Aircraft handling qualities data

SECTION I

INTRODUCTION

The purpose of this document is to provide handling qualities investi-

gators with readily usable data on several representative contemporary air-

craft. Included are those data required to obtain transfer functions relating

the aircraft's response to control inputs. An analytical description of the

aircraft's stability augmentor is also given.

For those aircraft for which complete information was available, the

following summarizes the contents and presentation:

7. Flight conditions for which computations are made

including: a. Configtu_ations (e.g., fuel load_ flaps,

gear, etc.)

b. Mach/altitude combinations

2. General arrangement

3- Control system description

4. Stability augmentation description

5- Tabulations and/or plots of non-dimensional stability

derivatives for trimmed flight

6- Dimensional, mass, and flight condition parameters

7- Dimensional stability derivatives

8. Transfer functions for control inputs

9" Selected_andling qualities parameters

10. Data sources

A page number cross index is presented in Table I-1.

The intention has been to make this report completely self-consistent

insofar as symbols, nomenclature, definitions, etc. The system used is

described in three appendices. Appendix A covers axis systems, symbols

and notation, and definitions of nondimensional and dimensional stability

derivatives. Appendix B gives the axis system transformations for the

derivatives. Appendix C includes the aircraft equations of motion and

transfer functions used herein.

X I

g

o

i i

<_ o_ _ _

_ _ _o_ _ aa

o_ _ _o _ _ _''_'"

. _. . _

The aircraft considered in this report span a wide range of sizes, speeds,

and uses. In each case_ transfer functions and handling qualities parameters

were computed for flight conditions which were selected to cover the flight

regimes of interest. A nominal configuration (generally cruise) was picked

for all up and away flight conditions. For this nominal configuration, plots

of trimmed non-dimensional aerodynamic force and moment coefficients are

presented. Also, in most cases, a power approach case is presented along

with a tabulation of aerodynamic coefficients. The coefficients are based

on rigid wind tunnel data 3 estimated flexible data_ or flight test results,

depending upon availability. This is indicated by the words "rigid, "

"flexible," and "flight" on each aero data plot. Also, the axis system is

indicated by "stability" for a body-fixed stability axis system or 'body"

for a body-fixed system aligned with the F.R.L. (Further clarification of

axis systems used is given in Appendix A.) Descriptions of control systems

and stability augmentation systems are given along with transfer functions.

Where a longitudinal control system has a significant effect on the equations

of motion (as with a bobweight) the stick-free transfer functions and handling

qualities are given.

Transfer functions are always given for body axis motion quantities.

Handling qualities parameters are also given in the body axis. All accelera-

tion transfer functions (a z and 4) are for the pilot's position. Thrust

transfer functions do not include any engine response characteristics.

A substantial portion of this report is in the form of computer printout.

The mnemonics used in this printout are defined in Appendix A.

The handling qualities parameters given in this report represent only a

small fraction of those developed over the years. The majority presented here

are used in past and present versions of MIL-F-8785. Although only SAS-off

values are shown, the definitions given in Appendix A are general and could

be used in conjunction with the HAS-on transfer functions to yield SAS-on

handling qualities parameters.

While complete coverage of each aircraft including only the "latest" and

'_oest" data would be desirable, the major criterion used was that the data be

accessible to the author. This is why only isolated flight conditions are

given for some aircraft, and also why, as those people more intimately familiar

with each particular aircraft will recognize, the data presented may repre-

sent an early estimate in the design process and perhaps the "nominal config-

uration" is one which never left the drawing board. The data have been reviewed

and, although not all those presented indicate unquestionable trends, those

data known to be based on only early "guesstimates" or showing unreasonable

trends have been deleted. In somecases data were estimated by the author.

As to how well the data can be expected to match the flying aircraft, it is

assumedthat those for whomthis document is intended knowwell the difficulties

of obtaining derivatives from flight test data. Every attempt has been made

to insure reliable translation, interpretation, and transcription of the data

from their source documents.

The manufacturers of the aircraft described herein can not be held account-

able for the information presented, nor would they be bound to concur in any

conclusions with respect to their aircraft which might be derived from its use.

-33A ACXSXOmm

"The NT-33A variable stability airplane (Serial No. 51-4120)

is an extensively modified T-33 jet trainer. The elevator,

aileron and rudder controls in the front cockpit are disconnected

from their respective control surfaces and have been connected

to separate servomechanisms that make up an 'artificial feel'

system. In addition, the elevator, aileron and rudder control

surfaces have been connected to individual servos which can be

driven by a number of different inputs. These servos receive

their electrical inputs from the artificial feel system (pilot's

commands, position or force), attitude and rate gyros, accelero-

meters, dynamic pressure, _ vane and _ probe. This arrangement,

through a response-feedback system, allows the normal T-33

derivatives to be augmented to the extent that the handling

qualities of many existing airplanes, future airplanes or hypo-

thetical research configurations, can be simulated. The original

T-33 nose section has been replaced with the larger nose of an

F-94 to provide the volume required for the electronic components

of the response-feedback system and the recording equipment."*

Transfer functions are given for only the primary surfaces and engine

thrust although the NT-33A also has other control surfaces and a range of con-

trol crossfeed and feedback combinations.

Aerodynamic data, for the most part, was taken from AFFDL-TR-70-71. However,

longitudinal data for the high lift configuration was obtained from LAL 1 27

andMach number derivatives from NACA-RM-7116.

.r-I 4_ .r-I or-I I1) (1) m 0 CD r-4 I::" 0 0 • _ .r_ P-I ,.-I •r_ _/_ t-.-.1 q_ bid .,rl ,-4 O

I I Ca E_

.r_ 4_

0 0

0 0 _d

q o

I

o

0 0 c)

, ©

4_ ¢-

I

i

f-!

!

@ r/l -,-4 .r-4 .r-I I:I O

#

,'d Q 4_ O

d

.,,-I

o _

o _

.4,} • Od (\J (_ O _--7 4-_ 4_ 4_ q_ q_ _ cq c+d c_ q_ Ckl ,,,4 _: f i i -P r4 ,-I b4] _) b.O cH I

_lC4 4 4

Ill ¢..} ,,--,i E_ ,--I 0 kC_ 0 0 0 r4 p_ _ 0 C'_ 0 0 0

,-,8_8oo

f2_ _ 0 0 ._ _ _ c_ [_ _ 0 0 •,-I _ t _ CO _ CL, 0 ,rl Od O _. C_d % C} _ 0.1 tk.l _£r -J r"-t -P 42 bD H > II II II II II b[ [- 4 II II tl II II r-I _ htg _h Lr'_ _ @ N _ N N '_d \D [:: O I-I _ H .JO

__o

4._ d_

°"

t_ qJ O !

I-'4

b

N

I

II I! II .--i

NT-33A

PITCH AXIS

Variable

Variable

Feel Stability

Input

Input

I

_]ST(in) ] -I0 _._ ---- _.3 Be(rod)

s z +.89s + 22.5

FST(Ib) _..026

ROLL AXIS

Variable Variable

Feel Stability

Input Input

FLAT (ib) I OST _,n I0 _a(rad)

sT

YAW AXIS

Variable

Variable

Feel Stability

Input

Input

I

I_PED(in) I 2.34 _. = _._ 8r(rad)

FpED(Ib)_

Feel system parameter values shown correspond

to the "Front Seat Engage" mode (normal NT-33)

Figure 11-3. NT-33A Control System

TABLE 11-I

Power_oach Non-Dimensional Stability Derivatives

h = sea level

VTo = 228 ft/sec = 139 kt

oo = 2.2 °

Longitudinal Lateral-Directional

( Stability Axis )

cL = .813

cy0 = -.72/r

cD = .139

Cn_ = .049/rad

CLm = 5.22/rad

C_0 = --.127/rad

CD_ = .94/rad

C_p = -.O7/rad

% = --.401/rad

C_p = -.045/rad

C_r = .20/rad

Cmq : -mo/raa

: Cnr = --.16/rad

CL5e = .34/rad

Cn5 a = --.O09/rad

Cm6e = -.89/rad

C_5 a = .14/rad

CYSr = .17/rad

Cnsr = -.O73/rad

C_5 r = -.OO2/rad

' SL NT-33A

.... 20,000 ft 13700 Ib

w

------ 40,O00ft .263

Rigid

B

Cl o

(deg) n

D D

\

4-

Z-

0 o

LO r- rJ O

oJ

I I I I I

,:_ _Q

-- 1.0 (%1 -- _C)

Od 0 0 0 O. 0

, 0 o.

F-r'-

z_

(..)

.4-- W_- W.-- f..) 0_

O0 x

I.LJ w.

O0

j.-

O0

_Jc_o

o.

000J_

! ,

:l

II

(.)

I I I I I -

0 0 LO o_ -- LO

o_ -- 0 0

m

6-

CL a

NT-33A

!

13700 Ib

(red -I )

I

Rigid

4- 4

!

!

!

SL

..... 20,O00ft

2-

-------- 40,000 ft

I I I

I

.6 .8

.2 .4

Mach

1.2

CDa

(rad "l)

I

I

.8

l

I

I

l

%

.4

.2 ,4 .6 .8

Mach

Mach

.2 I .4 .6 .8

I (_ I I I

/

(rad -i)

-.8

SL

NT-33A

..... 20,O00ft

13700 Ib

--"-- 40,O00ft

.263_

-1.2

Rigid

Mach

• _ .2 .4 .6 .8

Cm&

Cmd, -4

Cmq

(rod")

-8

-12

_Cmq

-16

NT-33A

13700 Ib

.263 F.,"

1.0

Rigid

CL M

"21 2 _ 3 6 8 4 i

| _ .4 Mach .6

-I.0

SL

..... 20,O00ft

------- 40,O00ft

.3-

CD M

I

0 .2 .4 .6 .8

Mach

Moch

0 .2 .4 .6 .8

Crn M

-.2

-.4

.4

CL8 e

(rod "l )

NT-33A

.2

Rigid

I I I I

O0 .2 .4 .6 .8

Mach

Moch

.2 .4 .6 .8

0 o

I I I I

-.4

Cm_ e

(rod -j )

-.8

-I.2'

1 _;

Mach

.2 .4 .6 .8

1 I I I

Cy_

(rad-i) -.4 --

NT-33A

SL

13700 Ib

..... 20,O00ft

Stability Axes

------- 40,O00ft

Rigid

.2

Cn/_

(rad -i )

I I I I

.2 .4 Mach .6 .8

f.®." /

-.2

Mach

0 .2 .4 .6 .8

0 I t l

-.2

-.4

c.tp

(rod "I)

m6 Boa

NT-S3A

- - SL

137001b

..... 20,O00ft

Stability Axis

--- "-"- 40,000 ft

Rigid

.O4

Cnp

_4r _,f

(rod "l)

-.04

-,08

SL NT-33A

• 20,000 ft 13700 Ib

------- 40,O00ft Stability Axis

Rigid

.3-

C._r_

Cn r .2 --

\',, \.

(rad "l)

%%% _ " """

C._ r

0 I I I I

.2 .4 .6 .8

Mach

'.1 Cn r

t9

.2O

.16

C}s a

(rad "l )

.12

' SL

NT-33A

13700 Ib

..... 20,000 ft

40,O00ft

Stability Axis

Rigid

0 I I I I

0 .2 .4 .6 .8

Mach

.01

Mach

.2 .4. .6 .8

Cn8 o

(rod -j )

-.01

¢

So is sum of both right and left

-.02

aileron deflections

2O

Cy_ r

(rod "l )

I I I I

O0 .?_ .4 .6 8

Mach

Mach

.2 .4 .6 .8

I I I I

-.04

Cn8 r

(rad "I)

-.08

NT-33A

, SL

m *== 13700 Ib

--- ?_O,O00ft

Stability Axis

---- _- 40,O00ft

Rigid

.04

C,_sr

(rad "l )

.02

I _ i I I

.2 .4 .6 .8

Mach

_e <1 ,0 r,,l I'- o_ p i_ _r+ ..4 _ 0 j • .4 1%1 • <_ . • C._ 0 0

o • _ _ -_ " _ _- o o

• _ ¢'_ ¢_J +,PI • _ I<'I "41" ,_ 1%1 P_I II

Io

ell _ 0

. _ o _

o

3 eg

__ ' _ o

_+ o _; " _" _ o _- _+ _ o + , o

_ , o o + o o o _ • . . o _ ® j o _

I_ _ r.- 17 _ _ _%j o_ _ t+_ 0_ • _ P" • • • 0 ,-I (_; _l" t II I<"X GO I

; +

o • O • * O _ I" • N l,O _,

o T ; = o

• • 0 0 ,Ti I" " I • • I I" " I rJ_ H ,0 • 4" cO u_ _. I _. ,,..4 I _. N 03 bl_ LIJ 0 0 4 i 0 0 _ I_ 0 0 _0 • _.i ",I"

N _ o o o _ o o _ _ _ o I J"

• 0 I" 0 • 0 u I" _ 0 • " I I" I" I " I=I C)

o

.i.)

ooo

I It) I _- 0 ,-4 0 0 -- 0

_ _ _ o o o _

• • o 0 i ff'l • I I I " " I I " I I I I H [/] A -,-I _I" lJu i",4 ._u w ._t 0 _ _ U L(_ I _ ¢_1

g o ...... _

0 • 0 _ g) 0 I_ _ _I 0 I 0 0 -- 0 0 _ • _r 0 • I I I I " I I I #q v

o

,0 ,,1" _0 I_- n,_ r'm _ uJ ..J -1" -.1- ur_ O ,o 0 0 0 _0 • ,_D * 0 0 $ N _ r'J O ,-_ O "-_ 0 _ O • O • _ • • O • I • I • I' I I • • I !

_0 ._ _0 r¢l ,-4 ,4) od u'_ 'd" .,t 0' h- -tO _ 0 co _ (o " 0 "-_ O_ " "-' N C_ ' _ N c_ r_I 0 0 C _ 0 0 0 0 _ _ " 0 0 • _ • 0 • 0 0 _ a 0 | l _ I l I • I" I* ,4 O N

Om _o

er, OO¢_ • ,0..0 fel 0 .-,_ N • ,, e¢_ _oe f¢, C_ 0 e..-, I I • • I I I v O u_ <D _ rr_ _. or.

_1" • e(O _o 00000_ OO i_ i°N_ )N

_ °,-_

I I ww O'.4" co O . O Pr'i _JO0 e O- u_ f_- O0"OO _T__.

eft/ .N ._r .-4 • I i • I ee I f,.

_0 oo 00 .,--,i _- _0 N f_ phi e rrl I_ _'$

OO ._o

.o-.I" ..-4c) • • ou '4" • • I I I" I • I u njf,_ fMf_ , • • • e,_

_o_

,.4P_ • _ule_ I I 1 !

I w_ 0 • ",lr 0 f.r. _r" ¢0 e ...4 _ 0 OOU_ • e_-I IN ..I-,-4 • I I • !

I r_ oe O _) _0_ .--, lir_ u'_ "'.1"0 " i I I • I I I

_-_o

_0_ _ODO_ eO_ eJe_

_- • •

I I v Z v O O IDur_ _O f..

• • e_.a oO • 0.

I II v _D _O f_" N r_- i_- o _ _0 _O OO_ _, O O " .,too , _0 ._ OO ,4" OO_'_ OO ._ CI_ .N • , | • ! • I I I ! _w I v ra- .0 ,.T O !

I (Du% N ,._ 4- UJ (N _" Om-,_ r.J _ _4 OO • 00 • {_ . 0D .

OO o_ 00.-* I'I _n .-:r I I II 1.1% u,% !

OO _0U% OO.y ueot L) • • I • ! !

• I !

H ----

E4

I erl kr% .0- .-.i -P .I" v) r-- .Oe,J _' .0,4"

LrA (,9 • _o_ oo._,-

r.2 • _ (D i'- • o.o_ H CH O9 • • I • I I I •r-I r.9 u,._" I I _o uJ -_ ,o u. co re% ,,T r--

_o_

our _ ".T 0 -,T '_ " oo 0 • • .(%1 • I I • ° !

I I ,_- er_N UJ 0"4" p-_p- _ °r_, D

• 0 °

I I I | 0", _r_ eel c0 r_.o O _% ('4 Oo (DO_T ,.r> p% ,,-.4 oo (DO • • • I I I" I" ,.-IN p.

Z_ Z Z

2_

O o o _ _ I .-, ÷ v I_ 0 ur_ • 0 P_ • F.d I • (%1 _ • _.I Q o 0 _ _ 0 co N t'_ m uJ x ÷ ,,-4 p,, o O m _ O I N • * _t i I I I _' o _ (%I f_.

'-4 -J o ,m cN I_ eel _ I ,-_ 0 • I_ I • i* _0 L¢_ * ¢_1 L_ Q0 O" 00 O r-- ,,1" c0 _0 r-- r_ _ O (_ ..-4 ,._ .-4 O (7'

_ o co

• _Ir LI_ ,-4 • • • e • • I I I I I O co I'-- _ O _ _0 ,_) ,,I" O u'_ _ • I ¢) u_ _I _I_ O I-I I I I I E_ H 0 C_ _ ".0 0 0 _ ",I" "-I" O O ,0 • O ,,I" _ O "-_ O 0 _ C_ c_ 0 '-'4 -- _ 00 _ el I 0 • C'q _- • • ,, • I I I I O I--I ÷ I_0 _-_ oO o _ # o _ r _ _ _ o o _ _ .

J 0 cq * • • 0 0 O0 * _-- I.--I r_ I ! I H Co H ,--1 c_ O M 0 o _ 0 • 0 t'_ 0 _ 0 I I I I I-4 _ _ _ + I i.-1

N 0 • ,--4 O -I"

I I I I ÷

I o

o o o

I I I I I I v o r_ O o_n ¢00" O e'% '4,0 P" eo ,_',D 0"_0 • P.- O er_ .% O0, C, • "_0 " • 00 • ec} • •-._O ,_D e4 • 0 • o,,-i N • e,.._ !

c) erl aO ,-_0_ O, o_r_ 00,'-4 0 r_ O, f,_ u% ,O eq _', 0_'_ P.. e.,4 P,- Nrr_o • 00' U_ ,0_ O ,0 • ",,tOO • • 4"0 • ON oO4 • el1_ t_40 era4 el%J I I I _._ N P" 0 _ Ou_ er_ ,O ,4" O ,.._ ,d" ,_) 0_0_ • D NU_ ,00,0 _0 ,0,0 O ,0 , • -* 0 .-4 , .,.., e-4 • 0,=4 ,,-.4 "'40 0,...4 I i ° _0 O0 ,.4 ,.4 WD _0_ _0_ ,-J ,_ ,0 ,.-4 _nwD_ _0 00"0 • I_0 ,, ,0_ • • _.J ,-4 Mlo,e (,q • • I I ,_ I_ r.- ¢;.i o,_r ,,,,.If,,, U,_U ,0 • eW p,- • ,-.4 ¢%10',0 • ¢_ _/" ,('1 I I !

u t,_ =ju ,"l CM 0 h- 0 ,,..4 • 0 r_l r-.

ee%; ,,,--4 • e(,_ _0 _ • ,....4 N • .-e t !

H _O_U_ f_ W_ ¢13 _ _0 _r_ _"_ 0

_o_. O_

" 0 "0 • _.

ee._ e,,-4 '4" • J_ !

I _0 _OQ_ ,.,4_ 0_0_ • 0"_" f%l ,...4 • ep,.

eo_ • O • • I!

I _N ._ _ _w_wv _v _Z ,I O

o_

N_ 0"%U'_ ,n _ 0 '4",O o_o_ o4 ,-+ _) _ID _P 0 r-- +0 ..-I e (,n (_t e I I I I I I I !

4, 4"

o °

r-. o41--.

t.%t P.....4 a) u,_ O "O O0 • , o • • oO , ,.-4 ON ,N _o_ r-- O o40_ --4 I I I I I I ÷ o

_o

,0,0 0 N _o_ L_ m'J I_

o_

_O_O 0 "0 O0 '0 _ • o • • ,O,,, _O_

i" T

, I I I I I CO 4- u%m- o

B o

cO ,0_,0 _o_ _o_ OO_ _O_ oo ..-+ (_ 0-% • oo(oo _ • .0+-_ • • w- I" I I I I I I

+

,0 N .;i- f_. , + oo_ o_._ 4._ _ • , , ,-+ u'% • O 4"-4 _0_ ,...+ 0 4" ..-1 .--.

• I I I I i ° I' ._ <_ • _ H c_ N o ,,t -,t c,_ u,% O0 ,O ,,o_ • o • • • ic,_ .,-# _0_ I I I I C) I !

+

_o

_o 0_ u% .o N .-+ 00_ 0 N tON _O e4_o _j -1" -4" N _ _.) ,o4 I I I I I I I ÷

_o

ON_@ ¢J_ 0 " _o

O0 ,04 o_g

,O,_, • ('4 , O _0,0 I" I • I I I, I

_2_

_ww

z_ 7

Z ÷ O u _, cO _ O -_ _ _ _ _ * ,0 U'_ CO O u_ _t e_ I _ _ t_ I _- u_ **,I u _ a0 -, O" -J _ • N I • -- -- _ O _ _t _I -- _ I v" p..

O 0 0 um r_ ..t _0 _O O _ _ _ 41 I_- O u_ _r_ _ I * * • O O • _ I_ • P_ I o O O 0 _ O • _ co • --_

(]Q

o _ ® _ + _ _ _ o _ o _ _

_O O _ a0 I c_ O r_ p e_I _ O _1 _ • _ I • • 0 _ 0 0 _ _ _1 • _l !

v _0

r_

I-I

+

0 r'_ .0 -,t" _ -.1" ,_ t _- _ _ t'-- ...0

_ o _. _ - - _ o o o o _

E_ u_ I_ • • I O O O O" O • ,-,I _0 • O

<_ H

"_ * 0 _ I * + * _ O @ _ _ • !

÷

A

I I .-_ J 0 L+r', ,_ I c_ ,.,.,+ 0 P'-- ,'_ u", 0 _ .-4 l_ • L_ • _ • ('%1 + • _,+ I%J t'%l • I I + LU _ _- _ _ <++._ "_ I -- _, <'%1 ,-, + , r,,.,l Or, _j ,_ _ ._

3O

NT-33A DATA SOURCES

Hall, G. Warren, and Ronald W. Huber, System Description and

Performance Data for the USAF/CAL Variable Stability T-33

Airplane, Air Force Flight' D_nsmics Laboratory Rept. No.

AFFDL TR-70-71, Aug. 1970

Tests of a I/5 Scale Wind Tunnel Model of the TP-80C Trainer,

Lockheed Aerodynamics Laboratory Rept. No. LAL 127, Jan. 23, 1948

Cleary, Joseph W., and Lyle J. Gray, High Speed Wind-Tunnel Tests

of a Model Pursuit Airplane and Correlation with Flight-Test

Results, NACA-RM-7116, .Jan. 21, 1948

Statler, Irving C., et al, The Development and Evaluation of the

CAL/Air Force Dyuamic Wind Tunnel Testing System_ Part l--

Description and Dynamic Tests Of an F-80 Model, A_'_'DL-TR-66-153,

Feb. 1967

Flight Manual_ USAF Series T-33A Aircraft, T. O. IT-33A-I.

SECTION III

F-IO4A

F- 104A BACKGROD'AID

The F-IO4A is a single place_ lightweight_ supersonic air superiority

fighter powered by a single turbojet engine with afterburner. The wing has

a full span leading edge flap. Trailing edge flaps have a blowing-type

boundary layer control system. Control is provided by conventional ailerons

and rudder and an all-movable stabilizer. Pitch_ roll_ and yaw dampers are

incorporated_ however their effect is not shown here. Pitch and roll con-

trols are fully irreversible while the yaw control is a cable-actuated rudder

without boost. A bobweight is used in the longitudinal feel system. Its

position is assumed to be at the pilot's location.

The primary source of data was LR 10794. Drag information was obtained

from LR-12873.

The nominal configuration used here is the combat loading for the F-]O4A

based on actual weight and balance data. The PA configuration is a typical

loading at flight manual approach speeds.

o

.H

o

c)

,-t

.,-4

\,-

OJ p_

o

o o

• r-I ._

0 o

,r--I

%

ry_

o

4_

o

r_)

rl

!o

I I I

°r--I

o

,--t

_1

8 o 8

i/]

I

q q o

o o d

o

I f---4

H

H

u/

(1)

-e-I -rq

b_

.r-I

,-t

o _3

.,-I

-r-t .H

O ii1

o

-,-I -r-t

.rt

o

ii ._I

.r-I

4_

._I

,rl

c) oJ oJ

Od 4_ 4_

_-_ c_ -p 4->

o 0

l_q 4.> r_ r H

111 ¢+_ i i

r-I ", I b.O b_

"d O b.0 _ ¢

:d o _ _ ,--I ,-I

o

_o o o

o _ _ o _, ksD _ _-_

_ _h cO

P, 4._ r--I O 4_

I'--I U II II rl II

H _ II II I1 II II

r.D 03 f_ Cb _ _ 0 I-4 H H

ID

wu

_0

r-i

c_

©

Z

m

o

I

&

!

H

_o

._

I

!q - >°

II

rJ)._ iu

C-_

F-104A

PITCH AXIS

8SsAs(rad)

G

FST(Ib)

8s(rad)

57.3

i

8s(deg)

-20 -I0 0 I0

3.2

Oz

32.2

F B

B

az assumed to be at pilot location

/in)

ROLL AXIS

8aSAs(rad)

F LAT --I I

I i 2,,4

ST (Ib) --i 2.7

_! 5"_ _ 8a (rod)

YAW AXIS

SpED(in)

7.35

FpED(Ib)

57.3 _ 8r(rad)

KDIR_

2.0

K°["/'I b/in_

1.0

o, I I I I I

0 .4 .8 1.2 1.6 2.0

Mac h

Figure 111-3. F-IO4A Control System

Power Approach Non-Dimensional Stability Derivatives

h = sea level

VTo = 287 ft/sec = 170 kt

_o = 2"3°

_s = --7.1°

Longitudinal

Lateral-Directional

(Stability Axis )

CL = .735

Cyp = -1.17/rad

% = .263

cn6 = .5o/r_

CL= = 3.44/tad

C2p = --.175/tad

CDa = .45/rad

C_p = --.285/tad

Cm_ = -.6_/ra_

Cnp = --.14/rad

Cma = --I .6/rad

C_r = .26_/rad

Cmq = ->.8/ra_

Cn r = --.7_/rad

Cg_s = .68/tad

Cnsa = .O0_2/rad

Cm_s = --1.4g/rad

C£5a = .039/rad

Cy_r = .2OS/ra_

C_Sr : .045/rad

C_ r = --.16/rad

CY_d = • 0325/rad

CnSd = --.025/tad

Cg5 d = -.O044/rad

I I I I I I 1

00_

G)

m_

o.

j-

O

_LLO

_0

O0

I

LL_D

I I I I I I 0

0 _ OJ --- _ 0_1

-- 0 q 0

Q

Oooo

_000

_J

O0

Od

c_

O_

.l( _o.

_J

O0

_D

/

_o.

q

!

t-

o

!

_GO

!

--LD

I ! I

I I I

0 0

u

Q

f.j o

L

q

C_J

IE

.D

0q.

ooo_

I

N

I I

JE

J::

o

o

co

O0

E)

q,.. q-- q_-"

"-00

ooo8

ooo

'Ill

I 0

'ili,

I I I

0,1

_1" O0

0 0

0 o. o.

I i

!

0J

I

I

! i

I=ll

"0

E E O

E "o

L_ r.j ,,..

L.

- N

--c_l

N.

I I I I I

I I I I I

Iv) _ --_ 0 ,--:

I"

I"

_o q m

oJ

_ cl)

I

OO

OO

o o

__{D

0r)i_ ii - )

II

I i

!

II

i

OJ --

I

_o. o-

(-

cJ

_E

0D--

-- 0D

(.i{) --

m'-o -_

o o _

u___,T

0J --

L

I

_I I I

O

O

Oa

O O

oJ 00 ,

I I

i

I

m i/1 i u) !

(w_ "T3

_J O

_I O

I..

L) -...

o B

q

-®

Od

_o_

- j÷ o _ |

--®

m ,, __E.

i

_m I

m |

I

' _/ -

t , -

i i

I

, /

N

t , i

I

o._

o. o.

m

, -

-

u

u

O

O

o_

8o(. o

II

N

1o N.

I

,I

1 1 I 1 I

I I I

O O

O

O

O O

o. q _. _. N

! I"

!

T

'"o

O O

L V

q

N

°_

3'(

I

_--.-__

_o--

®

T_ _..-

O0 ,._

I

t,-

u

q--

r-

U

#

/I

• I

____

' II

I , I ,

I I I

I I I I I I I I

o

0 0 a') 0 _ o

o

I I" I°

I I 0 _

I ! !

I I I

Q.--

L-O

¢j 0

_.) _

lb.

o.

q

o

._ILO

i

!

I

| i

J

I

#

,¢.

/

_C_J Od

--o

I I

t-

o

=E

u¢O

<_ .Q >, i ,,ore

_oo.--

"_.'2

-:_,oo,

LL __U') _'i_

I I I I I I I I I I

I o

• "-: 0 (30

o.

i i I

I

! !

!

I

m g lb. |

_ w 0

(..) 0 0 o

I,.

lb.

Q Q

c_

F

t-

C_

T

t- t--

I

.C_ 0

o_ I,. 4--

t- CD

D

O0

0 q-

O0

.Q cD

Qo

_I if)if)

_ I, _

¢/)re)if)

I

II

_'_

!

I !

/

_gr_

II

I

#

/

--o

e'-

.£:

U

u

o

o_

x

c_

m

I I

I I i

0 _0

_O . O. o _ o. o.....

o !

t,_ O

C.) I.

o.

oJ

_m.

_0

oJ

_o.

r-

(J

=S

--aO

_J

I I

I I I l

OJ --_

, ," O. o.

,.. -;-

c_o "o

>" 0

c 0 _< 0

r_ ,.-

÷ ÷

d

C, P,-, • 0 0 O, r_ O, .,IC) e • C, 0 _ • " • 0 q_

I-I u_ o

.-., 0 o o I-I OX ,dO

d _

o cO _ ol

-_ ? ? ?

o lu

q_ H O'x H

•_ o o o

I I I • ,-.I _ u', I C, " " " • ° _ r-, .o ,_ .-_ ,,t _ O_ I _ ,_ t _- _- _ 0 e_ 00 0 _ _'_ _ ,-4 _l ,-a I I I H IC_ IJ ° ' o: 0 0 0 0 ° " 0 0 O" ,_1 ,-a O" ,0 " 0 o ? ? , I 0 0 0 0 0 O_

-_ ? ? ?

!

, , _ G G

ut_ u,,,, I _ fD 0 LL.. "t" _ :> :> ::_ _: p... ,I ,t 0 _, uh C LF I I'.- I ! • I I" I I I • •

c

l • I l" I - • I • • 0 " I" 0 I' P_ "" I'_i Oe l_ I" I" _ I'- _ _._ O0 0 f" I'- ,_" ,lJ _ • "0 I J" IAJ • e 0 I_ e _ , _-_ .-_ • 4" .-4 O TM O O O 0 " O 0 0 0 _ _- 0 cq 0 0 • • • C) • _ • 0 " "-_ _ _ 0 CO I l " I I • i I ' " I 0 ",t

_ -- o o o o -- o o o o • • -_ _ o ,0 o

• • 0 • I'_ , 0 _ t" -,I" gJ 0 I " I I " I I " " I I _- I_I O_ 4) Im CO I _-

T

o -_ _ _- _ m o m _ _ - _ _

fll

N t._ CO O O O O ' O O O • " _ P'- O ,_D O

• • o " 7 ' o 7 _ '_ "' u

I I • I I' | " " + 4) o _o _ .

..4 • f_- ,0 (D u" O0 ,0000 OH `00 * * ,-4 `0OO *_0" cO . i',-¢X) .-'_0 * *u'_ • 0 4" _.- c, 1 *

I • • t'4 T I

I + -Z

._S_

_o ,_ *f_4.

_0_ OOO'4 0`, 4. • _ ,,-,4 ¢_1 0 _000 * OOtkl e,,I f*-- _7 , o o _ ! I I _ 4- `0 o 4.o * ,.-_ oo o_o Or, j, eOOt_ ,.-4 * (;" O" *0

I* • _J 7

!

I v" _0 oo o u,% •0",,-.4 *_'0 , t_. _ • u,% o_ co i-- .T 0 0 ,-_ ooo ,....4 _o oo _

? I

I I I I b- o `0 o

[--!

,o ,_u,% ,1"_ o

r.)

u_ i'xl `0 _ eel

_o_ 0`0o

*4"0,,0 0,4-,-4,0

_o_

-.-* o o ,,I3 4",-, C_--_ *0 I • I I I

H 0

r--

_o

(xJ .-_ u-% _oo • *-40 0,40, `0 .4- _ `0 oo `0 r,-O •0"I • i• I II -7, _ 4.

._,o

`0 .e4_

_ _ _,o

H _ _o 0-0<9O t-- u% -4" 43 e4*_ •0 e_ • ,-4 ,..* i I I 4.

, 4. 00 t-- i _- H q-_ _ pll O _ m ,

oo_

oo • _0 ,0 • ,--,* 0 0 CO I%JO • _o_o `0 •¢_1 P.,-o • ,,._ -,tO •,'-_ I * I !

I !

÷ `0 m- _ t-- * *OOi _ m-_e4 ! • • q" ..r • co ._ .4 f_l ,---I •O rn •,-_ I I I I r.- r_l r.-- cu ,-i 0",,1",;.,' 0_ co _-_ _ r'-- 0 _ • Un `0 .._ ,-4 u3_l ._ o _ _, "_ .

.,--*4" 4. • • e4 • -,t U'_ 04 '4" • * I I | I ,..._ ¢xl

A_w

u_ ,'-J A.

°W<_WW

Z ,4- 4"

?

-_ _._ _

-o_

L," • OCs -'4" I !

I I I."

"-¢G e4w • _-_0 OC_C f'--O _ , C_C_ e_ ado ..4" I • I I I I I .4 .-_ o I ku<t 1:o ,,I • _ o cr_ .4- • CJ , _'1 Go ,IF, :-4 • e'_ • • I I" I I v 4_ 4- 4" r_ I LU an_ _o_ N u% .-e 00_ e4 ut% (7.

I _" • ,4" • CC ,L-_ O0 ._, moo •

""i"

I w_ 4" o II I ,I-

_w_ o_

_o _o_ u% • 4 '4".00 .

000_ ,7 I o" 4- o

#

r_ u_o tU _t 00 I _ ,,0 ,_C O" _'% r'% u-_ 0 _u

H

O_ _gG_

o_

,.-i • .to ._ • I I I r_ u u_ r,l L_ um _o- .

l_ ....

OO

_u o c2 ._ _,_ _0

co o ._ aO 0 u', u% • I • • I I I I

R

u u_ I I I o • • ,-4 _ID 0 .%1 b'_ .

_.- 0 i'd 0 _o_o 00"_

_o_

o • I • I • • I

T

I I I

(9 ?

m-O" I -30 w o o- u'% IN ,4 _o t-- o ,._ , O0 .U" .. • t • I • ° I I I u.J o _ -_ -r -r .,T _rl ',T O_ "_

_,'_

i I I "" _ Lu uJ _J \I--If _ <_'_. ',,4 __ rn,_0 O mJr4 O I'41"40 • e40 ,-'_ o br_ co e,_ .-_ e,,i e,l ¢_ O O 00 O_'X* _000 * • O • ,_ • • ,_4 °O .-,t" • l'4 • I I I I +

S

_o 4-I."% _ ,1"4" _O_ O O _ ,.-* (xJ O ,,I" • O hn o_ O

_o_ oo

O.-_O • • ,I" O O *%J O_ • O * ._ OO .U"% I I I I i I I ÷ ,4 ,4"a_ o i,_....e ,o .O .O u'% '_ ,o .--.i aD O_" OOO'I .-4 t-.- (..) c.) • .._ • 0 • ,_ i l I I I I oo O',4" O o ,O ,O .-' _' :xJ 0_ _n t-..

_OOO.

.-4 O c00_ L*'% OO,_D • O • e_ !

I I !

I | I _-- 0 ,0 o O"

_o

_o .4",4"-.1".0 ,0 _O _ ca I_- ,_ t'- t-- O C) (_ .

O 0" ,_' • (DO ',_ O | * , I H w I t-.i _- O t'.- _o, 00 u'_o u,% _,,o ,'40 • • 00.4 * O _ ,,0 r4 O O --'_ • . .,.-4 "0" I I I I • I I H • a_ .-. (x) cO

;_ o

.-'I--40 _O_ .OOC • .-_ O e4 • .-_O • *Q' • , *u% | I !

!

[*4 _ ÷

M _

rJ O o

_;.

J _ • -4 ._) O-.tU_ *

_o_. .OOO_

,-4 In _o ._ 'N

?.?,_

I I t_ u_ O _0_ o'_ _ exl u-* ,O . a0 _r, 4" C'4m* :W t'- _"_ e4 ,0 a0 u'% ,O C'4 ..-e_I" r,.- ,a" ,.-I s% ..-4 • • *_0 • -e ,-., • ,..4 .o I I ! I * !

r,- _0 (D _. m.. a0 _e _.Jt_ 0" I-- _", a_ 4" ._ O U'_ e.4 o o, £%10 O O • , • .._ U-% 0 4" .,-_I I • I I I I ...e C3v_ #- u. :D ,_,%_ z

_:)'_ 7

Z

?

u] (x'_ _CZ um _ _, COl::) .oe OO "4" f'- • "4- I I I I -_" I.I- C_ .L., ,..-, N l.I 40" _ (%! _ U% _ C, eoo_ GOC C, CJ*_ ,I I I I I ,,9

I

I

_ _,_'

I"- Q 0 I',.- c. • -u'_ • c2 • _, • • I

.( I

!

I I LL, I'M _ _b • -, c('l 4" <'_ ._ _ o I_- oUm oo ,L_ I • I

t" I

_w •,.t _D ,o I o LIJ I"- _i_ 00 (f,O ..-., r-I ,'f,l _- ..4r ,,0_

i5 °

• I I I I

H

4" L_ • ,---¢ H L0_ bfl [/3 uu ._ e* • I I H _ ._ CQ I I f l.u I:o LU I"11 i',i

_gN_

4 U "P_ oo _ 0_ o, I I I

T cu

bJ (.J nl l'_- iJJ_ ._r c." co .o i'--. (_o ? o r..l u'_. o_ _g2; _i_ oa r,,l • • ,.& ,] o_i .-i L] r,j ._ o l-.i ._,.

• i • • I I t O" u_ 'JJ 4" O _.?

pr_oo uJ (:_ ,,o ,0 IP. _" " LP {_Jco cq _ ..L • .-i ..-4 • I • I w_ I I I ,,t b- _-u 4" _, .-' ,.-.¢ r_ o

_o.T -

i I I o o Lr , o I I D_ G r_ O" o .-_ r_ Io i'_ r_l ' C t_ _rq N .-4 I o _ _ I rQ I !

H

E-I

v -.t I uJ g.

H 0 I%t _ ¢'_ T"- !

I v _ O O N O ,,-.I _C_ ,.--I ,--4 I I O"

o _ _

C _ • 4t ,'_ I I I I• ,.t- u'_ • I_ ¢_

G

I.,L CO ;-- CO

_ o

,"4 U_ -- _ h" N -- 0" 0 4 "--8 0

o _ 3

I ÷

I

"_ oO 0 0 • 0 _0

o

n_ _0 0 0 _ _ 0 0 3 _ ° j 3.

I I n l 0 ,_" Q P- I _" N I _- ,0

3 _ _ • _

I I

h

0 ,0 d u_

o

,-. _ _. .-I N ¢_0 N" __ 0 _ ,-4 I I

_o _0

0 _a0 _... O O t_.- ao _-_ 0 .-e OCY_O • *o eO • _0_0 • e.-_ a00 i ° I" i ° + 0 0 oO

_--q_ o_

o0aD ,-., ID, O' ,0 if- t_ O" *O e_J 0.-_ • U'_O _0 , er_ ,-40 I I I* I I ÷ 0_0 _ .-4 *0 OC_ • O _0 0_-4 J_ .'-40 e_ I I I I ÷ 0 .4"

o _

t_u _, co_O_.

_00 _ _ _1" .4- r,.I t-- u', _0_ ."4 0 O *o • O'*O e_O _0 * ,-'O I ! I I o_

o ®_o

,.no a0._ _ o _0_ eO _-oo e_ 0 • ,,I"0 * • -e • r_ ! I I I I" C_ _o _0_ o _ _.

_0 0"0 -00 _0 eO • _eee_ I I l

o ÷

o', _0 •,'l- ao ._ O _, o0 o, _o_ ._ u", O O ",t ,,too ,,I"0 • • i0u_ t i °

÷ jo

a0_O 0_ 0_0 0 ,0 ee_ I I jO oN_ _.o. o _.

_ el%l _0 ._ ! I I I •,:r o a_ _o_ • O *O ,0_ O_ *N • I I I ! I ! I o w ZZ Z Z ÷

_o

0 u'_ (I) O_NO0 CP.-_ O" -:r .,f 0_0 • o0@@ .0 0 • ,_ 0o,_ ,4" ¢_1 (xl NO e_ I I I • I l l I ÷ _.'nO NO0 _0_ _0_ Q,. ._ , I_', r.,- r, NI _o_ wDO 0 ,_) •

O_ ._ ._

,0 ,0,_0 0.--_ 01',_ cOO NI"@ _0_ I !

I I I .IF o

_o_

u_100 IN. o, o ..i .-I 0"0" 00"0 0_, 0 ,0 00,_ °0 00_ ..-.i , ,.-4 ;_0 ! I • I I ! I .I.

o 0 (_.-i i_.

, Lira I_ 0 "0 oo ,h- • .wD,O er_ • • NOe._ • -4 (_w i,g • I I I I I I o 0 NWD(_ _ _0_ w0 • o • 0,0 .-i 0 • • o _.-I "_ 0 (_ _ • ! I I I I I I o-oo _0_ 0¢0 o0_ • 0 • • leo_ ,ONe; tn lu_

i

I I I I I 0". erlc}

_o °

,0 _ N r-

•._ _ ,00 . r,,I _t _l"

e,,-_ O0 ,_ _.. _3

r_ 0 f,_ f, rl • I I I ! I I I .-_o

°

0 .0 ;-. ° • ,o o rxl ,_D • I • I I I !

o ON _

_no

_0 ('_ ,0 P- P" 0_ ,.-4 .000

b_K_

• ,?, ,I. -_

O_ °_ _i" o i'_i rm _i ,,-a .,._- • I I I I I I !

_r ell ii_ ;',.O' F.- _J_ i_ .,l" (.J w0 o _ ,l) ,-_ e,l r,_ ,,_ ,0 r'-

,g r:, "i. _

o_ 0 00 • 00_0 • ,0,0" ,0 ,-a_ • O-a .(X; t{% 0 • • I" . I • I I ! ! g I I w _N O_ I.)

_N_ w ZZ Z 0 oom _0___

• ._, _ e o_

o _ o _- 0, ,o m r- o o0 . .t ._

• • ,_ , - - _, , o _, • _, I ,4 0 O"

o o, _

• • O, 0 • • o ,o N n,l ,-_ ,O ,,.4- ,O U'_ ,4" -,1" I_ o _- _.

• • O" 0 • 0 ,0 • 0] 0 _ _ _ _1 _ t_ u_ u'_ ,0 N 0" ,0 _ o _ I o ,-_ ,_- m _ o 0'_ • .-_ ..'_ 0 e_

o ,.- o, _ .o 0, _ " _ o

3-

H CH D3 H O O3

o _. _-

_- _ o . _.

Pq O _ _ O I _- I_ I'_ ,,I- _ r- _ _ O I 0 0 _q n,i NoD h. O_ 0 _ _ _

_ o _ _ I • . • .,- _ o _ _

I I',- 0 r'- r_- _I _o _.. fM o o i_ ,,,I_ I_, I ILl UJ _ 0_.

U') v rf % j O. _ _ I O O O

F- 104A DATA SOURCES

Stabi? [ty and Control and Handling Qualities_ F-IO4A, Lockheed Rept.

No. LR 10794, 12 Dec. 1955

Andrews, William H., and Herman A. Rediess, Flight-Determined Sta-

bility and Control Derivatives of a Supersonic Airplane with a

Low Aspect-Ratio Unswept Wing and a Tee-Tail, NASA Memo 2-2-59H,

A!or. '1959

Performance t F-IO4D, Lockheed Rept. No. LR-12873, I May 1958

Flight Manualt F-IO4A and F-IO4B USAF Series Aircraft, T. O. IF-IO4A-I,

15 Dec. 1961

Technica ! Manual t Flight Controls t USAF Series F-IO4A and F-I04C

Aircraft, T. O. 1F-104A-2-8, 15 Mar. 1960

6O

SECTION IV

F-4C

F-_C BAC_DROUND

The F-4C is an Air Force tactical fighter whose primary mission is

all-weather air-to-air missile combat. Lateral control is achieved by

ailerons in combination with spoilers on a swept wing. A swept stabilator

provides longitudinal stability and control. Directional stability and

control is accomplished through a conventional fin-rudder combination.

Landing speed is reduced by full span leading edge flaps and inboard plain

trailing edge flaps in conjunction with blowing-type boundary layer control

(BLC). Boundary layer control is automatically induced when full flap

deflection occurs.

Features distinguishing the USAF F-4C from its Navy counterpart, the

F-4B, are:

• Lack of drooped ailerons with flaps down resulting in

higher landing speeds.

• Dual flight controls resulting in slightly increased

control system inertia.

• Wing bumps to house larger main gear wheels resulting

in a slight drag increase.

Data included here was obtained primarily from MAC Report No. 9842.

Special emphasis is placed on the longitudinal control system because of

its relative complexity when compared to other aircraft. Figure IV-4 has

been addqd to help illustrate this system. Also, care has been taken to

retain s_m% of the control system nomenclaure used by the manufacturer, e.g., qB and PBF (see Fig. IV-5).

The Stability Augmentation block diagrams are shown in Fig. IV-7. The

roll SAS described is not included in lateral directional SAS on transfer

functions since it is faded out with the lateral control stick out of neutral

position.

_p :d q-i O O ,--I

@

O

(9

O <.9 m o o

(9 o o

.p .,q ,m tl

oO

i-.-]

-i (i;, rs] [.., q_ O rH qd .rd 4g .r_ O C} d_ b4)

®

r--I

I I

o

I > H

Od

(b .r4 E ,-I r_ H .,-I 4--

q.- r-- _1"

o .o

II II II .Q IU

F-4C

PITCH AXIS

_SsAs (rad)

Feel System

I _ Gearing / Actuator

8s(rad)

18sT(in)_ _

.0569qePsF

+ .OI57qBPBF -*

FST(Ib__ _-_.0369s 2 +.208s

,:_1 I _'-_ I- _ -I°_'+'1

_-- See Fig and for feel system details

Bobweight

az ts---_- _) of JtB= 39.3 ft

ROLL AXIS

8OsAs (rad)

Feel Spring Gearing /

Sa(rad)

_;T,,_ -I 2"961 =1 _ i -_ Spoiler

-__ 8sp( ra d )

AR! Gain

CLEAN O ,/

PA ARI

C38r {-.46 SAS OFF

= _-.69 SAS ON

__r I___--

<_rAm(rod)

_-:1_

YAW AXIS 8rARl(rad) 3rsAs (rad)

\ / Rudder

Feel Spring Gearing \ / Flexure

.._j_'_ SPED (i n) .___.J__

8r(rad)

_"_°_'_ - I _ I _I _ I- _ - l""txl -

_-- See Fig

K mR G air

V<235KIAS 36.61b/in -11.5deg/in

V>220KIAS 8.51b/in -6.5deg/in

Figure IV-3. F-hC Control System

ID C O C °_ t_ .J_ C

E o

O _ t_

.c

S_

_o __

..Q "t_ O C ¢) O'_

Er0

c)

_O

0,; v t_ C O °_ D_ ,.i,.,.

O "- LL ,,i,.-.

"_ {I) ,-4

._ c

© .Q O O .I

rn C_

•-_ O

_L