engine length.

Data for e:cisting production engines and a very few prototype engines arc listed in Table VU. These data were taken primarily from "Janes All the World's Aircraft, but in several t,_stances manufacturers' published data were used.

En_ne Weight - The most common measure of engine size is the sea level rated horsepower. Figure C-15 shows engine weight plotted against sea level power. The tread of increasing weight with power is clearly established, but there is considerable scatter in the data.

A somewhat better correlation is obtained by plotting engine weight against airflow at sea level power as shown in figure C-16. This is to be expected since the airflow is the major factor in sizing the engine components. Also, the effect of the engine cycle parameters (compressor pressure ratio, turbine inlet temperature, etc.) on the engine specific weight can be estimated with this correlation: Power/Airflow = f (Cycle Parameters) Weight = f (Airflow) Specific Weight = Weight/Power = Weight/Air flow/(Power/Air flow)

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Using Che lines drawn in figxtres C-15 and C-16, the specific weight and the weight/ aikflow ratio are plotted in figure C-17. Specific weight is diminished as rated power (or airflow) is increased. However, it is apparent that a minimum value is being ap- proached at the higher power levels.

En[ine Dimensions - Depending upon the engine design, the maximum frontal di- mension can be an envelope diameter, a width, or a height. The data given in figure C-18 makes no dlstflnction between these dimensions referring only to a maximum frontal dimension and plotting it against sea level power. Since no engines with offset gearboxes are included in the data, both turboprop and turboshaft engines are included.

Also, the correlation is tmaffected by the type of compressor. Intuitively, one would expect a smaller froutal dimension _th an all-axial compressor, but this trend is not evident from the few engines plotted at 3000(2240) - 5000 horsepower (3740 kw) which have axial compressors.

The engine length, on the other hand, is affected by the type of compressor. As would be expected, engines w'.th all-axial compressors are longer than engines having one or more centrifugal stages as shown in figures C-19 and C-20. Also, the addition of a gearbox adds length to the turboprop. Below 1000 rated horsepower, engine length appears independent of rated power. These engine:s 'all have centriflLgai compressor stag.es___ Engine Cost - Estimated OEM costs have been made in reference 2 for both turbo- prop and turboshaft engines. These e_timates are duplicated in fi[_we C-21 with the data extrapolated out to 5000 horsepower to be consistent with the data shown previously.

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SPECIFIC WEIGHT OF SUPERCHARGED AND/OR GEARED PISTON ENGINES 2.50 - 1.50 - Non-supercharged/geared engines 1.25 - 2..00 - <) 1.00 - A , I I I 1.50 I

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Next: APPENDIX D →

APPENDIX D

Q- FAN COMPUTE R PROGRAM FOR GE NERAL AVIATION AIRCRAFT

Performance, noise, weight and cost generalizations based on the methodology

discussed in the main text were computerized+ With this computer program, parame-

tric studies can be made which permit the evaluation of trade-offs among these factors

for various configurations. Variations in Q-Fan diameter, 2 - 7 feet, total activity fac-

tor (750 - 3000), activity factor (120 - 270), 0.7 integrated design lift coefficient,

number of blades (5 - 11), duct length/rotor diameter ratio (0.65 - 1.20), rotor to

duct exit area ratio (0. 8 to 1.1) for a tipspeed range of 450(137) to 800 ft/s (244 m/s).

Specific cost criteria based on a unit cost factor, a learning curve and manufacture

quantity are included as well as the option of inputting these quantities.

The computer deck is designated Hamilton deck H604 and is programmed in

FORTRAN V. The following are the pertinent input/output instructions.

Program Input

The first card includes the card number in column 3 and any legal Hollerith

punched in columns 4 through 72. The second card contains the following input data in

an (I3, 3X, 10F6.0) format:

1. Card number

2. Initial diameter, ft.

3. Increment in diameter if a range of diameters are to be computed

4. Number of diameters

5. Initial total activity (TAF) (the computer will select activity factor/blade,

number of blades and duct length/rotor diameter ratio corresponding to minimum

noise.

6. Increment of TAF if a range is to be computed.

7. Number of TAFs

8. Initial rotor to duct exit area ratio, A.R.

9. Increment of A.R. if a range is to be computed

10. Number ofA. R.s.

11. Variable pitch = 0., fixed pitch = 1.

The third card contains the following input data in a (213, 7F6.0) format:

1 Card number

2. Number of operating conditions with a maximum of 10

3. Time period. Code 1970 or 1980 whichever time period is being studied.

4. Airplane classification (Table IO). It is to be noted that the Q-Fans weight

and cost generalizations are not applicable for category L

5. Mount - If gear box weight presented in section on gearbox generalizations is

to be used, code mount = 1., since mount and gear box weights are combined. Other-

wise code 0.

Items 6 through 9 include the various cost options. Code all of these items as

zero if the ecst criteria built into the computer program i_ to be used. It is defined

as follows:

C=ZF(7.00"5+ E)

C I= F(7.00"5+ E)

Where: C - Average O. E. hi. Q-Fan cost for a number of units/year, S/lb.

C ! - Single unit O.E.M. Q-Fan rotor cost, $/Ibs.

LF

Z

LF I

LF

- Learning curve factor for a number of units/year

LFI

- Learning curve factor of a single unit

B - Number of blades

F

- Single unit cost factor

E

- Empirical factor

The 8§% slope learning curve is used and F,E and quantities are defined as

follows:

1970 1980

Cate_;ory F__ E._ Quantity F. E___ Quantity

II 2. i I. 5 2810 2. ! i. 5 5470

llI 2.1 3.5 1030 2.1 3.5 1990

IV 2. i 3.5 295 3.2 3.5 680

V 2.4 3.5 65 3.6 3.5 368

If any deviations are required, the following additional information must be coded.

Learning Curve Variation. It is based on a_suming that a learning curve is a

straight line when plotted on log paper. The learnLng curve is replaced as follows:

6. Learning curve factor for a single unit

7. Learning curve factor for 1000 units

Unit Cost Factor: If a revision in unit cost is required, code as follows: 8. unit cost, S/lb.

Quantity Variation: To investigate the effects of quantity changes on cost, code

as follows: 9. Quantity to be used.

Subsequent cards are coded as follows _Ith an (16, 8F6.0) format: i. Performance variations; KODE:

KODE = 1 for defining condition with thrust, (lbs.)

KODE = 2 for defining condition with power, SHP

KODE = 3 for defining condition with blade angle for fixed pitch application

SHP or thrust/Q-Fan or blade angle corresponding to option specified in (1)

3. Altitude in ft.

4. Velocity in knots, true airspeed. Code a condition corresponding to 66 knots

for calculating of noise, weight, and cost.

.A --= .............................

5. Temperature in °F. If standard day, Code = 0.

6. Pressure in lbs/ft 2. If standard day, Code = 0.

7. Initial tip speed, _rND-----2 fps

8. Increments of tip speed if a range is to be computed.

9. Number of tip speeds.

For subsequent cases, repeat all the input data previously specified.

For termi-

nation code a card with 25 in an (I3) format.

Progra_n Output

The input data prints out initially and then the pertinent data under the following

headings: 1. DL_. FT - rotor diameter, ft.

2. T.S. FPS - tip speed, fps

3. NO. BL - number of blades

4. AF/BL - activity factor/blade

5. L/D - duet length to rotor diameter ratio

6. SHP - power

7. Thrust - net thrust/Q-Fan. Includes shroud external and internal drag

losses and inlet ram recovery losses.

8. ANGLE - blade angle at 3/4 radius

The follow.ng items print out if velocity = 66 knots.

9. PND)J

- perceived noise level at 500 ft. side line in PNdB

10. DBA

- Weighted decibel, dBA

11. WT-LBS

- Q-F_u weight in lbotmds

12. COST

- Q-Fan cost in dollars

For the option where tip speedis varied, the calculations are made for the input

ranges in the following order

1. Tip speed

2. Diameter

3. Total activity factor

4. Area ratio

5. Operating conditi3n

The following warnings or messagesprint out

'TOTAL ACTIVITY FACTOR OF 'F6.3', EXCEEDS LIMITS' - the input TAF

exceeds the permissible 750-3000 TAF range. Check to see whether ATAF

or number of TAF's result in exceeding tim limit.

'KODE IS AN ILLEGAL NUMBER, KODE = ', IC' - the input item specifying

whether the horsepower, thrust or blade angle option is required has been

included as other than 1, 2 or 3, the only options available.

3. 'ADVANCE RATIO TOO HIGH = F8.4' - check to see whether the input diame-

ter, rpm, and velocity are correct. The advance ratio limi_.s are 0 to 5.

'AREA RATIO EXCEEDS LIMITS/AR = F3.0' - the input AR exceeds the

permissible 0. 8 to i. 1 AR range. Check to see whether, AAR or no. of AR's

result in exceeding the limits.

5. 'BLADE ANGLE = F4.2, EXCEEDS LIMITS OF 21-60 DEGREES' - check to

see that for option KODE = 3, the input blade angle is within the limits.

'MACH NO. OF TIP SPEED LIMITS ARE EXCEEDED/MACH NO. = F4.3,

TIP SPEED = F5.0' - the input exceeds the Mach No. limits of 0.0 _o 0.5 or

the tip speed exceeds the limits of 450 - 900 ft/s. Check to see whether Atip

speed or no. of tip speeds results in exceeding the limits.

'CPE = F5.3, EXCEEDS THE CPE LIMIT = F5.3' - the power or thrust re-

quirement exceeds the limits of the generalization. Reduce power or thrust

and try again.

8. 'ILLEGAL AIRPLANE CATEGORY' - the input value for airplane category no.

is other than the perrr2ssible 2. - 5.

9. 'THE I)IAMETER RANGE OF 2-7 FT. IS EXCEEDED; DIAMETER = ' - the

diameter exceeds the 2-7 ft limit restrictiol_ for noise computation.

i0. 'TIP SPEED = F6.0, EXCEEDSLIMITS FOR NOISECALCULATION' - the

permissible tip speedrange for noise calculations of 450 - 800 ft/s has been

exceeded.

'THRUST/DIAMETER SQUARED= F5.0, EXCEEDSLIMIT FOR NOISE

11.

CALCULATION' - The thrust/diameter squared is too high. Reducethe

thrust or power requirements and try again.

Sample Cases

Codingfor three sample cases of the input are shownin figure D-1 and the corres-

ponding output are presented as figures D-2 through D-4 respectively. The sample

cases are presented in the following order:

i. The condition is defined by thrust, tip speed, AR and diameter variations and

request for performance and cost calculations based on the information included in

the computer program.

2. The condition is defined by power and tip speedand diameter variations and

request for performance.

3. The condition is defined by blade angle andtip speedvariation.

Computer Deck

The flow chart for the computer program is shownon figure D-5 and a listing is

presented as fig_areD-6. The computer program has been run on an IBM - System/

370. Approximately 500operating conditions are computedper minute.

_ _ o °.

,_ o 8 8 8 _ _ o°°',_ o_ o_ _ £'.'_, _'_ O' .<.1

_ _-_

._ _ _ _ oo

o o,_ _ _ _"

_,. ,_._o_ z_._ oe_.._, o..:.1 o _ o_ _lr-I

_,_ o_ o_ o_

_1

_l 1_ _ ,_ oa _

.- _ _o.o_!_ _ _

• _l _i _

Z m I- n Z ILl ._1 n I 11: ee • e e+ HAMILTON STANDARD COMPUTER DECK NO. H_C4 C.RMPUI'ES PERFnRNAfSCE,NCISE,WFIG|-,-r, ANE COST FOR GENERAL AVIATION O-FAf_S SHP I_,!PUT -- TIP SPEED, AR, _NO P,IA. VARIATIONS ")PERATIRG CONDI TION Sir _ = 550. CLASSI FICATION : 5. CLri : 0.3 ALT- FT = 20009. GbA O B,l× = 1. ELF : 0.3 V-KTAS = 245.0 DATE =1980. SCING : O.O T E',IP F : 0.0 QL_D,T : O.

PRESS. = O. PITCH TYpE 0 IJTAL ACTIVITY FACTOr= 1500. AREA RATIO : 1.000 D[;, FT T.S.FP£ SHP THRUST ANGLE 3.50 600. 550. 514. 58.1 3.50 650_ 550. 522. 54.2 3.50 700. 550 • 524. 50.8 3.50 763. 550. 51 9. 47.9 4.30 600. 55 ] • 520, 54.0 4. O0 650. 550. 526. _0.6 4.00 700. 550. 525. 47.5 _.00 750 . 553 . 517. 44.7 T)TAt ACTIVITY FACTOR: 2500. AREA RATIO = 1.000 OIA FT T.S.FPS SHP THRUST ANGLE 3. 50 6'30. 550. 518. 54.1 3.50 650. 553. 518. 5C.6 3.50 700 . 550 . 512. 47.6 3.50 750. 550. 501. 44.9 4.30 630 . 550 . 513. 50.8 4. O0 650. 550. 510. 47.6 ....

4.00 7'30. 550. 504. 44.7 4.00 ....... 7_0 . 550 , 494. 42.2 T]TAL ACTIVITY FACTQR: 1500. AREA RATIC : 0.900 DIA FT T.S.FPS SlIP THRUST ANGLE 3. bO 61',' .- 550. 520. 57.4 3.50 65,]. 550. 528. 53.# 3.50 790 . 550 . 529. 4£.8 3.50 750. 550. 526. 46.6 4,00 600 . 550 . 53C. 53.0 4. O0 650. 550. 534. 49.3 4.00 (90. 55'3. 534. 46,0 4.00 7-;0 • 550., 528. 4-_.2 T]TAL ACTIVITY FACTQU= 2500. AI,EA RATIt] : 0.900 DIA FT T.S.FPS SHP THRUST ANGLE 3. 50 600. 550. 52_ 53.0 3.50 650. 5_0. 526. 4_.4 3.5 0 700. 550. 52 t • 46. [ 3.50 750. 550. 512, 43.2 4.30 600. 550. 526. 4£. 3 4. O0 650. 550. 524. 45.9 4.00 700. 550. 51 ?, 43.0 4.00 ?SO. 550. 51 1 • 4,0.6 FIGURE D--3. SAMPLE CASE II OF COMPUTER PRINT OUT U3 ,k_, -;.,,_ : "u ',4" CD ,,0 U_ .'% -,,1"

=./4..,' _

._.1 0", o I0 r,,- I i-- __ 0 II 11 II I1 '.9,-- .4.4; ..., o 0 ..-* II II II LU Z ,"_ _- _,. ....,I, _ '._ ',-, ',..'D ..) 0 '-'_ 4_ I1 I1 II II tl Z-_ I u_n_ -' "." ''"*'_;_'I_'_-._'_',.<*'_.. --._, _-.i''_o"

,1

(MAIN)

___ READS INPUT.SETS

UP VARIATIONS IN

DIAM ETERjTAF, AR t

i -1

AND TIP SPEED

(ENG DAT)

ilPE.FM_

(PERFM)

f (PERFM) .

THRUST GIVEN ]

THRUST & BLADE

POWER & THRUST

POWER & BLADE /

CALCULATED

POWER GIVEN I ANGLE CALCULATED

BLADE ANGLE GIVEN,]

ANGLE CALCULATED t

t

DAT)

NO

Y,Es _ (QFNOIS)

l NOi SE

CALC, ]

_ (WTQFN)

WEIGHT

CA LC. 1

_ (QFCOST)

COST

CALC. J

YES HAVE ALL CONDITIONS

NO

FOR THIS CASE

[,,,_

BEEN COM PUTED

FIGURE D--5. FLOW CHART FOR H.S. DECK H604

I,A,MILT_IN STANDAR[' COMPUTER [)ECK P604 -Q-FANS FOR GENERAL AVIATI3N r;iu ENS It)N CNRL( 31),CLOD(27},JKODE! IC),ALT(I0) ,VKTS(IO},TC(IO), I r_o(13) , TPSP(IO),OTPSP(IO ),XTPSP(IO),TIIRUST(IO),SHP(IO),ANGLE{ 10) P'_TA CN ql / I. , I. , 6. ,'_. , 750. , I120. , 1500. ,I 90J. ,2480. ,3000 .,650 . , !75C'.,8J 3., 5.0,b.O,6.0,6.4, ?.4, _.C, _.C, q.O, g. 92 ,8. 8,g. 8_ll.O, 9. 92 , 211. O,ll • O,tt.O,t l.O,ll.O/ I;AT "_ CL OO /2.,1.,5. ,3.,750.,960. ,2C00. ,2420. ,3000. ,650.,750. _800., I .716,.6 _0,,.675,.75 v, .714,.6Q3,.955, .qlS, .897, 1 .032, 1.003,.99t,,._ ?.I. ] 36, [ • 136, i. 136/ PCP P_4= l .0 ZF t _G=I m CR= I.

_JF=I 5 WRITE ( 6, I} I F:OPMAT ( 'I',I8X,'HAUILTON STANDARD COMPUTER DECK NO,, I(604'/[4-X,'COM IFgTFS P FRFORMANCE,NCISE,_EICHT, ANt?, COST FOR'/25X, 'GENERAt. _VIATI3 2_ C-FAN S') P__AD (5 ,I0) ICARC 10 I T)R'-IA T ( I 3,69H

t )

IF ( [CAR _,.E0.25} GC To 6000 V,R ITE( 6 , I0) ICARO FtAD (5 ,20} 0 iA, ODI A, XDIA, TA F I, DTAF I,XTAF I,ARI ,DAR I , XARI , l XF P , KWR I TE I Fr'=XFP +.01 2 ) FL;PMAT(6X,IOF6.0,I6t _:)IA=XDIA+.OI r,TAPI=XTAFI+.OI NAPI=XAP, I+.OI PEAD (5,30) NOF,XDAIE,CAIN,GBOXM,CLF1,CLF,SCING,QUANT 20 F L}FMAT(BX,13,1OF6.@ I [.J 50 IC=I,NOF I;EAO {5,40) JKODE(IC),TEMP,ALT{ IC),VKTS(IC),TO(IC|,POIICI,TPSP(IC) I ,_)TPSP( I C ), X TPSP { IC ) 40 FOPMAT(_X,13,1OF6.0) IF(JKOOE(IC).GT.1) C-O TO 42 THP UST( IC )=TEMP Gq TO 50 42 IFIJKOOE(IC) .GT.2) GC TO 44 SHP(IC) =TEMP G9 TO 50 44 ANOLF{ IC)=TEMP 5O CO_,_TINU [: I'_ATE=X[)ATE+.OI b q 5000 IC=I,NOF POPO=O.

NTPSP=XTPSP{ IC} H=ALT(IC) TO=TOIIC) PO=PO(iC) WRITE (o,5S) SS FQ,qMAT (/23X ,' OPERATING COM')ITION'/; KKOE=J_ODE|IC) GO TO (60,?O,801,KKDE _0 WRI TE (6,65) THRUST(IC|,CAT/_,CLFI 6b FqRMAT( iHO, 2X,'THR,IST =',F?.C,5X,'CLASSIFICAI"-ION --' ,F5.0,_X,'CLFI FIGURE D-'-6. LISTING OF ADVANCED GENEI:_a_,_. AVIATION Q--FAN PROGRAM (PAGE 1 OF 26) 9-35 # o ! =;,r6 .2) (-(] TO 90 70 KK_E=7 WRITF (6,75) SHP(IC),CATN,CLFI 75 Fr_RMAT(IHO,2X,' SHP :' ,FT.O,5X, 'CLASSIFICATION =', F5.0, 4X, 'CLFI I : , , F6 .2-) G(] TU g O _'0 KK[_E=F) _'RITE (6,853 ANGLE( IC],CATN, CLFI F_5 F(]PMAT(IHO,2X,'ANGLE =' ,FT.O,SX, 'CLASSIFICATION =', FS.O, 4X, 'CLFI I =', F,S.?)

90 WRITE (6,953 H,GBOXM,CLF,VKTS(IC),XEATE, SCING, TO,QUANT,POtIFP 05 FDRMATI3X,'ALT-FT =',FT.O,5X,'GEAR BCX',BX,i=',FS.0,4X,'CLF =', IFS.2/3X,tV-KTAS =', FT. I,_X,'OATE',I2X, '=',FS.0,4X,'SCING =',F5.[/ 23X,'TEMP F =',FT.I,31X,'_U_i._T =' ,FS.0/3X,'PRESS. =',FT.O, 35X, 'PITCH TYpEI,EXpI5) ARA=ARI-CARI OF) 4000 I=I,NARI AR A=ARA +DAR I TAF =TAF I-DTAF I PO 3000 J=!,NTAFI T AF=T AF ÷CT AF I IF(VKl_S(IC).NE.66. l GO TC ?R5 WRITE (0,2803 TAF,AP.A 2F_O F[]PMATIIHO,' TCTAL ACTIVITY FACT'OR=',FT.O, , AREA RATIO =',F6.3 If' DIA.FT. T.S.FPS NO. BL _F/BL LI_ SHP THRUST AI_GLE PNDB 2 r)_A WT-L BS COST ' ) C,O TO 2 89 2_5 WRITE(6,288) TAF,ARA 28R FORMATIIHO,' TF)TAL ACTIVITY FACTOR=',FT.O,' AREA RATIO =' iF6.3 1/' gIA FT T.S.FPS SHP THRUST ANGLE' | 289 DRt]T=D I A-DOT A F)FI 2000 K=I,NDIA DRC_T= DROT +DI) IA TS=TPSP(IC}-DTPSP(IC) DO 1000 L=I,NTPSP II=O K liE, E =KKDE TS=TS÷D TPSP{ IC) XNMAX=60._TS!{3.14161Y_DROT) [._EFINITION (3F N(]. OF BLADES AND AF AS F(TAF,TS) IF(TAF.GE.750..AND.TAF.LE._O00.) GO TO 310 WRITE (6 :?.903 TAF 290 FORMAT( IHO_' T(]TAL ACTIVITY FACTC_R OF' ,F6.3,' EXCEEDS LIMITS'I GO TO 6000 310 CArL (_'LINE (CN'_i,I,TAF,TS,F_L,LIMIT) IRL=BL÷.5 BL = I BL AF=TAF/BL CALL B_LINE (CLOD, I,TAF,TS_COD,LIMIT) 315 CAIL ENGDAT {XNMAX,PCRPM,GR, DR{]T,TFRUST(IC),SHP(IC|,EFFP, VKTSIIC), IRORO, KODE,IERROR,WQFT,CQFT,BMEP,ZNQFTI,ZNQFT21ANGLE(ICItNOE,CATN, 2 PO, TO, BL, AF, COD, ARAt /- FLAG, GMOXM, IDAT E, QUANT, CLF I,C IF, SC ING, 3KHP I TE , H, IF,) IT= II÷l IF(VKTS(IC)._E.66.| GC TC leO0 FIGURE D-13. LISTING OF ADVANCED GENERAL AVIATION (_-FAN PROGRAM (PAGE 2 OF 26)

CO TO (320,340,360,3_0)tlI

kO L)E: 21

CU TO 315

34C !F (QUANT.EQ.O..ANO.CLFI.EQ.O.._NC.CLF. FQ.O..AND.SCING.EQ.O.) KODE 2

i=l i. i

(QUANT, EQ.O.,ANO, CLFI,f_E.O..ANE,CL_.NE,O.,AND.SCING.EQ.O.) KODE I

I--L 2. 1

IF ( QUANI ,NE,O. ,ANO.CL F1 . EQ .0 . ,AND,CL F. EQ, O, ,AND.SC ING.EQ. Oo ) KC])E

i= i 3

IF (QUANT.NE. O..AND.CLF IoNE.O..AND.CLF. NE. O. ) KODE= 14

IF (QUANI.EQ.O..AI_D. CLFI.EQ.O.._NC.CL F.EQ.O..AND.SC ING.NE.O. l- KO)E

l=I

IF (QU ANT, EQ,3, ,ANO,CL FI,NE ,0 ,.AND ,C LF.NE, O. ,AND, SC ING,NE, O. ) KODE

i=t6

C'J T[] 315

3(0 _UDE=31

CO TO 315

3FO CONTINUE

WRT rE (6_390) DRCT_TStEL_/_F,CCCtSHP( [C)_THRUST(IC) tANGLE( IClt

IZNOFTlt ZNQFT2tWQFTICOFT

300 FORMAT (F't.2,F8.0,F7.0, FT.I,F6,3tF7.0,FS.0, F6.I,FS. 1,F7. I,F8.0,FS..O)

I)

GO TO t 000

6C0 WRITF.(6_z, IOI DROTtTS_Sl4P(IC)tTHRUST(IC)tANGLE(IC)

410 F3RMAT( F8,2._ _F 11. O,F1 O, 0 tF tO, i)

IOCO CONTINUE

20C0 [ONTI NUE

3OCO CONTINUE

40CO CONTINUE

5000 CONTINUE

or} TO 5

6000 CONTINUE

END

FIGU RE D--6. L.ISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM

(PAGE 3 OF 26)

23?

bU_,_)UTI ,E bNGOAT {×NMAAtPCRPM_GR, OkGT_ TrIRUSTtSrIPtEFFP_VKTSIMUROt [_UUZ, I E_,UK ,WwFT ,CI_FT,I_ MEP, ZNQFT L, ZN_FTZ, BLANG,NOE, CA TN, Z PO, TO,_L,AF,.CO0 tARAI, ZFLAGTGBUAM, IOATE,_UANT, CLFI,CLF,SC[NG, 3KNRITE,X,IFPI ,IbC ,H ,ST COMMdN /UNIV/ NPC ,NSC ,R ,_ ,ALPHLO,CLALPH,SW I,_F ttM ,VMO tEMMO ,A_, tB 2EYE_ ,_ ,_P , TA , wL_ ,WGS tKwR [(E,OLHC_ _,KSI ZE COMMDNIP,_P OAT/ZJ I,CP,CT K_RI TE=KRk[ TE _I=X 30) KPM=XNNAX_:PCkPM*GR AFT=AF*BL IF (KODE GT.LO) Gd TO 50 IF (KJL)E.LE .b) KPERFM=2 i_ (KdDE.EQ.7) KPERFM=I IF (KODE.GT.I.A_O._.ODE.LT.LL) KPERFM:3 5J IF {KUOE.LT._/_) GO TO 350 mRITE (6,55)KODE 55 FORMAT (LH0,3X,'KODE IS AN ILLEGAL NUMBEK,KUDE=,,13) I ER_,OR: i GO, TU 5UOO 350 I I PSPD:. 0523b_RPM_DROT _OO] IF (KuDE.LT.I]) GU TO 4uO IF (KUDE.LT.21) GO TO bc)O IF {KUDE.LT.31} GO TO GOO CALL _FNLJ[S (AF,13LI TIPSPO_THRUST,DRUTt ZN_JF T i , LN_F T2 _ hUE, IIERkOR,K_RI TE) Gu TU 50JO Q OU CALL PERFM (TO,PO,RORO, H, TIPSPD,SHP,THRUST_VKTS,OROT,AFTtARA,CO0t ]. r_PERFMt BM_P, OL ANG, RPM, [ ERROr, tFFP,u_, K,_KI TE) Gu To 5OJO CALL QFCOST (CATN,IOATE,C_JFT, IE_ROR,KCIOE,CLFI,CLP,CQUANT,BL_SCING, I IFP, KhRI TE } GO TO D_O0 CALL wTQFN( _L, DROT,AF,SHP, TIPSP[), CATN, ZFLAG,GL_OXM,W(_FT, IDATE,COD, i IFP, _.mRI TEI 50O0 bETURN _NL) FIGURE D--6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE. 4 OF 26) 2.38 SUbPGUTINE PERFM (I,.,PO,RORO,H,TIPSPL,SHP,THRUST,VKTS,OROT,AFT,ARA I ,CAD, KPER FM,BMEP,_ILANG ,RPM, I EPROR ,EFFF ,GR, KWR ITEJ CIFENSION AAFI (II) ,APAFT(11),ATAFT(86), ACO0(37),CTT(7}, ICFP(7} ,BLLIT),ATS(9),APMN(9) ,AJ(5I,AM_(5},ZJJ(TI,BLLL(4),CTIT(TI, 2CPPP(4),SHP_.(7;,RPMP(CI,SHPP(_),XAR(4),TS(7},TIPS(4},ATHRST{41 t 3ASF P (_) ,At TFR(11) , PPESSR(ii) ,CI ANG(I6,7,4) ,BLLCH(53) , 41A_ (4) ,ATMN(?2},BLDANG(I>,7,k},CPAG(12,7,4), 5CPIVL (5),CPP,4J(5),CPAI%G{ 16,7,4|,INN(7,4} , INA(7,4| CIIvFNSIGN DIII!2},U2(II2},DBIII2),O4(I'2),EI(II2J,E2(II2),E3{lI2) , IE4(I 12 |,61 (£4) ,02( 84|, 03( 8&} ,G418 L ) ,HI(_4} ,H2[ 84) ,H3(84) ,H4| 84 l 2.,AI(42),A2(42},AS{42), A4{42) ,CDCT(42,4] ECQU[VALENCE(UI,(.TANG(I,I,I)),(DP,CTANGI i, 1,2}),(05,CTANG(I,I,3_l, i (D4,CTANG(I,I,4} },(I!,CPANG{I,I,I)I,IE2,CPANG( I, 1,2)I, (ES,CPANG(I, 21,3)), (E4,CPANG(I, 1,4) ),(GI,CPAG{ I,I,I)},(G2,CPAG(i,I,2) ),{G3,CPAG 3(i,I,3)), (G_-,CPAG(I,I,_.)I, (HI,BLDANGII,I,I)),(H2,BLOANG( i, 1,2i }, _.(H3, BLDANG{I,I,3)),(He-,BLDANG(1,1,4) ) 5,(AI,CIJCT(I,I) },(A2,CDCT(1,2I),(A3,CDCT(I,3)I,(A4,CDCT(I,4) ) L;AIA AA('T /750-,I000.,17_0,.,1500.,1750;.,2000.,,2250.,2500.,2750., i-_000., 3250./ F.AIA APAFT /1.9,1._,1.31,i.17, I.078,1.,.94,.9,.80,.825,.805/ DATA ATAFT /I-,6.,Ii.,0.,i.,2.,3.,4.,5.,750.,i000., 112_0., 1500.,1750.,2000.,2250.,2500.,2753.,5000.,3250.,I.54,1.52, 21. 195, I. i O, I. 04, I. _, .965, . 94 ,. 912 ,. 89, . S75, 1.095 _ 1.375 , 1.228 _ I "12 t 31.052, I. 0,-96, -92, • 595 ,.87,. 845,1.99,1 . 51 , 1 .31,1.16, i. 07,1.0, .95, 4.90,.965, .84,.82,2.h-15,1.708,1._,08,1.21,].087,I.0,.93,.875,.855, 5.81,.782,2-95,1.95,1._25,1.27, i. I18,1.0,.915,.848,.795,.765,.738, C3.56,2.22, 1.665,1.33,1.1&,I.0,.89,.805,.740,.690,.665/ EATA ACOD /2-,4-,6.,-0,1.,3.,5.,.7,.e,.9,1.,I.i,I.2, 1.0005, .0003, .GO01, .0,- .0005,-_. OGl ,. 00&,.0035,. 0018,. 0,-. 0038, 2-.0065, .020, .0 la2, .0078,. 0,-.0085,-. O167, .050, .037, .020, .0,-.0252 , 3-.05_/ DATA XAR /-_,.S,I.O,I.I/ EATA IAR /8,9,10,11/ L'ATA ATS /350-,400.,_'50.,500.,550.,600.,700.,800.,900./ L.ATA APMN/I-O, 1-002, 1.006,1.012,1.025,1.0385, 1.065,1.0885, l.lO/ DATA ZJJ /-0,.5,1.,2.,3.,4.,5./ L DATA ALTPR/0.,10000.,20000.,30000.,40000.,50000., 160000. , 70000. , 80000. ,90000. , I00000. / [AIA PRESSR /I-0,.6877,.&595,.2970,.1851,.I145,.07078, 1.04419, .02741 ,.01699,. 01854/ DATA TS /350.,450.,550,,_50.,750.,850o,900,/ DATA Of/ 1.275,. 522,.714,1.002,1.316,1.692,2.039,2.12,2.18,2.22,3.04,5.215, 23.52,3.83 5,4.02, O. , 3.17,.336,.6900 1.391,I.586,1.868,2.13,2.78,2.518,2.725,2.970,3.370 43.60,3*0. , 50.,.104,.494,1.042,1.313,1.551,1.718,1.900,2._35,2.615,3.035,3.285 6,4*0., 7-.075, . 139,.._82,. 590,. 691 ,.936,1. I76,1.294,1.349, I .528,1.762,2.125 8,2.5] 5,2. 7455,2,0., 9-.423,-.[59,oI14,.&32,.940,I.036, 1. 132,1.22?,1.44,1.695,2.07,2.278 1,4_0., 2-.34,.047,o226,.396,.530,.&54,.800, 1.069,1.5,1.625,1.84,5"0., 3-.t2,-. 127,. 148,.451,. 736,. 918, 1.262,1.4&2,8"0./ [ATA D2/ 1.22,.634, .890, i.170, I.50 e., 1.777,2.05a,2.406,2.505,2.qa,3.167,3.61, FIGURE D--6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM

(PAGE 5 OF 26)

9.89

3.125,. 279,.444,.STt,.783,1.1e8,1.646,1.901,2.18,2.325,2°505, 4!.2k,3 ,,, bSL,,! ,, 88,2____, 5".015,.028,.351,.539,.816,1.081,1.377, 1°836,2.025,2.385,2.90,3.365 ._.,..3 ° 56, 3 _Ii.,,._,.

7-.186,.008,.237,.483,.740, 1.047,I.329, 1.61g,1.869,2.31,2.7_,,2.90, 84*0. , _-.403,-.097,.189,.522,.816,1=161, I.658,2.13,2.315,7,0°, 1 -,._5, -. 19_j -.0O_, ._t a_Z, _5L9_5, I. 463. I- 6____,_I_8OxB_Jl=_, 2-.645,-.136, .093,.352, .910,1.196,1.350,9,0./ £ATA JJIZ 11_ 388,._i{,._097ji_6_,i.3_ 2.01_,2.s42,2o7,8,2.98,3.11,3.20_, 23_ 30, _. 5_ = 3° 790,3=_81 , ....

5 .De,. z 1s,. 5o9,. 4s3, 1. o 2x, 1. i69,7.7s_ 1;z. 2z 7,5._s9,_;._6,2. sz, 2. n, 42.82,3.085,3.30,3._6,

s. 034,. 2__,. _ 9,._ _,. _TL, _.___,t.36_, _. 9_, _.f68, _._i,L 3_,27%_i --

62° 7 _, 3.04,3. _. 8,0L*_ ......

7--I18,-.012,.250,.532, .871,i.138,1o431 ,I°675,1.923,2.11,2.2W, 82.52 5,2.(>85,3_0., 9--26,-.0_7,. I_4,.4_7,.

90_,1-368,1._80, I.518,I.762,2.08,2.22,5_0., I--50,- .287,. 016,.21 7,.

475**Z_Q*/_0-lZ, l_l_.t.2.B_,l._zSj_d_.27.5,O..

2 -.07,-. 505,-. 335, --14&,-037,-17,.297,.610,.84,1.22,1.32,5,0./ CATA D4/ 1.12,. 3 53, .519,. 729, .95 7,1.23,l.83L,2.337,2.k67,2.S4,3.212,_.54, 23-90, z_. 158,4°3 9,_3. , 3.04,. [77,.426,°624,.8& _, _ o_9, _ _9_,__9, _.9oo, _.2V_ 2_i; 2.%_]....

43.038, 3.45_,3.77,4.0B, 5-.(34G,-.006, .14C,.681t .9os,l._,_.77_,Z.oz_,_._,L_o,_.ose,_._, 63.62,3*0. , 7-°Z52,-.156,.033,.305, ;bO-O,. 875,l.242,1.871,2.315,2.76,3.02,5,0. , 8-" "= 35'-" 2 59' " 107, • 470, .994,1.4 i0,1.7,2Ai 1,2. _0,7,0., 9"1.133,-.692,-.263, "035, -Z94, • 572 ,. 789 , 1.075,1._78, i °70, 6,0. ,........

i-I.171,-.935,-.514,-.074, o140,.4"(@,.815,1.00,8,0./ t A ] A E I / . . . . . . . . . . .

1.18, .3 _.,._85,. 7_, I.ZI Z, i. 7{z9_,2.9-i__,2.(__3_, _5,5. .6. .8. .I 0..

211.2,0., 3.18,.348, .771,i.932,Z, _09,).0, _.6,_,,09,5,,6,, 8,j IQ,,II,2.,_0_, .....

4.1e,.267,.7_.6, 1.772,2.

439,3-2,3.8,_.60,0. ,8., I0. ,Ii.2,4,0. , 5-15,-5z'9,1.101,1.64,_, 925 , 2.65 l, 3._87,3,903,4_ _7; 5,00,6° _ _ t 8. z_ O__._ 6,11.2,2=0., 7-.229, .294,1.010,2.!Q_ • _i 11 ,-_-5_3, _. Q_}._ Z/,_. 6_, 8.. i O. • I I .2.

84*0., 9.18,1.624,2.407,3o20_, i.Ib,I.991,3._82,5.28_, 6. 939, 8. , 10. , I I • 2,8*0./ CATA E2/ i .18, ._I,. C35, .9',3, l. B7 _, 1.720,2.267,3.067,_.65,5.,8.,8.,I0.,II.2, 22_0., _elE, °304, °446, .601,.85

7, 1.,,_s, 2. _.9_., _. 8-i2, _.so,,,.o9,_., _., ,o. ,,__.2

4,2_0. , 5.1_:,. 22_,,. 529, ._, i .29_., I .8 16, 2. 502, 3. 857,_,. 60,6., 8., 10., 11.2,3_0., 6.0_4, . 337,°7(=9,1.36312°05,2.e95_,3,898_5._Q03_6._L _8.9_!0._t_ -_4_0._.0a2__ 7-.178,.481,1°288,2.(_57,3.588,5.063,7.458, _0.,11.2, 7"0., 8.16,.795, 1 • 502 , 3- 705,6o 3 i_ 8,916 t iQ.2 _ 1,2.____,_ !.......

9°I _, 2. 091 , 3.29g, 4.813,8. 079, I0. , I 1.2,9_'0°/ UATA E3/ 1.1e,.267, .355, .534,.781, I. 121,2.083,3°256,3.648,4._,5.2,6,0,6.8_, FIGURE D'-6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM

(PAGE 6 OF 26)

_40

.... _ _ .................. _ "_'_?'_-z-y" 7,;- .':;_ ', i.-, W"_, . - .....

2.L, i0. , 1 I_2.L ..........

3.18, .264, .327, .486, i. 168, 1. _5_ ;L z_i, LTT6; ,,. 0g _, 4,_. 2,6.0,6.848, _L,iQ..II.21 .......

5.197,. 398,. 646,. _l, 1.-,,I 6, z:sT4,2j97, _. 888, 4.663, S:2-_ _.6; g.-8,,8, _.....

.._IO- ; 11.2,0. ,__________ ,-Ai-_i,-6_-8 7. 187,. 342,. 83g, 1-525,2.453,3.261,4.218,5.119 48,8., I 0., 811.2,3_0,.

_.18,.678, 1.283,2.5,4.074,5.791,6.6_2,e.848,8.,I0., n.2,5.0._

i..i _ _i 766- i_. 869,Zo 7_9, 3 -9-_..£* _./I£,.__,._79 • _. _-_:,_,-IQ, • i.I_._ "__0_1 2.18,. 800, I- 600,2.635,3.606,4.375,4.957,6. 848,8. , I0. , I 1.2,5mO. / _ __DATA ._I ........

1-18'. 255,- 328,-%70,.674,. 980, I. 758,2. 593,2.84,3.65,5.,6.,8.,i0., 211.2,Q,, ._e,. 2 5_,. ,. _. _,. 6_-_,. _;01,1. _g_-;_: 7%2-, 2.30_ ,_. _,,-; 3. _;,,. 09, _. ,6. ,8., _IQ-, l.g, 5.1_, ._,. _,_,. 7-ti, _. gz: _,i8;_. ,,;.,g_. z_,.,,,.;:. _o,g ,8. ,1o. ;_1 ; 2-,_;6:-;- - ._- _7_ •., 21.1_, ,- _._..2J,_i-,Z 0 ]..,.1..,__.71.,3...,__Z_.___ 6.11.,,3_.._B_,__l.Q,._11,2,5" 0.,_.L ........

?-.147i.503,1.56,2.88T, 5.019,6°743,8.,10..i11.2.,7_0., 8-1.277,- 108, l,el 7, 2. 886, 4. _ 77, 5o4_'_7,6. 578,8,, |.0o,11.2,6*Q_ ,_ .....

9-.360, .509,2.442,4.738,5.994,8.,i0.,ii.2,8e0./ £ATA INN/ I 14,14,13,12,q,8,7, I14,1_*12,1_,9 j_*6, ........................................

115, ii, i0,14,12,1 i, 8, ll_,ib., 13 ,ii,9,10,8/ [_ATA [NAI - i12,10,_,12, iI,_I,8, --,12, i0, II,I0,9,9, I12,12,12, i2,12,12*12, _.

III, 12, i0,12,9, I0,12/ ................

CAIA Ol / 1-18,.3_,,.465,.788, 1.212,I.769,2.418,2.692,3.b5,4.65,5_65,6.60, 2o181 • 3/t81 ®771, Io952,2.309, _- O,4.og, 5.0,6.0,6.6,2"0., 3.1_,.267,.7z_6, 1.77_,2.43g,3o8,4.6,5o6,6.6,3,0., 4-. 345,. O, • 54_, I . IQI,I=_O, I=925,Z,_51,3.487,),90), 5.00, 6,11,6,b, 5-.860,-.580,-.229,.294,1.010,2. I03,4.111,4.547,5.008,5.477,6.64,0.

6'-" 164,'I •295,-. 815,-. 140, i.¢2%,2.%07,3.208,). 857,4.479,5. 224, 7(;.786,0., 8-2.25,-1.59,-i.32,-.4, 1.991,3.482,5.28&,b.939,4mO./ CATA G2 / i.i_,. 41,. 6_, .9_3, I. _7_,, 1.7_0,_,_67, _. 061 ,_,65,_.(_, _,65,6-6, 2 o18, .30_, • 446, • 601 , • 857, 1.485,2.392,2. 872,3.6,_. 09,5o65,6.6, • 18,.224,.529,1.294, 1.816,2.502,_o857,4.60,5.6_6°6,2_0°, _.-.218, .084, . 337, .769, 1.363,2.05,2.951,3°898,5.00_,6° ii ,6°6,0o , 5-I.1 _,-.885,-.955,-.178,.481,1.288_2.457,3.58815.06_,7.458,2_0., 6-I -86,-I- 57,-I. 19, -. 61 ,-. 795, i. 502,3.705, 6. 314,8. 916 ,B*O. , 7-2.84,-2.55,-2, 14,-i ,47,-. 17r2. Og| _ 5. 299,4.8_3r 8° 079/ CATA G3 / I .18,.267,o355,.53_,o781, Io_21,2.083_o256_3.648_5.2_6o0,6.84, 2.18, .264, . 327,. 487, i .168, I o_57,2. 231,3. 576, _.09, 5.2, 6.0,6° 8_ 8, 3-18,.197,.398,.646,.971,I.416_1.879_2._97_3.888,4.603,6.0,6.8W8, _-.28 ,-. 17, . 187, .3&2, .839, i .525,2. _5_,3.261 ,_. 213,5.119,6.111 ,6.8W8 5 ,-I • 06, -. 89, -. (_55,-° )_ t .l 8, °678 I_. °_8_r 2o 5_ 4, 07_ 15.791,6,642,6. 848j 6-1.81,-1.61,-1.32,-.9,.18, .766_i.869,2.7_9,_.964,5.314,6.679,6,848 7 ,-2.49,-2. 135,- i°51, .18,.80, 1.6,Z,6_5,3,606_4. )75,_, 957,6. 848,7o 2/ CATA G4 /

FIGURE D-'6. LISTING OF ADVANCED GENERAL AVIATION Q_FAN PROGRAM

(PAGE 7 OF 26) 2.18,.257, .438' "643, • 901, I- 262,1 • 792,2. 308,2.824,4. 134,5.37,6.6, 4-._75,-o165,.076,.211,.521,1 .i07,I.871,2°675,3.794,6.113,6o28,6.6, 6-2.44,-I. 678,- I. 277, • i08, i "617,2- 886,4- 177,5.437,6. 578,6.7,2_ Oot 7-3.76, -3.3_, - 1 _91B_ - i. 3/_3, -A B2_ ,_-..-36 O, • 509,2. _2,6. 738 * 5.99_ ,._-Z- _6.6/ • - E,_'[A HI I i 13.. !9.5,23.8,29.9,3b. 5, 50_ - i, 60_ I, 67.5,7_.9,81.5, 316"8,20- i , 31 • 1,44. O, 50.3,60.5,66.6,73.1 ,80° 0,3_0., 420.0.27., 3_'" 7' 40"3' 4_- 8'4Z*_ ,52.5,57 o9, (_0.5,b5.5,70o0,71 o7, 525.0,30., 35. ,40.2,45.3,51.2,61.0,63°0,65.0,67.0,70o,0., ¢30° , 3_. ,_0o , 45. ,_2.9,55,.6, _8, _*(PQ, 5,62-6,65, O, _O_5,Q° , 7:.5.,40.,45., 50-,57._,b0o9,65.2,69.1,4_0./ £ATA h2 / i12.,22.7,28.,33.4,39. _,,43.4,z_8.8,56.,80.1,66.1,72.,77.4, 214"2'20.0,24.6,28o O, _2.6,41. Q, _0.0,54.0,59,5,_2.5,71. _, _¢.5, 317" i ' 19- i ,2b.9,39-7,45 : I, 5 I. I, 62.2,66.6,71.0,72.4,2_0. , 420. , 29.6, 34. _', 39.5.4z_J 3,&_.3J55°O,_0.4, GG. O, 7O.O ,72o4, O. , 525.,30.,35.,39.5,44.7,49.3,54.6,59.3,65=0,73.4,2,_0., 735., 40. ,45. , 50. ,55. ,60.,62 . 5,65.4,71.6,3_:0o / £ATA H3 1 113.7, i 7.4,21.8,26.8,31.6,36.9,_-7.5,56.9,b0.1 , 71.6t 77.5,83.6, 214.7, 19.0,22 . O, 26.7,38,.0,41° i, _9.0,_9.0,_. i ,71.0,77° 0,8_. I , 316.5,18.3,27.6,32.4,37.0,42.0,46.5,50.7,60.7,66.6,75.0,80.5, _20. O, 2 7.0,_._, 36.9, _2.1,_t7_.._ _2_9,57.3,62,0,_. 0,70.0,72,9, 525.0,34.0,35.0,_,0.0,&5.5,48.6,51.5,56.4,61.9,67.4,70.0,70.7, (_30°0'35"(v,40oC,45.0,52.4,55.0,5@. 3,¢0._,63o4,6_)°4,09.4,70.4, 735.0,42.5,50.0,.=2.5,59.8,61.4,63.3,6&.9,06°l,67.1,69.&,70.O/ E_1" A H4 / II0., 17. ,21.4,26.,30.5, 35. 1,4_..9,52.2,61°6,70.0,75.8,0., 21_,, 19., _¢,',,2 I,, 3 _. ,4_, 5_, e, _Q, ,5_., 61,6,70° ,75.8, 3!8" ' 21.6, 26.4, 35.4,43.8,52.8,58.1 ,bl.6,70&O, 75.8,2_0., 420. ,27.,3_-.8,37.0,40.9,_,.=,8,90.¢,55.0,¢0.3, 69.4,70. ,71.1, 525., 35.,41.o,45.7,49o6,54.4,59o0,65.4,70.0, 3_0., 6_0.,42.7, _0.,55o,59.4,62.3,65.0,67.4,69o6,70o,2,0., 735°,45.,_6.1,59o4, 58.6,59.5,61°3,64.6,68.0,69.7,70.,70.7/ OATA BLLCH 12.,9,,&-,_l,,_5_,!O,._5.,4D, t45,,50,,55,,60.1.8,.9,_Q 1 ,I. 1, .97, .6_.7,. 34, .0,i .37,1.125,. 86,. 55, 1.86, 1.642,1.38, I. i0,2.3 O, 22. i0,1 o84,1 • 5b,2 °7Z,2,52,2 °28,2 °00, 3,25,2.955,2.66,2.38,3,77,3,_,45 3,3.12,2-78,4.38,4.05,3.62,3o 17,5.00,4. 634,4.25,3_71/ CATA CPML 13.65,4.09,4.b0,6.11,6.64/ LATA CPMJ /0.,.5,1.,2.,2.3/ £ATA ATMN /10''9"'-6,'Q°,,_,i,0,i.5,_.0,2.5,3°0,3.5|4°0 1,43_., 500.,_00.,700.,800. ,900. 'i.000,I-007,1.024,1.060,1.i00,1%146 2 'I.000, i- 008,1 • u_8,1.066, l.l I0, i. 166,1.000, 1.010, 1.032,1.078, 1.130 3,1. 196,1.00G, I.012.1.037,1.090,1. 159,1.244, 1.000,1.014,1.044, I.II0 4,1.209,1°355,1.000,I.016,1.0_2,_,13(_,Io29_, 1.475,1.000,Io019, io060 5,1.168,1.379,1.553,1.000, i.022,1.070,1.208, 1.450,1.601,1.000, I.025 6,1. oeo, I. 253, i. 524,1.634/ tArA AI/Io,7.,4.,0.,.5,1.,2.,3.,4.,5.,.0,I.2,2°4,3.6, i=000,° 0014,.0028,.0042, 2.0002, .0019,.0037,.0054, FIGURE D--6. LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE28OF 26) 3.00Q_tJQQ2?,,/_C&_j_Q060 ....

4.0024,.0048,.0072,.0096, _-OQ49,=Q075,.D_LLOI27L ........

6-0082,.0108,.0135,.0162, 7.011_,.01-3..016B..0193/ CATA A2/2.,7.,4.,O.,.5,1.,2.,3.,4.,5.,.O,I.2,2.4tB.6, 1.0000,.0014,.Q02_,.(L04__4_ ..........................

2.0003,.0020,.0097,.0054, 3.0007,.0027,.00_,.Q0_8, 4.0526,.0050,.0075t.0099, _.Q057,.GQ_,_OIIO..O137_ 6.0u92,.O123,.O153,.O18B, 7.0138,,0166,.019_,_022.21 ......

DAIA A3/3. ,7. ;4.,0. , .5, I., 2. ,3. ,/_ _5., .0, I. 2,2oW,3. _, i.0000, . O0 _ 5, . O0)Q,_Q_9_, ...................

2.0C04,.0020,.00B7,.0054, 4.0030,.0056,.0081,.0106, 5.0062,.0093,.01Z4,,0155, 6.0116,.0140,.0172,.0204, 7.0165,.OI96,.0228,.QZol/ CAIA A4/_.,T.,4.,O.,.5tl.,2.,B.,4.tS.,. .

1.000 U, .00 15, • OOBQ,. 0_5, ..............

2.0504, .0022,.0041,.0060, 3.0008, . 0031 , .0055, . 0079, 4.0034,.00(0,.0088,.0014, _.O074,.OI06,oOI38,.VITO, ......

6.0128,.0163,.0198,.0233, 7.0187,.0222,.0258,.0294/ ............................

COD=CAC/I.2 IERROR=O IF {RORO. E_.O.J GO lO 2010 FC=SQRT(518.69/TOJ GO TU 2090 IF (TO.NE.O.) GO TO 2060 .........

IF { H-3OO00. J 2020,2020, 2040 I0=518.688-. 00356,H GO TO 2060 2_40 TO=B_9.98B 2G60 THE TA2 =516.69/T0 IF (PO.N£.O.} GO TO 2080 CA[L UNINT(II,ALTPR{I),PkESSF(II,H,DELlA2,LIMIT} 2O8O FC=S_RTIIHETA2J HOFO=I.0/{DEETA2_THETA2} IF {VKTSI 2100,2120,2100 SMN=.OOI512_=VKIS_FC GO TO 2140 SMN=TIPSFD_FC/IlI6.

CALL UNINT (]I,AAFT(1),APAFT{IJ_AFT_PAFT,LIMIT) IF (LIMIT.NF.O} GO TO 5 ZJI:5.3Ogx:VKTS/T|PSP5 I£(ZJI.LE.5..AND.ZJI.GE.O._ GO TO Z155 _FITE [6,2150_ZJ!

21bO FO_MAT(IHO,3X,' ADVANCE RATIC: TO0 HIGH =',F8.4} IEPRUR=I GO TO 5000 FIGURE O--6. LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGe& OF 26) P 2155 IF (_,PEWd-M.LE.3_ G(] TC 8 216u I,_(KPERFN.F_.2| GU TU 21/:0 ...............

CP:.?18_l 0._ • SHP_RD_O/{ DROT _2_I [PSPD_*3 J Gl_ T[, 2].99 ..................

2180 C T = 4148. _ IH R US I_.RORO / ( Dy_£1r _,_2,_ I I p_.S20_ ....................

TCT,_L ACT TVITY FACTOR ADJUSTMENT 2199 CALL _: IWLAU (AIAFT,I,ZJI,AFT,TAFTtLIMITJ IF LLIMIT.E_.O) GU TG 8 ....

5 WRITE (6,6} AFT 6 FP.kMAT (IF"O,3X,' TOTAL ACTIVITY FACTOR EXCEEOS THE LIMITS "'/_X, i' TAF=',_ _,,0} IEI-kOR=I .......

GO TU 5000 SHRCU{. LENGHI/DIA_ETER AOJUSTMENT '- CALL LII_bAD (ACL]DtItZJI_CGDtCTCODtLIMIT; I0 CONTINUE _-** _*w,, If'(AF, A.GL..799.ANO.ARA,LE.I,IOI] GO TO 11 6RITE (0,!2) ARA .................

12 FO[_MAT (IHO,3X,' AREA RATIO EXCEEDS LIMITSW/3X,I AR=e,F}.O| I E_ ROt< :i " GC, TO :.000 ii IIAR:I O._ARA+.O01 .....

{.0 20 I=I,', IF {IIAR.NE.IAPIIJ} 60 TO 20 .......

II:I III:l ..........

GO TO 30 20 CONTINUE II=1 IIi:4 ............

3C EO lUO0 I=II,III 60 TO (125,125,150,150,150),KPERFM 125 IF (ZJI.NE.O.) GO TO 130 IJ=l .....

IIJ:l GO TC 175 130 IJ:l IFIIJl .GE.I.) IJ=2 IF(ZJ I .GE .2 • ) I J=3 IF(ZJ I .GE.3. } I d:4 ....

IIJ=IJ+3 CU T[' 175 150 CALL BIQUAD (bLLCI_,I_BLANG,ARA_JLIM_L|MIT| IF (LIMIT.EW.O.) GO TO leO .................

6WITE (6,155) 6LANG 15_ FCkMAT (1HO,'6LADE ANGLE=' ,F4.2,'EXCEEDS LIMITS OF 21-60 DEGREES-(| ..........

IERROR:I ** GO Tr] 5000 160 IJ:I IIJ=4 iF (ZJLIM-L,T.2..ANU.ZJLIM.|.E,3.| IIJ=5 IF {Z.JLIM.GT.3..AND.ZJLIM.LE°4.) IIJ:6 IF (ZJLIM.GT._,..AND,ZJLIM.tE,5.) IIJ=7 175 IX= C;.

C(J _00 J=IJ,IIJ MACF N(_°/ IIPSPEEC ADJUSTMENI

FIGURE D--6. LIST!NG OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM

(PAGE 10 OF 26)

5 •000(_ u 002 7_,,009 _h,. 006 0 _.0024, .00_,8,.0072,. 0096, 5. J 049,. O0 ?.5., ,,OLQI, ,glZ?, 6.0082, .0108,. 0135,. 0162, 7.0118,.0t_3,,. 0168..0193/ CATA A2/2. ,7-, 4.,0.,.51 i. ,2. ,3. ,k.,5.,.O, 1.2,2.4,3.6, 1.0000, .OO l_tJ. QO_2B ,, . 0_0__, .......................

2.0003, .0020, .0037, .0054, 5.0007, '" • QD.. • ,,.. 0 Q_8 ,, ,, C.06 B _ 4.0026, .0050,.0075,.0099t 5.0057,. O CIEg__,_Qll o.. 013 7, 6.0u92, .0123, .0155, .0183, 7., Ol 38,. 0 i(,6,. O 19_t,, 022._ ...........

DATA A3/3- ,7. ,4.,0. ; .5, !., 2o , 3. ,4.,5. , °0, 1.2,2°4,3.6, 1.0000, . O0 }, 5,, 00}q, _ Q_Q_, _ _ .................

2o0604, .0020,.0037,.0054, 3.000_, • OO 3 O,. Q_SO, ,, ODll_, _.0030, .0056,. 0081, • 0106, 5°0062, .0093, .01241.01551 6.0118, . O[ 40,. 0 i72, .0204, 7.01e3, .0196, .0228, ,0261/ CAIA A4/_..,7.,4.,0.,.5,1.,2.,3.,4.,5.,.0,-1.2,?..4,3.6, l.OOOO, • O0 15,. 0Q3_. 0.Q_.5, ..............

2.0GOz,,.0022,.0041,.0060, 3.0008,.0031,.0055,.0079, .......

_..003_., .00_ 0,. 0088, .001 4, 5.OOTk., .0106, .0138, .0170, .........

6.0128, .0163,.0198, .0233, 7.01_7, .0222, ,025@, ,029_/ £OD=CAC/I .2 IERROR=O IF {RORO.EW.O.J GO lO 2010 FC =S(QR T [ 518.69/T0} GO TO 2090 IF (TO.NE.O.} GO TO 2060 .......

IF [H-3_,O0 0.) 2020,2020, 2040 10=51 8.688-. 00356_H GO TO 2060 2[,40 T0=3_9.988 THE TA2 =516.b9/TO IF (PQ.NE.O.} GL] TO 2080 CArL U,'_INT (11 ,ALTPR(I ) ,PPESSF(I |,H,DELTA2,LIMIT| 2O8O FC=S_R T [ 1 HETA 2 } ROFO= 1.0/ ( DELTA2'_THETA2 } IF {VKTSJ 2100,2120,2100 SMh=. 001512x'VK I S=FC GO CO 2140 2120 SMf_= f I PSPDW_FC/1116.

CALL UNINT (II,AAFT(II,APAFT{I},AFT_PAFTtl IMIT) IF (LIMIT.NF.O; GO TO 5 ZJI =5. 309'c:VK TS/I IPSPD IFIZJI.LE.5..AND.ZJI.GE.0. I GO TO 2155 WFITE {6,2150JZJI 21 5O FQI_NAT(IHO,3X,' ADVANCE RATIC TOO HIGH =ItF8.Z,} IEPRUR=I GO TQ 5000 FIGURE D'-6. LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGe& OF 26) !X=IX+I lP l SP D=T I P SPOI FC CALL UNINT (9,ATS(I},APMN|_|,TPTSPDLP._MN, LIMIT} IF(LIMII.NE.OI GO TO 40 CALL B IQUAO (._TM.NsI,ZJJ|JJ. LI2_ISPD,TMN,L3]__I3J____.

GU _F] 50 GO _KITE (Ct45J SMD,,TIPSPD _5 FO_MAT(IHO,3X,'MACH NO. OR TIPSEED LIMITS ARE-EXcEEDED'/4X, I' MACH NO,='IF4.}I' TIPSP__E_D='LFS_,.Q] .............

IERROR:I GO TO 5_00 50 O_. TQI IO0,20L,/3OO'_OO,3OG),KPERFM lOG CPE=CP_PAFT:PMN CALL UNINT (INNIJ,II,CPANGII,J,II,CTA-NG(I,J,II,CPE,CTTIlXI,LIMITI CALL BIQUAD ICCCTIL,[} ....... LIL__TT_IX_X.J__A___T, LIMITI CTT ( I X |:(CTT( I X) *CTCOD-ACDCTJ/(TAFT*TMN) CT=CTT ( IX } CALL UNINT (I_._-|J,IItCPAO{I,Jt IItBLDANG(ItJ,IItCPEtBLL(IXIgLIMITi GO TU 500 200 CTE=CT mTAETmTMN-CTCOD CA LL B [ QU AO I C _CI | ILl } , .ijZ 41, C_IELACD_C.T_tLII_.LI_L_ CTE=CT E+ACOCT £ALL UNINT IIN_.L,[_U_C.IAJ_LGt]_Q.t_-Cp_ENG|I,J,II,CTE,CPPIIXIwLIMITI .

CAll UNINT (INAIJ,II,CPAG(I,J, II,BLDANGII,J,II,CPPIIX)_BLL(IX|I ILIMIT] CPPI IX }=CPP( I X )/{ PAFTm PMNI ...................

CP=CPP ( IX!

GO TO 500 300 CALL UNINT (INA[J_.IJ,BLDANGil_(1,J,II,BLANG,CPP|IXI,LIMIT i) IF {LIMIT,NE,OJ.GO TO 4C)C) CALL UNINT (INN( J, I J C*ANGC t, J,i-J ,Ct- NG(i ,CTTt IX}, ILIMITI GO TO 500 400 _ITE (b, ._50l ..

=*50 FO&MAT (ihO,3X,' CP, CT, OR J ARE OFF CURVES'} IERRQR=I GO TO 5000 500 CONTINUE IFIKPERFM.GE.3) GO TO 700 IfIZJ,N_.,llJJ G _. I_L .__5_.(i__ BLANG: BLL If| CTTT( I }=CT CPPPII I=CP ELLL( I|:BLANG GO TO I000 550 CALL UNINT (_,ZJJ(IQ),BLL{I I,._Z_ I__BJ.LL[_!_ [, L IM I T I _IANG:BLLLII IF(KPERFM.EQ.2| GIJ TO 600 CALL UNINT (4,ZJJ|IJ)_CTT(I I , ZJ I _CTTT ( [ I,L IMIT | CT=CTTT( I ) GO TO I000 OO.O CALL UNINT (4,ZJJ(IJ_,CP_P.I1 } ,ZJ L_G PP-P--LU..__I__I.I 1.___ CP=CPPPII l C,O TO lOuO 700 IFIIJ.EQ. IIJ! GC TO 750 FIGURE D--6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE 11 OF 26) CAll IJNINT |4el J J( I J| .£TT 11| :/JI :£T;L IMIT] CALL UNINT(4tZJJ( I J) ,CPP( I I,ZJI,CP_L IMIT) 75(_ ('-ALl BIQtlADI&T.__FT.I *IJI.AFT;TAFT.LIMIT) CALL B IQUAD( ATMN)I, ZJI tTPT $PD, TMN,L IM[T | .rP=K PJ (PA FT_rPMN 1 CALL B IQUAD(CDCT |1, I ) t 1, ZJI )CT,ACDCT,LIHIT | £T= I C T +£.T CO I')-A C DE T ) I f TAF I).TMN | ASHP( I )=CP*DROT**2*TIPSPD**3/(RORO*o718*IO,E6| ..... ..AI.I:LIL.%T_LLL= C T * n R fiT * * 2 • TIP _P 13..2 / l _ 148 =.RC)RO | SHP=ASHP( II THRII_ T =ATHR_T( I} 1000 CONTINUE ....... _.GO_ _I[i _XI]_ Q.__L2..CtO._ L2LEQ__. JJ3_O 0,13 g._J_ _ ......

1100 IFIIII.EQ.!IIGO TO 1150 ......... -CALL UFLI_I_._(4, XAR( i ).-_-JJ-=AJ_A__IMI.IJ.

CALL UNINT (4,XARII])CTTT(1)tARA,CT,LIMITI 1150 THRUST=rT*DRC}T**Z*TIPSPD**2/I6148.,HfIROl GO TO 1275 ._. 3.200 IELI I L.E_=II.LC_..T_O_J.25_Q ..........

CALL UNINT (4,XAR(1),BLLL(II,AR-A)SLAN-G-)LIMIT) CALL U__lrtI-J_u_CP-P.__._I1 12 50 SHP=CP*DROT**2,)TIPSPD**31[,?IS,10oE6,RORO) _ 1 _ 76 _c,,PJE=_ P *P A F T * PM N ._ CALL UNINT(5,CPHJIII,CPHL(II,ARA,CPELMtLIMITI --- . LF.I.C._P ELt_GE =CP.ELGO XD___ C}o .....

WRITE (6. 1151 CPE,CPELM ... LI_. £-QI_AT_IIJzt_ ,.;C_PE__2_.ES_3.3x ),_t_Eg._ THE _£PE LIFII7__=' )Fi._l IERROR=I _ .£.,Q_.I_D___O_Q.Q 1300 IF (III.E(Q.IIIGO TO =)500 ..................

.... _.CALL Uht/_.I. (4.tZAI_Z}__u_$J:IF.(J._iSLIF.tLi_IJ.L} CALL UNINT (4,XARIIItATHRST(1)tARA, THRUST,LIMIT) __ _500 IF(ZJL.EQ.O.J__G_ TO _700 EFFP=CT/CP*ZJ I -.f_ _5_Q0.9___ 6700 EFFP=O.

...... 50_0.0_ IF _.I_I_E,_E=_0 } -HRIEEJI_t_9__OO } Dr OI.t_TLPSP.D_$J-I.P_.j _ra_R.t,!_. t _ _LA_.N_G., Z.,tj ,_V.a ....

ICT,SMN)EFFP 9000 FORM AI ( LH.Q_3X- I ' O |A -= ' LF _, LJL__X._ ' T ! p SPEE D=) _ F4.O) 3Xt _ _.Hp;:'" ,_- -, 0 ))X _ I'THRUST=' )FS.0/3X) =BLADE ANGLE=),F_.I)3X)'J=',,F#,..,3) "_':)_Cp=i,F_.'_) 23X ) ..£.I__L=_F_5.3,3 X, ' '=' *, • = EF FP= ' • F _._.3J.__ ......... _ .......

PETURN -- END._ FIGURE D--_.

LISTING OF ADVANCED GENERAL AVIATION Q-'FAN PROGRAM (PAGE 12 OF 26) ____.%LLIIBOUT I_L_Q,_JIO_I_,S__.IA_L, T IPSPD ,THRUST, DROT • ZNQF I , ZNQF2 , i hOE, I ERROR, KWRI TE) __ DI_I_ON ZNI lI.5.5_J_.LZ_N.N.___I55|,ZN411551,ZNS{155|,ZN|I55_5|t I TAFL ( 5 I,ZNT( 5 J, RDL (7|,DPNL(T) _ EQUIVALENCE (ZN (1 ,I ), ZNI I , ( .ZN(I,2 I,ZN2 I, (ZN(I,3|, ZN3I, (ZN( Ir 4) r ......

IZN4), (ZN[I,5},ZN5)

..... £A TA__ TAEi _/_ _7 5_gju._._O_O_L ti50 _0, ,.__Q 00,_, 3_ QQQ LZ____

DATA RDL /2.,3o,40,50,6,,7,/ .....DATA DPNL /-6,_61-_4J_Ot-1___7_tOt, 1__t_2.t20]/ DATA ZNI / I, ,16.,8.,100,150,20,,30.,400,50.,60, t700,800,_00,I00,, .... i_.1 _Z_i,__ _L_O._QL,_29_O_,_,j__2 50_L,_}_30 0,_, 4}0.0,_,_5 00_.,5.5 p._L6 00_,j 6_ O.,7qO.__LL7__5.0 •,800., .

2 68, O, 68o 7,6906,700 7,72,.9,73.5,750 1,77o0, .. _} ?,,_0 0_, "r2,.I, 72_._..o_ 23..p, 7__, ;_, .'5.} ; T_a:_9,T8, _, ..................

48100,77o5,76o5,76o4,77,0,7707,78o 7,8000t 94.07, 8 g. 9,8_. O_,_S 3._0 • 82.0.82; 0,_8.2._2_,Bz. o, ' 6108-5,9900tq3*_,g003,88*lt8609_8600,8505, • Lz_Z},..o. ,..1_1 o.: o; 1o2.5, 9 e;o_ 9L_4,_4_, 9.Z._O_L6 8.9. _ :.8_8. L, ..................

8138o0, 124o0,112.3,105.3,I00o0,961_,93.7,92o0, 9_153.5,.It,0;.3,.122:.]:.112.5,105; &_,.I.000 8;970 5,95.5 i 171. O, 154, 5, i 3205,120. O, ii I. O, I05, 3, i01,5,9_.z; ' .......

2 !89;.5__= 170, Q_ ! 4______5.,_12 8_,.5 ! I_.1 7_... O_t_110__.Sj_I05, 8, ! p3_, 0___ .................

3 205. O, 187, 0,I 54, O, 136. O, 12 30 5, 11 5, 3,109, 8, I06.5, _2.5 8_._Q_ 2 z__88, .o_, _13_z ,_o_, I_ 6.6,..Q,_ I___. Lq,12___ ,_s,_.12_ .2 ;.o_,.! k%_, ............

5 31 7. O, 275.0,233. O, 1980 O, 1720 0,150o O, 138, O, 1 28, 0, O _, O, 382, .0,324, O, 27_, O, 235, 0_, 2 02.O, 174, O, !5.B.:_0., .........

7_00.0,505.0,422,0,3510 0,306.0,25900,226o0,196.0, 8 000o 0,660,0,5W6: 0_, 46q_ 0, B8 _. 0, B26__q_2800 0.92W0.. 0__ D_TA ZN2 /2.,16,,80,100,150,200,300,40o,500,600,70o,80,,900,I060, .....

. .1.l __5_ _..15-0 =..t 2 q0._Llt .25___0.tjL___ 00__U_4_.5_ 0___L_500__J_55._0__. t_6_0, g _.j 6_j_0 j 70_0..U? " 50, j_ @.P01L__.......

2 650 8,66, 5 ,6803, 71,_4,7308,7502,760 7,780 0, 69o3,69.2,70,3_7205,7_.7_76.1_77o6,79,0, &7401,72o8,72.3, 740B,7508,?7. StTB. 8,B000, 584.&,7908_70£1. t7806_790B,80.0_81.0,82,0, 692. °.', 38. O , 84.9,83.7,8300,82.5,82.9,84. O, T 1Q O- I, 9 _.: 0,91_.. _l_j "9; 1,8.6._ _3, B5.._0 L__'*.,_ 7, 86. Oj .............

8 10e. i , 1020 6,970 5,9304,90. I ,880 0,870018708, 9 116.0_i_0,0,i0_,4_99,0t94o_,90:9 r 89._4_89.9, I 124o0,117o8,111, 8,105.5,100.0,95. 8,93o0,92o_.., 2 13B- 3,1260 0, ll_,0, 11 [09,106.3, I010 I,q7o 2,94.6, 3 ]&O.O,132,8,126,2,1190&,_13.0,107,2,101,9,97,0, 4 _69.0,158.0,148,0/138. 5,129.0,119,8,111,O,103, 3, 6 295.0,260,0,228, O, 2060 O, 186. O, 167, O, I&9o O, _ 33.8, 7 440.0,38000,325, 8, 2750 O, 2380 0,210, 5,187o 0,165, 0, 86_0.0,5250 0,430,0;355, O, 2980Q, 26_00,2_2,0,2060 0/ DATA ZN) / 3. ,16,,8. ,£0, ,15o ,20,,_0.,40. ,50. ,600,700,800,90.,I00, ," i..!2 5., 15Q., 2QQ,.:2)0°, 9Qo_t:.950,_, 500,, 5500,6000,65Q°, .7009 ,7500,800., 2 6500, 6703,600 _, 710 _t 73.5,75°4,77o _ t#9°O, ...........

680 Ot 69° 3,71o 1 , 730 0,75, 0,76° 8,78° 5,80, 3,, 47007, 71o5,72'#,7404,76o2,781i,7908,81o5, 576o09 75o0,75°6,76°8,78o5,80.0,8_,7,8._. I, 6 80.5, 780 O, 78°6, 79. 3,80° 5,81.7,83° 2,84.9, "- 7 85° O, 82o 5,81 o4,8 I° 9,82°5,83° 5,84_ 5 ,86, O, "_ B-9; 9, 8 6. _;, 8%. 5, 84.3; 8%_ _; B S_, _, B4j o, 8,%_, 99_° 5, 910 I t 890 I _ 87* 3,86°8,86.8,87o _,Bd, 5_ I _90 5, 95o 7,920 8, _O, 8,89, _ , 89° 0,89, 0,8)°5, FIGURE D"-6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM

(PAGE 13 OF 26)

24?

2 I05. C , !00,6,97e 0,94.9,93, 0,91,8,91, 0,9_,0, _ iI0, O, I05, 7, I02,, 0,98,5 ,g_, 2_94, 2,92,9,9212, 130,0,121,0,111,4,108, 8_108,0,99,4,96,8,95,5, 5156,, !40. S,130.0,118,9,110.5,104,8,101.0,99.0, 6_2C., 188, 5,166.0,141,0t129.5, I19, 5,114.0,109,51, 7 29_, O, 245,. O, 207,0,178, O, 156, O, 140,0,131,5,1 28,0, 8.38C',0,306,0,251,0,2!_',0,186,0,166,0,154,0,150,0/ DATA ZN4 /4,,16,,8,,I0,,15.,20,,30,,400,50, ,60.,70,,80,,90,,I00,, 1125,, 150,,200,,250,,300,,4C_0,,500,,550,,600,,650,,700,,750,,_0C,, 2 66.9,68,6,70.4,71.9,73.8,75.8,77, 6,79.5, 368,3,70,3,72,2,73.,_8_75;?,77,5,79, 2t.8.Q;8_, .

4 69, 8,71,6,73.4,75, l , 77, O, 78, 7,80, 5,82, O, 5 72,, 3,73, 9,75.5 , 77,2,79, 2,80, 7, 82, 2,83, 5, 674,8,75,8,77,3,79,0,81,0,82,5,83,8,85,0, 7 78, O, 77, g, 78, 8,80, 3,82,2,83, 5,84, 8, 86, 2, 881,_,_0,0,80,3,8"1,5,83,3,84,6,86,0,87,2, 9 84, 6 t 82, 5,82: 0,83, 3.,84, 6 t 8_5- 9_L87,. _.0,8.8, 1, I 87.8, 84.6,83.9,84.7,85.8,86. 8,884 0,89.0, 290.8,86. g,85.9,86.2,87.0,87.7,88.8,90.0, 3 93. 6, 89. I , 87. 8,88. I ,88.4,89.3,90. 1,90.9, 4104.0, 96. 2,92. 5,91.8,91. 5,91. 3,91. 7,92.9, 5116. 5 , 102. 7 ,96.8,95. 5,94.4,93. 7,93. 9,94. 8.

6151.3, 124. 0,109.8,104.5,100:5,9799,97.9t98.0, 7196. O, 153. 5 , 12 Q. 5, 116. 4, 108.0, 103.4,100.9,100.6, 824b. O, 191. 5,158.5,136. 5,123.5t 113.8_ i07.4, I03.0/ DATA ZN5 /5.,16.,8.,i0.,15..20.,30. :40.,50. ,60.,70.,80.,90.,100. , i 125. , 150_ , 200. ,250. , 300. , 450. , 500., 550. , 600., 650., 700. , 750. ,B 00. , 2 69.9, 7 I. 5,7_-.0,74. 4,75.8,77. O, 77.8,78.5, 6,80. O, 3 71.1,72.9,74.5,76._2,77.7,78.6, 79.

472.0,73.8,75.5,77.1,78.6,79.9,80. 9,81. 5, 573. 7, 75.7,77.5,79.2,80.7,82.0,83. 0,83.5, 675.1, 77.0.78.9,8_(,6,82.0,83.&,84. 5,85.0, 776.4,78.1 ,79.9,81.5,83.0,84.3,85. 5,86.5, 6,87.5, 877._I,79.2.80.9,82.3,8&.0,85.5, 86.

978.8_ 80.2,81.6 _ 83.2 v 8&,9186.3_2 87, 5188.5, 179.8,81.0.82.4,83.8,85.5,86.8,88. 3,89.6, 281.0,81.9,83.1,84.5,86.0,87e5,89. 0,90.6, 382.0, 82.8,84.0,85.2,86.9,88.5,90.

0,91.6, 4 84.7, 8 4o 8,85.5 , 86.7,88.0,89. _, 91.

0,92.6, 5 88.3, 8 6.8 , 86.8 , _8. O, 89.3,90.6, 92. 1,93.6, 6 98.5,93.9,92.1 , 91.5,91,5,92.2,93. 5,95.0, 7115.0, I07_ 8 , I02. O, 97.. 9 , 95.3.94.7, 95.3,90.8, 139.5, !27.&,]16.5,107. 1,101.0,98.0,97.3,98.31 IF (TIPSPD, GE,4OO,,OR. TIPSPD, LE,800,1 GO T0 I00 _RI'[E {6,50l TIPSPD 50 FOFMAT [IHO,' TIPSPEED:',F6,0,' EXCEEDS LIMITS FOR NOISE CALCUL I AT/ON' i IERROR=I GO TO i000 "[AF=AF x_Bt

IOO

TO[' 2 = T HRU ST / I DR P.TW,,k 2 ) IF(TOD2, GE, IO,,CR,TOD2,LF,300, i GO TO 200 _RITE [6, 1503 TODP 150 EXCEEDS LIMIT FOR FORMAT lll_O,' THRUST/DIAMETER SQUARED=' , F5, 0, ' NOISE CALCULATION' | IFRRUR=I FIGURE D--e.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM

(PAGE 14 OF 26)

GO TO tO00 200 CO __00 I=1,5 CALL BIQUAD (ZN(I,I),I ,TOD2,TIPSPD,ZNT{II,LIMII) 300 CONTINUE CALL UNINT (5,TAFL(I|_ZNTII),TAF,_NQFI ,LIMIT) CALl_ UNINT (6,RDL(IJ tDPNL(II_DROT,DZNQF,LIMIT) IF (LIMIT°EQ°O! GO TO 400 WRITE (0,350l DRCT FT, IS EXCEEDEDJDIAMETER= t, 350 FORMAT(IHO_ 'THE DIAMETER RANGE OF 2-_ I F3,0I IERROR=I

Go TO 1000 "

400 XNOE=NOE ZNQF i = ZNQF1-4° 5 ZNQF I =ZNQF I+DZNQF_I 0,* ALOGI 0 (XNOE) ZNQF2=ZNQFI-12, ....... _I.F_ (.K_W_R..I.T..E ,,N.E, _0L_HRJ T E.(. 6__t 4501 _Z N. QF.I, Z N_QF 2 ..

450 FORMAT(IHO,' QFAN NOISE AT °IM.N AT 500 FEET = ',F6-,I_, -_ PNDB AND = I 'gFb;.].t' DB_(A)'I. ........

1000 RETURN END FIGURE D-'6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE 15 OF 26) ,° Su_RCUTINE BTCFN (6L,D, AFISHPtI,CAIN,ZFLAGtGDQXMtWQFT,IDATE,CODt IIFP,K_RITE) LIMENSION ZKM (6} ,LKIib)_LK2io}_ZL3(_)tZK416ItZLSIO),ZK_(6I_ZP(61y ILKIb),ZS(e) ,ZT(6 },Z_3(Oi_L_5(6) ..........................................................................

bIMENS !(3N ZL5 (_.)

DATA Zt 5/_.,,2,_,8,4,f_,4.11 LATA ZKM/I.?_.,I.?,,,I_74,I.3,1.74,i.B/ LAIA ZKI/2A. 5,20.), 2c,.5,2(_.5,26.5,2o,b/ LATA Z_,2/. O_, .07,. 07,.07,. 06,, 061 oAIA Z Z2/_, 25,B. 3_, _oB_,, 9. _,b. 7,7.74/ L, ATA ZK411.13,&oO,4. b_,_.6t4._,4.6/ bAIA ZZ_/Z-.45,5.14,5,1_,4.35t4°45,3.7_/ DATA ZKC/,0,2.3_,2.3_,2.33,.C},.0/ DATA ZPI° Q,. @ ,._. d_,ml, 8/ DATA ZR/2_,2°e,2,O,2.I,2.b,2. I/ EAIA ZS/.2, . 2 ,°;' ,. 2 ,.;/, . 2/ DAIA ZT/. 2 ,.2 ,.- _°2t.2, .2/ CGMMC'_ / CPCB / WKOT,wSPIN,W_I,JCT,wTMT,I_TFLG,WAFTB IEI_RC_R=C N=t. ATr ' *.01 IF {N.EQ°I)GC TU lb if (_.GT.3)GO TO b N=ri-I Gb T[] 7 ) IE (K.EQ.Z..ANC. IUATE.F_.I970]N=3 IF ( N. FQ, 5. AND. IDAT E,,E_, 19 8O_N=_ IF(N.CT.Z_.AKD.TI-P°FQ, II Gb TC 15 IF (r,:.GT.6) GC TO 15 ? IF(IFP.FQ,II GO TO 14 bE, T_ (20,20,20, LU,20_J. OI_N iO z,I_(N)=ZZ3(N)'_(D/_._,_,_.25 _K_ I N ) =ZZ5 (1',)/( I .2'_13.t'_'_. L5 ) u6 T r 30 3._ 4.1',3 ( N ) =C), Z.I',,5 (N|=ZLS(N) [F(N.E_.4I ZK5(N|=ZLS(N)t[ (,2_D)_,_°251 C,L, TO 30 Ib _klTE(&_17) C_TN 17 Fi,.,KMAT IIHO,3X,'ILLEbAL AIKPLANE CATEGbKYt CATN =_ ,F3°O) I _kROP=I C_I., TE 300 2.0 L_.3(N)=ZZB(k) LKS(N)=ZZ'_(NI .,t_a FLAG=ZFL AC;+,0I oU IFIFLAG.FQ.1) GO TO O2 LIk7=4. _ (_2 Lt_7=C.

b5 LY=I.+.OS/(BL/IO.,_(AF/I?U. 1"_,5)*T1500.

IF (/_F.LT.170.) GU TO 70 I F ( N.GE.7 I X_= !. 0 Z_=O.

iF (N.LT.?IGO TO o7 ZIJ=I .7 (.;L, T C 80 _7 ZlJ=l,q FIGU RE D---6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PRO(_.RAM (PAGE 16 OF 26) _-50 o_ r 80 (.j tr{:, .LT.7)i,C T( 75 tO-( _'.z-'_(t( /1C0. -Z .U3 ) ) _"_. b o,. zt.,.:105_(LIJ-ZV) LL,_= ( IL-3,_' ZV)I, ; .

_.,. ,., = ( ZUi_._-ZVI/L.

LL.>=Zt_-ZV _=I_l I 10.

_=l. lb.

_=_FII?O.

t =I l_CC, ZZ=( 1,4.071/(/_C*_' .b)_E )_*1.5 ,t'L":.C,E.7) ,TZ=I.U XI=L_ _.' (L)'_/_x'*ZP ( hi IN)*&SF'.PI(ZO._O) )_"¢'ZLb*E_:*9 i.F( IFP.FC.! ) _C Tu 9b ,,,_= Z_ ! (1'.)_ZY_(I.+/ ^3_-? K ? ( t'_ ) '_ E',_* ZV_ E/ _ ZL,5*bL / E*_Z oL. T(" IOC c,,,; X3= ), Az,= ,), AC= Z'.

A,-=25.Z_Z_/Ce'_ZL. 2 O'J A?= ZK 7"( SPP 15(].h. )_'_2 ^_=. c ]*{)_'{" 2 ,_F, uT=XI'_'(X2+X3+_,_+XS)ex(_ ,,5PI h=X_ _uuC 1 = (9. _'x'CCCeZ.8 )*D*D v, TMT=0.

v,,Ar TB=C.

,-,ThLG= C.

IF {CPCXM. NE.O,) GD TO ibU ,,IM T =._,,c* (SFP'_D/T) _** 8_ IF (IFL_G.FC.I._ C_b T0 2Uu }_,L) ,,,IF LG =X?

Zv_ _C,FF=W._CT+v, SPI_ev, L)uCI+nTMTe_TFLG+_,AETD IE(KwRIIE.NE,C) h_ I TE (o, 25 O |CA1N, I L)ATE _ SHP _, T, v_OT,_SPIN, WTF L.G, i,,,UuC T , WIF'T , _A FT_, nwFT /50 FL_Y, ATIIHO,?X_'_FAN nEIGhT'//)X_'AIRPLANE CATEGORY :_,F3.O,)X,' _;AI _L =' , i 5_.X,' SHP=e _F_.O_.i)£_' TIPSPEE_J =' _F,,.O/_X,'R(JTL]R ASSEM_SLY', ;r_,I,,PLUDI)S,/_A_m_pINNEk'_ZX,F_.I,,PbbNOS_/3X_'FI ,_L,E_ _ UX,F_.I, _' PuU.":[ S'13X, ' FUCI' ,IOX,F6. I _m PLiUNDb m/)X i _M(,]UNT =* _SX,FS. i_ _Pl]uNr]_' / -_3X_ ' AFIFPEnEY_,SX, Fb. i_ _ PC'UNDS _ /3X,'U_FAN _E I_HT' _3X,hS, L, _PL)UNL)S' ) _uo KL. TU_N LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM FIGU RE 0"-6.

(PAGE 17 OF' 26) 25_.

C'll_q.,?_lT [_F (._FCOST|ChTN, ICA'TE,CQFI', IFPRORIKODE ,C LFI,CLF,CCUANT,._L I,£C INq, IFr.,KV_RITE) ,'I"ENSI_N XF× ( 2,5} ,XEX(2,_) ,XCUA_(2,5) ,'I ,_'_S I Cb XF_L {2,4) r-r)h.'_lkl / CF:F._rl I VwRCIi_SrIN,WtTLCTt_TIvT,_TFLC,WAFTP.

PAT A X_l /0°,0., _.4, 2°4,2.6t 2._,2.6,4.q/ XF× l].,O.,t.6 ,L.5,3.51_.5,_o5,3._,3.5,3.5/ XFX /9.,0., 2. I ,2. 1,2. I, 2. I, _. I, 3. 2,2.@,3.6/ r _TA X)iJAK /D. ,O.,2DIO.,5_FO.,IO30.,IqcC.,295._680.,_5. I_68./ .'JC._:STI,CCCST?II_.S(,3_,,5CI _=(ATN+oO I I _rq=Kr_E-_ -t 9 IF-_F ROR= C • : .r- (N • 6T ,i °ANI:. _ .LT. (.) CC TC I0 !_VP _R= 1 k.R :TF (6, 5)ChTN F., rq_'_4AT (tH.)t-_k,' ILL_CAL ._!_PL_[- CAIECCpy, CATN=', F-3°O) C:I T-I 1 C6C ] ) IF( ILAT E,E'].]._7_ } I=i T=( TT_aTF..EG. 19801 I =2 C) Tr} ( 2..3i40, 59, eC, 2C,4C), TK()I) 2" (Cl Pt:3.2ITB ¢CL _:L..?2 ?;.. (')tlAN-=XCLI._KJ{ I,_l "_: IF {IFa,,7-Q,I) GC T r" "_7 I ".r'qT=XgX(I,_aI*( 7.*'PL _x,. E+),F X( TIN)} r,r} TC 7C "_ lJ,CnST=XFL( I,NiX,(?.*.-PL_._.+),FX(I,I_) ) F'q Tq 7,) aC (CI F-L=C I.F 1 CCI F:P. L F C',O TC 3D _C C r_U _N= COUA'_I T rCE F[=3 .21Tq rClg=t. C2 :_ Tq 35 0 rQUAN=CCU _NT FCI. F I=CLF 1 CCL. F=CI F ?C I F ( KCr)._,O T.]. q } UCCST=SC IKC Yt.q-- { & [. I-1G (CCLF)-AL_G(CC'tFI|) I_,gC775527 xZb=[XPlA I_f]C;(CCU/_k),_XLI_÷_LC.C(CCL F] }}/CrLFI P,] C _(' T:XZ I',,_ LCI2S T'_WPCT cqkST=X IN X'lJCr]S T I rgoI K:C r_, ST_,SPI _ CqUC T: C r_N g T_V,D CC T ( T,UT= X Z N_WT MI-,_UC CST 2 ( .'_ c TF_=C.t'NS T_ V,AF T F_ CFt G:XZ,'I-*. XFX( I ,N ) _'UCO.S'Te.WTFL G COFT=CRCT+CSPIK+CCIJCT÷C.T_T _CI_FTP_CFI C TF IK_._ITE._IE.O) WPITEIe,ICO)CCLFI,CCL_,UCf'ST,CO.U/tk,CRCT,CSPTN, I fFl. C, CPbPI, CTMT, C,%FTql COFT IgS F'JP'IAT (IHO,3X,'CFAh CISST 'I/RX,'CCLFI=',F6.4,3X,'CCLF=',F_._,3X, ['ucq_:T = ',F5.2, 3X,'COUAIN ='IFS. C 213X,'RI;T(_R ASSF_VP-LY',3XirS.0, ' CCLL #RS'I3X,'SPINNF_', ?X,F_.O,' liCit _I _PS'/3X,'FLANGr,,12X,_4.C,, F)CLIAQS,/3Xi,I)UCT, ,IOXIFS.C,' DOllARS _,'/3X, '_CIINT',qX_F@. (,' D.rLLAR..'/_),,'AFTFRBCDY _ ,4XiFq.O,'. I]9,LI ARg'/ r,l_X,'Qr-h,_ CCI£T ',_X,FR.O, ' 12ft.[ _l_e,,,) ltiOC ;-E IbnN PND

FIGURE D--6. LISTING OF ADVANC_p GENERAL. AVIATION Q-FAN PROGRAM

(PAGE 18 OF 26) 2a_ SUBROUTINE- BILINE (T, I, XI, YI, Z, K) ENTRY blLIN (T, I, Xl, YIt Z, K) CBILINE C DIMENSION T{I),XC(4), O(4)., P(Sl," Y(4),C(4) DIMENSION T(I{,XC(4}, D(4), P(5), Y(4),C(4) EQUIVALENCE (XC(1), D(1)}, I (C(I{_ CI), (C(2}, C2), (C(._), C31, (C(4), C4), 2 (E(1), D_.), (D(2), D2|, (D(3), D3), (D(_), D4), 3 (P(l}, P}), (P(2), P?), (P(3), P3), (p(t.), P4), (P(5), PSi C C TA-BLF SET UP C T(I ) : TAELE [XUMBEn C T(I+I) : CEGREE CHOICE (0,1,3} C P, EGRE_ CHOICE P.'PTIOKS -_0- USE FIRST VALUE OF TABLE FOR ANSWER C -I- LINEAR INTERPOLATION C -2- THIRD ORDER INTERPOLATION C T(I+2) = NUMBER OF (X) VALUES C T(I+3) = NUMBER OF (Y) VALUES (0. FOR UNIVARIATE TABLE) C T(I+_) = VALUES n.F (X) IN ASCENDING ORDER TN = T(I÷])-2oO IF(T(I+I}) 20,20, .:0 20 K:O Z=T(I+2) G() TO 999 ° 30 NX = T(I÷2) NY = T(I*3) J1- = I+4 J2 : Jl ÷ NX - I

IDX = I +i

X : Xl SEARCH IN X SENSE L = 0 GO TO I000 C RETURN HERE FROM SEARCH [)F X K : KX IF (TNI 1! 03tlO4t104 104 JX= JXI FIGU RE D--6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM

(PAGE 19 oF 26)

C THE FOLLOWING cEr_F PUTS X AND/OR Y VALUES IN XC BLOCK I05 Dn 110 J:I,4 XC(J) = T{JXI) Ii0 JXI = JXI+I C GET COFFF. IN X SENSE GO TO 2000 C RETURt. HERE WITF_ COEFF. TEST FOR UNIVARE OR _IVARIATE 2OO I_ (NY) 300,210,300 210 JY = JX ÷NX IF (TN} 212,211,2!I Z = C] '_(T(JY÷I}-T(JY)) +T(JYI CLI T C] 9999 Z = 0.0 Dr" 220 J=l, _ Z= Z ÷ C(J)_T(JY) 220 jy = Jy+).

GO TO 9999 C C BIVARIATF TABLE 300 L=I X = Y/ J/ = J2+l J2 = J I+NY- I C JXl = SUBSCRIPT oF IST Y SEAPCH IN Y SENSE CO TO I000 580 F = K+3'_KX C INTERPOLATE IN X SENSE C SUBSCRIPT- BASE IkOo OF COL. NO. OF YS IF (TN) 501, 519, _19 501 !Y = JXI +NY *(JX -IDX -2) JX = JY ÷ NY Z = T{JY) +CI "_(T(JX|-T(JY|I Z = (X- T(JXI))/ (T(JX!+I }-T(JXI))_ (T(JY+I)+CI_(TIJX+I)-T(JY+I)| -Z} +Z CO TO 99o9 5!9 JY : J2+! +(JX -[DX -3J_NY.+JX1 -J1 DO 550 M=I,4 JX = JY Y(M) : 0.0 DO 520 d=l,4 Y(M) = Y(M) + C(J)*T(JX) 520 JX = JX+NY 5_.0 JY = JY+!

C C GFT CL}EFF. IN Y SENSF CO TO 105 600 I = 0.0 F)O 700 d=l,4 7O0 Z = I + C(J)X'Y(J) 9999 RETURN C C SEARCH RCUTIt,:E - INPUT JI,J2,X C -OUT PUT RA,RB,KX, JXl FIGURE D--6. LISTING OF ADVANCED GENERAL AVIATION Q_-FAN I=ROGRAM (PAGE 20 OF" 26) " :.' '_ .... " ""_'__,._-a-)_,), ," " ,:,_,, ,. ,=',C_'-'; " ,' " _ -:,' ........ " ..........

I000 KX = 0 00. i010 J_Ji,J2 IF (T(J|- X) I01C, I050,I050 CONTINUE I010 ?FF HIG_ END C J = J2 X = T(J2) KX = 2 IF (TN) II01,1020,I020 USE LAST 4 PCINTS AND CURVE 1020 JX! = J2-3 RA = 0,0 GO TO 160C FIRST INTERVAl, OTHER TEST FOR - - FFF LOW END, i090 , 1100 1050 IF(J-JL-I) i080 , 1100 IF [TN} I101,1102t_,I02 1101 JXl = J-i G_ TO 16.01 1080 IF(T(J)-X) I082, i O_O, I082 1082 KX : i X : T(JI) lOqO JXl = Jl IF (TN) I_"01,1091,109 _.

1091 oA = 1.0 GO TO 160 0 C TEST FOR LAST INTERVAl. NO, YES, NO 1107 IF (J -J2) !5C0, I02(_,_-500 1500 JXl = J-2 RA = (T(.J) -X )/(T(J) - T(J-II ) 1600 _5 = 1.0- RA C C RETURN BACK TC _AIN BODY leOl IF (L) 500, IC0, 500 C C COEFFICINT ROUTINE - INPUT X, Xl, X2, X3, X4, R/_, RB 1103 JX = JX1 2000 IF [TN) 20CI,2002,2002 2001 CI = (X -T(JXl)) /{T{JXI+I)-T{JXIJ) GO TO 2021 2002 DO 2010 J= 1,3 2010 P(J) = XC{J+I)-XCt J) P4 = PI+P2 P._ = P2*P3 120 202C_ J=1,& 2020 D(J* " X-XC(J| CI = RA/PIW'D2/P_W'D3 C2 =-RA/PI'_D!/P2*D3 ÷ RB/P2*D3/PSW_D4 C3 = RA/P2'WDI/P4*D2 - RB/P2X_D2/P_'I'D& C& = RBIPS'I'D21P3'_D3 C RETURN TO MAII_ _OOY 2021 IF {L) 600,200,600 END

FIGURE 0-'6. LISTING OF ADVANCED GENERAL. AVIATION Q--FAN PROGRAM

(PAGE 21 OF 26)

9.55

SU[IROUTIKE BIOUAD (T, It Xl, YI, Z_ K) ENTPY i_IQU_ (T, I, XI, YI, Z, K) TPIS RUUTINE IkTEF. POLATES OVER A 4 POINT INTERVAL USING A VARIAT!C)N CF 2ND DEGREE INTERPOLATION TO PRODUCE A CONTINU_ITY OF SLOPE BETI_EEN ADJACENT INTERVALS.

[IMENSIOI_ T(I},XC(4), O(_), P(5), Y(4),C(_,I F_QUIVALENCE (XC(!), D(1)) C £ TABLE SET UP C T(I ) = TABLE NUMBER C T(I+I) = NUMBER OF (X) VALUES C T(I÷2} - I_UMBFR OF (Y) VALUFS (0. FOR UNIVARIATE TABLE) C I(!÷3} = _AtUES OF (X) IN ASCENDING ORDER NX = T(I_I NY = T(I+2) J! = I+?

J2 = J1 + _X - I X = Xl SEARCH IN X $EN$_ L = 0 GU TO i000 C I_FTURN HERE FRCM _EARCH r2F X !00 K = KX JX= JX _.

C THE FOLLOWING CCP[ PUTS X AND/DR Y VALUES IN XC BLgCK lOS DO 1!0 J=1,4 XC(JJ = T{JXI) JXl = JXI*I C GET COEFF. IN X SEI_SE GO TO _7000 C RETUFN HERE WITH £OEFF. T E_T FOR UNIVARE OR BIyARIA[E 2O0 IF {NYI 300,2! 0,_00 2!0 Z=O.

JY = JX+NX DO 22g J=1, _ Z= Z + C{JI'_TIJY) 22O JY = JY+I FIGURE D--6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE 22 OF 26) 9.56 GO TO 9gqo C RIVARIATE TABLE C 30C L=L X = YI Jl = J2+I J2 = JI+NY-I JXl : SUBSCRIPT OF IST Y C SEARCH IN Y SE_'SE GO TO I000 5OO K = K+3*KX C INTEPPOLATE IN X SENSE NO. OF YS SUBSC_IPI - B_SE NO. OF COL.

C JY : J2+l + (JX-I- 3) _'NY + JXl-Jl O0 590 M=l,Z- JX : JY Y( M} = O.

DO 5?0 J: I,_ Y(M) = Y(M) + C(J) *T(JX) 520 JX = JX+NY 550 JY = JY+I C C GET COEFF. IN Y SENSE GO TO !05 Z : 0.

6OO Dr' 700 J:[ ,_ 700 Z : Z • C(J)'_Y(J| 9qqq RETURN C C SFARCH ROUTINE- INPUT J!,J2,X C -qUT PUT RA,RB,KX, JXI IO00 KX = O P.O 1010 J=JI,J?

IF (T(J}- XI 1010,1050,1050 ICI0 CONI I NUE C OFF HIGH ENP X = T(J2) KX = 2 C USE LAST 4 PCINTS A_,.F). CURVE E JXl = J2-3 RA : 0.

(;U TEl 1600 C TEST FOR - - OFF 10W FNl _' 1050 IF( J-Jl -I ) I. ORO , 1080 IF[T(J)-X) I082 _I OgO,!Oe2 1082 K'X = I X = T(JI) IOgO JXI = J!

RA = I.

GO TO 16OO TEST F_R LASI INTERVAL NO, YES, NO C IF [J- J2) I_00,i020,1500 1500 JXl : J-2 RA : (TiJ) - X )/(T(J) - TIJ-1) ) FIGURE D--6. LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE 23 OF 26)

25?

I_00 RB = I. - _A C C FETURN [_ACK TC MAIN BODY IF (L) 500, I00, 500 f C COEFFICINT kOCTINF - INPUT "X, XI , X2, Xq, X_,, RA, _ DO 2010 J=l,3 20!0 P(J) = XC(J+I)-XC(J) P(4)=P(1)+P(2) P(SI=P(21+P(31 DO 2020 d=l, _.

2020 D(J) = X-XC(J) C (1)=(RA/P(I) )_(b(2 i/P(4) I_O(}I C (2)=(-RA/P(I ))_(0(111P(2 ))'wO(3) +(RB/P(2) )'_(D(3)/P(_)),_O(4) C (?)=(RA/P(2) ),c,( D( i )/P (4})'_D(2}-(RB/P(2) }*( _(2 )/P(3) )*D(4) C(_'-)=(RB/P(_ ) )*(('.(2)/P(31 ]_D(3) RE TURN TO MAIN BODY IF(t) 600,200_600 END FIGURE D-6.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE 24 OF 26) SUBP(IUTINE UNIhT ( N, XA, YA, X , Y, L) REwRITTLN SFPTEP_ER 18, 1967 UNIVARIATE TABLE FOLTINF WITH SEPERATE ARRAYS FOR X AND Y - S 66 THIS ROUTINE INTERPCLATES OVER A & POINT INTERVAL USING A VARIATIC_N OF 2N[" DEGREE INTERPOLATION TO PROOUCE A Cr)NTINUITY OF SLI_PE BETWEEN ADJACENT INTERVALS.

D I MEI',:S I CIN XA(!), YA(I ), DI4), P(5) L:O I=l C TEST FOR _FF LOW ENC NO = YES IF ( XA(1)-X } IOO, 150, lO I0 L=l Cfl TO 150 i00 DO !20 I=2,N IF ( XA(1)-X) 120, imO, 200 CONTINUE C OFF HIGH EN. n I = N L: 2 ".._C Y: YA{I) GO TO qgg C TES[ FOR FIRSI INTERVAL ?00 IF{I-2| 2z.C,220,2z-,0 C FIRST INTERVAL 22O JXI= I RA : I.

GO TO e,00 C T'EST FOR LAST INTERVAL 2_,0 IF(I-N! _OC, 250, 300 C LAST INTFRVAL 250 JXI = N-3 RA = O.

GF_ TO 400 500 JXI = I-2 RA -- (XA(I)-X) /(XA(I )--XA(I-l) ) 400 RB : I, - RA FIGURE D-_.

LISTING OF ADVANCED GENERAL AVIATION Q--FAN PROGRAM (PAGE 25 OF 26,/ -- --,- .... _ .............. __._,,-_.A_-T_ _... _,_. C:_.-I,-"_. -

GETCOEFFICIENTS ANERESULTS

J = JXl

DO500 I=i,3

P(I) = XA(J+I) - X#(J)

D{I) = X- XA(J)

500 J = J+1

D(4.) = X- XA(J)

P(_) = P(1) + P(2)

P(5_ = P(2I + P(3}

R FSULT

Y = YA{JXI}. • RAIP(I} '_ D(2)/P(4) $ D(3} ÷

! YA(JXI+I) w,(-RA/P(I) '_ D(1)IP(2) $ D(3| + RB/P(2) m D(3)IP(5|

2 '_D|/-,.)} * YA(JXI*2} '_(RA/P'2) w_ DII)/P(4) m D(2} - RBIP(2)

'_ 0(2_/P(3) ,_ 0("-)} + YA(JXI+3) _' RB/P(5| '_ D(2}/P(3} • O(31 c)9g RETURN END FIGURE D--6. LISTING OF ADVANCED GENERALAVIATION Q--FAN PROGRAM (PAGE 26 OF 26)

Overview

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APPENDIX D

Cate_;ory F__ E._ Quantity F. E___ Quantity