APPENDIX - A : WEIGHT ESTIMATIOIi EQUATIONS
APPENDIX - A : WEIGHT ESTIMATIOIi EQUATIONS BY ’TORENBEEK’ The a i r p l a n e s t r u c t u r e w e i g h t , W s t r u c t w i l l be assu- med t o c o n s i s t of t h e f o l l o w i n g components: 5 . 1 Wing, Ww 5 . 2 Empennage, W emP 5 . 3 F u s e l a g e , Wf 5.4 Nacelles, Wn T h e r ef o r e : 5 . 5 Landing g e a r , W ( A . 1 )
+ W f + w n + w
‘struct = ww + w
emP 9 E q u a t i o n s f o r s t r u c t u r e w e i g h t e s t i m a t i o n a r e p r e s e n t e d f o r t h e f o l l o w i n g t y p e s of a i r p l a n e s : 1. General A v i a t i o n A i r p l a n e s 2. Commercial T r a n s p o r t Airplanes 1. Wing- Weight Estimation The f o l l o w i n g e q u a t i o n applies t o l i g h t t r a n s p o r t a i r p l a n e s w i t h take-off w e i g h t s below 1 2 , 5 0 0 lbs: ( A . 1.1) of new terms: b = wing s p a n i n f t = wing semi-chord sweep a n g l e
fl 1 / 2
tr = maximum t h i c k n e s s of wing r o o t chord i n f t A.1.2 The f o l l o w i n g e q u a t i o n a p p l i e s t o t r a n s p o r t a i r p l a n e s w i t h t a k e - o f f w e i g h t s above 12,500 lbs:
ww =
= 0 . 0 0 1 7 w E I Z F ( b / c o ~ ~ 1 , ~ ) 0 ~ 7 5 Cl + (6.3cos(A /b}1’21x ( A . 1 . 2 ) of new term = maximum z e r o f u e l w e i g h t = WTo - WF ( A . 1 . 3 ) wMZF S ~ e c i a l n o t e s : 1 . Equation (A. 1 * 2) includes the weight of normal h i g h lift d e v i c e s as w e l l as a i l e r o n s .
2 . For spoilers and speed brakes 2 p e r c e n t s h o u l d be added.
3. If t h e a i r p l a n e h a s 2 wing mounted e n g i n e s reduce t h e wing w e i g h t by 5 p e r c e n t .
4. If t h e a i r p l a n e h a s 4 wing mounted e n g i n e s reduce t h e wing w e i g h t by 1 0 p e r c e n t .
5 . I f t h e l a n d i n g gear is n o t mounted under t h e wing reduce t h e wing weight by 5 p e r c e n t .
6. For braced wings reduce t h e wing weight by 3 0 p e r c e n t . The r e s u l t i n g wing w e i g h t estimate does i n c l u d e t h e weight of t h e s t r u t . The l a t t e r is roughly 10 p e r c e n t of t h e wing weight.
7. For Fowler f l a p s add 2 p e r c e n t t o wing weight.
2. Empennage FJeight Estimation w i l l be e x p r e s s e d as f o l l o w s : Empennage w e i g h t , W emP
W = W h + w , + w c #
(A.2) emP where: wh = h o r i z o n t a l t a i l weight i n l b s Wv = v e r t i c a l t a i l w e i g h t i n l b s W , = c a n a r d weight i n l b s E q u a t i o n s f o r empennage weight components a r e p r e s e n t e d i n t h e remainder of t h i s s e c t i o n .
h.2.1 The f o l l o w i n g e q u a t i o n a p p l i e s t o l i g h t t r a n s p o r t a i r p l a n e s w i t h d e s i g n d i v e s p e e d s up t o 2 5 0 kts and w i t h c o n v e n t i o n a l t a i l c o n f i g u r a t i o n s : 2 0 . 7 5 (A.2.1) = O . O ~ I ~ , ~ ~ ( S ~ + s h ) 1 W B emP
-
1 , = d i s t . from wing -d/4 t o v e r t . t a i l cv/4 i n f t
Sr = r u d d e r area i n f t A v = v e r t i c a l t a i l t a p e r r a t i o A . 2 . 2 The f o l l o w i n g e q u a t i o n a p p l i e s t o t r a n s p o r t a i r p l a n e s - a n d t o b u s i n e s s jets w i t h d e s i g n d i v e speeds above 250 k t s .
wh = ( A . 2 . 2 ) where Kh takes on t h e f o l l o w i n g v a l u e s : Kh = 1 . 0 for f i x e d i n c i d e n c e s t a b i l i z e r s Kh = 1.1 f o r v a r i a b l e i n c i d e n c e s t a b i l i z e r s t u
-
( A . 2 . 3 )
wv. -
= KvSv[3. ~ ~ ~ ( s v ~ o ' 2 v ~ / ~ , ~ ~ ~ ( c o ~ 1 / z V ) l l 2 1 - 0 . 2 8 7 1
where K , takes on t h e f o l l o w i n g v a l u e s : K, = 1 . 0 f o r f u s e l a g e mounted h o r i z o n t a l t a i l s f o r f i n mounted h o r i z o n t a l t a i l s : Kv = (1 + o . 1 5 ( S h Z h / S v b v ) l ( A . 2 . 4 ) of new terms: VD = d e s i g n d i v e speed i n KEAS h o r i z o n t a l t a i l semi-chord sweep a n g l e 1 / 2 h v e r t i c a l t a i l semi-chord sweep a n g l e 1 / 2 v 3 . F u s e l a g e Weight E s t i m a t i o n A.3.1 The f o l l o w i n g e q u a t i o n a p p l i e s t o t r a n s p o r t a i r p l a n e s and t o b u s i n e s s j e t s w i t h d e s i g n d i v e s p e e d s above 2 5 0 k t s .
The c o n s t a n t Kf takes on t h e f o l l o w i n g v a l u e s : Kf = 1.08 f o r a p r e s s u r i z e d fuselage = 1.07 f o r a main gear attached t o t h e fuselage.
= 1.10 f o r a c a r g o a i r p l a n e w i t h a c a r g o f l o o r These effects are m u l t i p l i c a t i v e f o r a i r p l a n e s equipped w i t h a l l of t h e above.
of new terms: VD = d e s i g n d i v e s p e e d i n KEAS lh = d i s t a n c e from wing C / 4 t o hor. t a i l Gh/4 i n f t = f u s e l a g e gross s h e l l area i n f t s f g s 4 . Nacelle Weight Estimation The n a c e l l e weight is assumed t o c o n s i s t of t h e f o l l o w i n g components: 1. For podded e n g i n e s : t h e s t r u c t u r a l w e i g h t associated w i t h t h e e n g i n e e x t e r n a l d u c t s and or cowls.
Any p y l o n weight is i n c l u d e d .
2 . For p r o p e l l e r d r i v e n a i r p l a n e s : t h e s t r u c t u r a l weight associated w i t h t h e e n g i n e e x t e r n a l d u c t s and o r cowls p l u s t h e w e i g h t d u e t o t h e e n g i n e mounting trusses.
3. For b u r i e d e n g i n e s : t h e s t r u c t u r a l w e i g h t a s s o c i a t e d w i t h s p e c i a l cowling and o r d u c t i n g p r o v i s i o n s .
A.4.l W , = 2.S(PTO) 1 / 2 ( A . 4 . 1 ) T h i s weight i n c l u d e s t h e e n t i r e e n g i n e s e c t i o n forward of t h e f i r e w a l l .
t o n e n u i g e s : Wn = 0.32PT0 f o r h o r i z o n t a l l y opposed e n g i n e s ( A . 4 . 2 ) ( A . 4 . 3 ) 1 o.045(PTo) 5 / 4 for radial e n g i n e s ' n ( 7 i . 4 . 4 ) W , = 0.14(PT0) f o r t u r b o p r o p e n g i n e s 6 0 Notes: 1 . S i n c e PTo is t h e total required take-off horsepower, these weight estimates i n c l u d e t h e w e i g h t s of n a c e l l e s .
2. If t h e main l a n d i n g gear retracts i n t o t h e n a c e l l e s , add 0 . 0 4 l b s / h p t o the n a c e l l e w e i g h t 3. If t h e e n g i n e e x h a u s t s o v e r t h e wing, as i n t h e Lockheed Electra, add 0.11 l b s / h p to t h e n a c e l l e weight.
A . 4 . 2 For t W e t o r low b v v Wn = 0.055TT0 ( A . 4 . 5 ) Wn = 0 . 0 6 5 T T 0 ( A . 4 . 6 ) S i n c e TTO is t h e t o t a l required take-off t h r u s t , t h e s e e q u a t i o n s a c c o u n t for t h e weight of n a c e l l e s .
5 . Landing G e a r Weight E s t i m a t i o n A.5.1 The f o l l o w i n g e q u a t i o n a p p l i e s t o t r a n s p o r t a i r p l a n e s and t o b u s i n e s s j e t s w i t h the main g e a r mounted on t h e wing and t h e n o s e gear mounted on t h e f u s e l a g e : The factor K takes on t h e f o l l o w i n g v a l u e s : gr K = 1.0 for low wing a i r p l a n e s gr K = 1.08 for h i g h wing a i r p l a n e s qr 6 1 Airplane Gear Gear A D 9 9 comp .
Type Type - Jet Trainers Retr. Main 3 3 . 0 0.04 0.021 0.0 and Business Nose 1 2 . 0 0.06 0.0 0.0 Jets Other c i v i l Fixed 0.10 Main 2 0 . 0 0.019 0.0 airplanes Nose 2 5 . 0 0.0 0.0024 0 . 0 T a i l 9 0.0 0.0024 0.0 0.16 Retr. Main 4 0 . 0 0.019 1 . 5 x 1 0 : ; Nose 2 0 . 0 0.10 0 . 0 2.0xlO T a i l 5 . 0 0.0 0.0031 0.0 6 2
APPENDIX B
APPENDIX B Program Listing f o r "Torenbeek" Method of Aircraft Component Weight Estimation C THIS PROGRAM IS BASED ONTORENBEEK'S EQUATIONS FOR WEIGHT C PREDICTION FOR CONVENTIONAL METAL AIRCRAFT C C WRITTEN BY RICHARD D. ROE C BOEING MILITARY AIRPLANE CO.
C (316) 526-7336 C MODIFIED BY JIM RITTER, FEBRo 1986 C THE WICHITA STATE UNIVERSITY C (316) 689-3410 C C C B WING SPAN IN FEET C BF WIDTH OF FUSELAGE IN FEET C BS STRUCTURAL WING SPAN IN FEET C ESHP ENGINE SHIP HORSEPOWER C HF DEPTH OF FUSELAGE IN FEET C LAMDA WING SWEEP ANGLE IN DEGREES LAMH C HORIZONTAL TAIL SWEEP ANGLE IN DEGREES C LAMV VERTICAL TAIL SWEEP ANGLE IN DEGREES C NULT ULTIMATE LOAD FACTOR C PTO BLOWER HORSEPOWER PER ENGINE C WING AREA IN SQUARE FEET S C SH HORIZONTAL TAIL AREA IN SQUARE FEET C SG TOTAL SURFACE AREA OF FUSELAGE C
sv VERTICAL TAIL AREA IN SQUARE FEET
C TR TAPER RATIO C TTO TAKEOFF TORQUE C VD DESIGN DIVE SPEED C WF WEIGHT OF FUSELAGE IN LBS C WGROSS MAXIMUM TAKEOFF WEIGHT C WHOR WEIGHT OF HORIZONTAL TAIL C WMAIN WEIGHT OF MAIN LANDING GEAR C WNAC WEIGHT OF NACELLE IN LBS C WNOSE WEIGHT OF NOSE LANDING GEAR IN LBS
C wsc WEIGHT OF SURFACE CONTROL GROUP IN LBS
C WTAIL WEIGHT OF TAIL LANDING GEAR IN LBS C WVERT WEIGHT OF VERTICAL TAIL IN LBS C WW8 WEIGHT OF WING IN LBS C C C C C WING WEIGHT C LOGICAL"1 TITLE (60) REAL LAMDA,KW,NULT,LAMH,KH,LAMV,KWF,KUC,KSC,KV,LT, &KW6,KW7,KW8,KW9,KFl,KF2,KF3,KF4 DATA NW6/0/,NW7/0/,NW8/0/,NW9/0/,NF1/0/,NF2/0/,NF3/0/, ~KW6/~o/,KW7/1./,KW~/1./,KW9/l~/,KFl/l./,KF2/l~/,KF3/l./,KF4/1./ C 6 3 C IN THIS MODIFICATION, TWO FILES ARE CREATED, AN IN- C PUT FILE "NASA4IN DATA" AND AN OUTPUT FILE "NASA40UT LIST- C ING". AT THE FIRST STEP OF INTERACTION, IT IS POSSIBLE TO C CHOOSE THE PREVIOUSLY CREATED INPUT SET (NASA4IN) THUS BYPASSING C THE FOLLOWING PROCEDURE. THE ADVANTAGE IS IN TIME SAVED IF C IT IS DESIRABLE TO VARY ONLY A FEW PARAMETERS BETWEEN RUNS.
C THE OUTPUT SET (NASA40UT) IS ALWAYS RECREATED.
C LLLL=l WRITE(6,398)
398 FORMAT ( ' IF INTERACTIVE PROCEDURE NOT REQUIRED, ENTER "2" '
*/,2x, 'AND PROGRAM w m READ FROM A PREVIOUSLY CREATED INPUT L I ~ T ~ , */,2X,'"NASA4IN LISTING". IF INTERACTIVE PROCEDURE IS DESIRED, I , */,2X,'ENTER "1" AND NASA4IN LISTING WILL BE CREATED ANEW.') READ (5, * ) LLLL IF(LLLL.EQ.1)GO TO 4 READ(4,400)TITLE,WGROSS,B,LAMDA,S,NULT,TR,NI, *NW6,NW7,NW8,NW9,BH,SH,VD,LAMH,BV,SV,LAMV,N6,SG,~F,BF,LT, *NFltNF2,NF3,N3,NN,N2,KLG,KSC,N5,PT0 C WRITE(4,400)TITLE,WGROSS,B,LAMDA,S,NULT,TR,NI, C *NW6,NW7,NW8,NWgIBH,SH,VD,LAMH,BV,~,LAMV,N6,SG,HF,BF,LT, C *NFltNF2,NF3,N3,NN,N2,KLG,KSC,N5,PT0 400 FORMAT(60A1/,6(F12.4/) ,5(1lX,Il/) ,7(F12.4/) ,llX,Il/, *4 (F12.4/) ,7 (llX, I1/) ,F12.4/,11X, 11/,F12.4) KW=.0017 IF(WGROSS.GE.12500.)KW=.00125 IF(NI.EQ.O)F1=1.0 IF (NI.EQ. 1) F1=. 95 IF (NI.EQ. 2)F1=.90
KV=1 . 0
IF (N6.EQ.2)KV=(SH*BH/S/BV)*.15+1.0
KUC=1 . 0
IF (N3. NE. 1) KUC=l . 08
IF (NN. EQ. 1) WMAIN=KUC* (3 3. + . 04*WGROSS**. 75+. 021*WGROSS)
IF (NN.EQ. 1) WNOSE=KUC* (12. + . 06*WGROSS**.75)
IF (NN.EQ . 1) WTAIL=0 .
IF (N2.EQ. 1) WMAIN=KUC* (20 .+. l*WGROSS**. 75+. 019*WGROSS)
IF (N2 . EQ. 1) WNOSE=KUC* (25. + . 0024*WGROSS)
IF (N2. EQ. 1) WTAIL=KUC* (9 . + . 0024*WGROSS)
IF(N2.EQ.2)WMAIN~KUC*(40~+.16*WGROSS**.75+.019*WGROSS+l.5E-5 **WGROSS**l. 5) IF(N2.EQ.2)WNOSE=KUC*(20.+.l*WGROSS**.75~2.E-6*WGROSS**l.5)
IF (N2.EQ. 2)WTAIL=KUC* (5 .+. 0031"WGROSS)
IF (N5 . EQ. 1) WNAC=2.5* (PTO) ** .5
IF (N5 . EQ. 2)WNAC= . 045*PTO** 1.25
IF(N5.EQ.3)WNAC=.14*PTO IF (N5.EQ. 4 ) WNAC= .055*PTO
IF (N5 . EQ .5) WNAC= .065*PTO
IF(NW6.EQ,l)KW6 = 1.02 IF(NW7.EQ.l)KW7 = .95 IF(NW8.EQ01)KW8 = .70 IF(NW9.EQ.l)KW9 = 1.02 IF(NFl.EQ.1)KFl = 1.08 IF(NF2.EQ01)KF2 = 1.07 IF(NF3.EQ.l)KF3 = 1.10 6 4 IF(NW7.EQ.l)KF4 = 1.04 IF(LLLL.EQ.2)GO TO 301 4 WRITE(6,135) 135 FORMAT(' INPUT TITLE FOR OUTPUT UP TO 60 CHARACTERS') READ(5,50) (TITLE(KKK),KKK=1,60) WRITE(4,51) (TITLE(KKK),KKK=1,60) 50 FORMAT(60Al) 5 1 FORMAT ( 2X, 6 0Al) WRITE(6,100) 108 FORMAT(' INPUT MAXIMUM TAKEOFF WEIGHT')
READ (5, * ) WGROSS
WRITE (4, * ) WGROSS
WRITE(6,lBl) 181 FORMAT(' INPUT WING SPAN IN FEET') READ (5, * ) B
WRITE (4, * ) B
WRITE(6,102) 102 FORMAT(' INPUT WING SWEEP ANGLE IN DEGREES') READ (5, * ) LAMDA
WRITE (4, * ) LAMDA
WRITE(6,103) 103 FORMAT ( ' INPUT WING AREA IN SQUARE FEET')
READ (5, * ) S
WRITE ( 4 , * ) S IF(WGROSS.GE.12500.) GO TO 200 KW=. 0017 GO TO 201 200 KWz.00125 CONTINUE WRITE(6,114) FORMAT(' INPUT THE ULTIMATE LOAD FACTOR')
READ ( 5 , * ) NULT
WRITE (4, * ) NULT WRITE(6,123) FORMAT(' INPUT TAPER RATIO') READ(5,*)TR WRITE(4,*)TR WRITE(6,151) 151 FORMAT(' INPUT NUMBER OF ENGINES ON EACH WING 0,1,2') READ (5, * ) NI WRITE (4, * ) NI NP=NI+l GOT0(152,153,154) ,NP 152 Fl=l.0 GO TO 155 153 F1=.95 GO TO 155 154 F1=.90 155 CONTINUE WRITE(6,506) 506 FORMAT(' IF SPOILERS OR SPEEDBRAKES ARE INCLUDED, ENTER l.'/, & ' OTHERWISE, ENTER 0.') READ(5,*)NW6 606 IF(NW6.EQ.l)KW6=1.02
WRITE (4 , * ) N W 6
6 5 WRITE(6,507) 507 FORMAT(' IF MAIN LANDING GEAR IS FUSELAGE-MOUNTED, ENTER lo'/, & ' OTHERWISE, ENTER 0.') READ(5,*)NW7 60 7 IF (NW7.EQ. 1 ) KW7=. 9 5 WRITE (4, * ) NW7 WRITE(6,508) 508 FORMAT(' THE WING IS STRUT-BRACED, ENTER 1. OTHERWISE ENTER 0 . ' / , & ' (WING WEIGHT WILL NOT INCLUDE STRUT WEIGHT.) ' ) READ(5,*)NW8 608 IF (NW8. EQ. 1) KW8=. 70 WRITE(4,*)NW8 WRITE(6,509) 509 FORMAT(' IF FOWLER FLAPS ARE USED, ENTER l.'/, & ' OTHERWISE, ENTER 0 . ' ) READ (5, * ) N W 9 609 IF (NW9.EQ. 1) KW9=1.02
WRITE (4, * ) NW9
301 BREF=6.25 BS=B/COS(.017453*LAMDA/2) AA=(BREF/BS)**.5+1
AB= (BS*S/WGROSS/TR) ** . 3
WW8=(WGROSS*KW*BS**.75*AA*NULT**.55*AB)*Fl*KW6*KW7*KW8*KW9 IF(LLLL.EQ.2)GO TO 302 c---------------------------------------------------------------------- C C TAIL GROUP C WRITE (6,104) 104 FORMAT(' INPUT HORIZONTAL TAIL SPAN IN FEET') READ (5, * ) BH WRITE ( 4 , * ) BH WRITE (6,105) 105 FORMAT(' INPUT HORIZONTAL TAIL AREA IN SQUARE FEET')
READ ( 5, * ) SH
WRITE(4,*)SH WRITE(6,106) 106 FORMAT(' INPUT DESIGN DIVE SPEED IN KNOTS') READ (5, *)VD
WRITE (4, * )VD
WRITE (6,107 ) 107 FORMAT(' INPUT HORIZONTAL TAIL SWEEP ANGLE IN DEGREES') READ (5, *) LAMH WRITE (4, * ) LAMH 302 KH=1.0 C C HORIZONTAL TAIL WEIGHT C AC=SH**.2*VD/(COS(LAMH*.017453))**.5/1000.
WHOR=SH*KH*(3.5*AC-.2) IF(LLLL.EQ.2)GO TO 303 WRITE(6,108) 108 FORMAT(' INPUT VERTICAL TAIL SPAN') READ (5, * ) BV WRITE(4,*)BV 6 6 WRITE(6,109) 109 FORMAT(' INPUT VERTICAL TAIL AREA IN SQUARE FEET') READ ( 5 , * ) SV WRITE(4,")SV WRITE(6,llB) 110 FORMAT(' INPUT VERTICAL TAIL SWEEP ANGLE IN DEGREES')
READ (5, * ) LAMV
WRITE ( 4 , * ) LAMV
WRITE(6,133) 133 FORMAT(' INPUT' ,/,20X, '1 FOR FUSELAGE MOUNTED TAILPLANE' $ ,/,28X,'2 FOR FIN MOUNTED TAILPLANE')
READ ( 5, * ) N6
WRITE (4, * ) N6
GOT0 (213,214 ) , N6
213 KV=l . 0
GO TO 215 214 KV=(SH*BH/SV/BV)*.15+1.0 215 CONTINUE c .
C VERTICAL TAIL WEIGHT C 303 AD=SV**.2*VD/(COS(LAMV*.017453))**,5/1000.
WVERT=SV*KV* ( 3.5*AD-. 2) IF(LLLL.EQ.2)GO TO 304 c---------------------------------------------------------------------- C C BODY GROUP C WRITE (6,111) 111 FORMAT(' INPUT TOTAL SHELL AREA IN SQUARE FEET') READ (5, * ) SG WRITE (4, * ) SG WRITE (6,112) 112 FORMAT(' INPUT DEPTH OF FUSELAGE IN FEET') READ (5, *) HF WRITE(4,*)HF WRITE (6,113) 113 FORMAT(' INPUT WIDTH OF FUSELAGE IN FEET') READ ( 5 , * ) BF WRITE (4, *) BF WRITE (6,134) 134 FORMAT(' INPUT WING 1/4 MAC TO TAIL 1/4 MAC IN FEET') READ ( 5 , * ) LT WRITE(4,*)LT WRITE(6,701) 701 FORMAT(' IF THE FUSELAGE IS PRESSURIZED, ENTER l.'/, & ' OTHERWISE, ENTER 0. ' )
READ (5, * ) NF1
801 IF(NFl.EQ.l)KF1=1.08 WRITE ( 4 , * ) NF1 WRITE ( 6,702 ) 702 FORMAT(' IF ENGINES ARE REAR-MOUNTED ON THE FUSELAGE, ENTER l . ' / , & ' OTHERWISE, ENTER 0. ' )
READ ( 5, * ) NF2
802 IF(NF2.EQ01)KF2=1.04 6 7 WRITE (4, * ) NF2 WRITE (6,703) 703 FORMAT(' IS THE AIRPLANE A CARGO AIRPLANE WITH A CARGO FLOOR?', 6' ENTER lo'/,' OTHERWISE, ENTER 0.') READ(5,*)NF3
803 IF (NF3. EQ. 1) KF3=1 . 10
WRITE (4, * ) NF3 IF (NW7. EQ. 1)KF4=1.07 C C (Nw7 REPRESENTS THE STATE OF MAIN GEAR ATTACHMENT. THE QUESTION HAS C BEEN ASKED IN THE WING SECTION, THE INFORMATION IS AGAIN USED HERE.)
C 304 KWFr.021 WF=(KWF* (VD*LT/(BF+HF))**.5*SG**1.2) *KFl*RF2*KF3*KF4 IF(LLLL.EQ.2)GO TO 305 c---------------------------------------------------------------------- C C ALIGHTING GEAR C WRITE (6,117) 117 FORMAT(' INPUTV,/,20X,'1 FOR LOW WING AIRCRAFT1,/,20X,'2 FOR I , &'ALL OTHERS')
READ (5, * ) N3
WRITE (4, * ) N3 IF(N3.NE.1) GO TO 205 KUC=l .
GO TO 206 205 KUC=1.08 206 CONTINUE WRITE(6,115) 115 FORMAT(' INPUTg,/,20X,'1 FOR JET TRAINERS AND EXECUTIVE ', $'AIRCRAFT',/,20X,'2 FOR ALL OTHER CIVIL AIRCRAFT',/,lBX, $'(A CHOICE OF "1" WILL ASSUME A RETRACTABLE, NOSE GEAR AIRPLANE)') READ ( 5 , * ) NN WRITE ( 4 , * ) NN IF(NN.NE.1) GO TO 202 WMAIN=KUC*(33.+.04*WGROSS**.75+.021*WGROSS) WNOSE=KUC*(12.+.06*WGROSS**.75) N2=0 WRITE ( 4 , * ) N2 KLG = 1 GO TO 505 202 WRITE(6,116) 116 FORMAT(' INPUT',/,20X,'l FOR FIXED LANDING GEAR',/,20X,'2 FOR', $ ' RETRACTABLE LANDING GEAR') READ(5,*)N2 WRITE (4, * ) N2 IF(N2.NE.l) GO TO 204 WMAIN=KUC*(20.+.1*WGROSS**.75+.019*WGROSS) WNOSE=KUC* (25.+.0024*WGROSS) WTAIL=KUC* (9.+.0024*WGROSS) GO TO 203 WMAIN~KUC*(40.+.L6*WGROSS**.75+.019*WGROSS+l.5E-5*WGROSS**l.5) WNOSE=KUC*(20.+.l*WGROSS**.75+2.E-6*WGROSS**l.5) WTAIL=KUC*(5.+.0031*WGROSS) 6 8 C C SURFACE CONTROL GROUP C WRITE (6,118 ) 118 FORMAT(' INPUT KSC',/,20X,'KSC=.23 FOR LIGHT AIRCRAFT WITHOUT I , $'DUPLICATE C0NTROLSq,/,20X,'KSC=.44 FOR TRANSPORT AIRCRAFT AND I , $'TRAINERS, MANUAL CONTROLSf,/,20X,'KSC=.64 FOR TRANSPORT I , $'AIRCRAFT WITH POWERED CONTROLS AND1,/,28X,'TRAILING EDGE ', $'HIGH LIFT DEVICES') READ ( 5 , * ) KSC WRITE (4,*)KSC C C NACELLE GROUP C WRITE (6,119 ) 119 FORMAT(' INPUT ',/,20X,'1 FOR LIGHT AIRCRAFT1,/,20X,'2 FOR I , S'MULTI ENGINE RECIPROCATING',/,20X,'3 FOR TURBOPROP AIRCRAFT', $/,20X,'4 FOR TURBOJET OF TURBOFAN AIRCRAFT1,/,20X,'S FOR ', $'HIGH BYPASS TURBOFANS')
READ (5, * ) N5
WRITE (4, * ) N5 GOT0(207,208,209,210,21l),N5 C C LIGHT AIRCRAFT C 207 WRITE(6,120)
120 FORMAT( ' INPUT BHP PER ENGINE')
READ (5, * ) PTO
WRITE ( 4 , *) PTO WNAC=2.5* (PTO)**.5 GO TO 212 C C MULTIPLE RECIPROCATING ENGINES AIRCRAFT C 208 WRITE(6,120) READ ( 5 , * ) PTO WRITE ( 4 , * ) PTO
WNAC= . 0 45*PTO** 1 .25
GO TO 212 C C TURBOPROP C 209 WRITE (6,121) 121 FORMAT(' INPUT ENGINE SHIP HORSEPOWER AT TAKEOFF') READ ( 5 ,*) ESHP 6 9 WRITE(4,*)ESHP WNAC=. 14*ESHP GO TO 212 C C TURBOJET OR TURBOFAN C 210 WRITE(6,122) 122 FORMAT(' INPUT TAKEOFF TORQUE') READ (5, * ) TTO
WRITE (4, * ) TTO
WNAC=.055*TTO GO TO 212 C C HIGH BYPASS TURBOFANS 211 WRITE(6,122) READ (5, * ) TTO WRITE (4,*)TTO WNAC=.065*TTO 212 CONTINUE 306 WRITE(6,136) TITLE WRITE(7,136) TITLE 136 FORMAT(SX, (40A1)) WRITE (6,124) WW8 WRITE (7,124) WW8 124 FORMAT(' THE WING WEIGHT=',F15.4) WRITE (6,125) WHOR WRITE (7,125) WHOR 125 FORMAT( / , I THE HORIZONTAL TAIL WEIGHT =',F15.4) WRITE (6,126) WVERT WRITE(7,126)WVERT 126 FORMAT( / , I THE VERTICAL TAIL WEIGHT=',F15.4) WRITE(6,127)WF WRITE (7,127) WF 127 FORMAT( / , I THE FUSELAGE WEIGHT =',F15.4) WRITE ( 6,128 ) WMAIN WRITE (7,128 ) WMAIN 128 FORMAT( / , I THE MAIN LANDING GEAR WEIGHT=',F15.4) IF (KLG. EQ. 1)WRITE (6,129)WNOSE IF (KLG.EQ. 1) WRITE (7,129) WNOSE 129 FORMAT( / , I THE NOSE LANDING GEAR WEIGHT=',FlS.I)
IF (KLG . EQ. 2)WRITE (6,130) WTAIL
IF (KLG.EQ.2)WRITE(7,130)WTAIL 130 FORMAT( / , I THE TAIL LANDING GEAR WEIGHT=',F15.4) WRITE(6,131)WSC WRITE (7,131) WSC 131 FORMAT( /,' THE SURFACE CONTROL WEIGHT=',F15.4) WRITE (6,132) WNAC WRITE(7,132)WNAC 132 FORMAT( / , I THE NACELLE WEIGHT=',F15.4) STOP END 7 0 A P P E N 3 I X C . W S U Weight Estimation P r o g r a m s .
GENREG FORTRAN C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C * THE FOLLOWING PROGRAM IS A GENERAL REGRESSION *
C * ANALYSIS PROGRAM. THE 'Yr VALUES (ACTUAL WTS. *
C * ON WHICH THE REGRESSION IS BASED) ARE READ IN *
C * BELOW. THE 'X' AND 'Z' VALUES ARE DETERMINED *
C * BY SUBROUTINES AT THE END OF THE LISTING. THE *
C * REGRESSION IS DONE TWICE, ONCE IN LINEAR FOR- *
C * MAT AND ONCE IN NATURAL LOG FORMAT FOR THE *
C * PURPOSE OF COMPRESSING THE DATA. THE MATRICES *
C * ARE DETERMINED AND PRINTED, AND THEN SOLVED *
C * SIMULTANEOUSLY BY IBM LIBRARY SUBROUTINE TO *
C * TO DETERMINE THE COEFFICIENTS. FINALLY, THE *
C * ORIGINAL 'XI AND 'Z' VALUES ARE USED WITH THE *
C * NEW COEFFICIENTS TO COMPUTE VALUES OF 'Y' AND *
C * THESE NEW VALUES ARE COMPARED WITH THE ACTUAL *
C * VALUES, NORMALIZED, AND STATISTICALLY EVALUATED. *
C * *
C * THIS PROGRAM IS EXECUTED BY USE OF EXEC "GENREX". *
C * *
C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C ' REAL N(20) ,LF(20) ,LAMDA(20) ,LAMDAT(20) ,LAMDAV(20) ,LNX,LNY,LNZ DIMENSION A1(20),A2(20) rGW(20) ,WW(2O),RHO(2O),FW(2O),FS(2O), &BW(20) ,SW(20) rCR(20) rCT(20) rTR(20) rTT(20) pX(20) rY(20) ,2(2O) &RHOP(20) ,RHOR(20) ,ER(20) ,FF (20) ,BF (20),FWTACT(20) ,RHOT(20) DIMENSION BT(20) IST(20) rCRT(20) rCTT(20) rTRT(20) pTTT(20) ,YCAV(20), kHWTACT(20) rRHOV(20) rFV(20) rFVS(20),BV(2O) ,SV(2O) rCRV(2O) ,CTV(20) &TRV(20) ITTV(20) ,VWTACT(20) ,A(3,3) rB(3) rYCAL(20) IYTOT(20) ,YCCC(20) &YNORM(20),FT(2O),FTS(20) ,YYCAL(20),YY(20) ,WGS(20) ,WGS2(20),AGW(20) C C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C * THE FOLLOWING DATA IS READ FROM FILE # 4 , CALLED *
C * 'GENDAT DATA'. IT REPRESENTS WEIGHTS, MATERIAL *
C * PROPERTIES, AND GEOMETRIES OF THE AIRPLANES IN- *
C * TENDED FOR THE REGRESSION. *
C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
c READ (4,l) NCASE READ ( 4 , 2 ) (A1 (I),A2 (I),GW (I) ,WW (I),FWTACT(I),HWTACT (I), &VWTACT(I),N(I),I=l,NCASE) READ(4,3) (RHO(I),RHOP(I) ,RHOR(I) ,ER(I) ,RHOT(I) ,RHOV(I), &I=l,NCASE) READ(4,3) (FW(I),FS(I),FT(I),FTS(I),FV(I) ,FVS(I),I=l,NCASE) READ(4,3) (BW(1),SW(I)rBT(1) ,ST(I) ,BV(I) ,SV(I) ,I=l,NCASE) READ (4,3) (BF (I),LF (I),FF (I),LAMDA (I),LAMDAT (I),LAMDAV (I), &I=l,NCASE) READ(4,3) (CR(I),CT(I),CRT(I),CTT(I),CRV(I)~CTV(I)~I~l~NCASE) READ(4,3) (TR(1) gTT(1) fTRT(1),TTT(I) rTRV(1) ,TTV(I) ,1=1,NCASE) DO 6 I = 1,NCASE 6 ER(I)=ER(I) * 1000000.
7 1 C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C
* THE FOLLOWING SUBROUTINES ARE SEQUENTIALLY *
C
* CALLED FOR THE PURPOSE OF DETERMINING 'XI AND *
C
* 'Z' FROM THE APPROPRIATE DATA. THE SUBROUTINE *
C
* EQUATIONS ARE IN NON-DIMENSIONAL FORM; 'X', 'Y', *
C
C * AND 'Z' HAVE BEEN MADE NON-DIMENSIONAL BY DIVIDING *
* ACTUAL WEIGHT OF EACH COMPONENT BY THE AIRPLANE *
C
* GROSS WEIGHT. *
C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C C DO 108 L = 1,4 IF(L.EQ.1)CALL WING(NCASE,GW,WW,N,RHO,FW,FS,LAMDA,BW,SW,CR,CT, &TR,TT,X,Y, Z ) IF(L.EQ.2)CALL FUSLGE(NCASE,GW,WW,N,RHOP,RHOR,ER,FF,LF,BF, &FWTACT,X,Y,Z) IF (L.EQ. 3 ) CALL HZTAIL (NCASE, GW,WW, N, RHOT,FT,FTS,LAMDAT,BT, SW, &ST,CRT,CTT,TRT,TTT,HWTACT,X,Y,Z) IF(L.EQ.4)CALL VTAIL(NCASE,GW,WW,N,RHOV,FV,FVS,LAMDAV,BV,SW, & SV, CRV CTV TRV TTV, INTACT,X Y Z )
C WRITE (7r23)(X(I),Y (I ) , Z (I) I=l,NCASE)
23 FORMAT(3F20.8) C
******************
C
* LINEAR VERSION *
C
******************
C C C INITIALIZE SUMMATION ROUTINE C SMX = X(1) SMX2 = X(1) * * 2 .
SMY = Y(1) SMZ = Z(1) SMZ2 = Z(1) ** 2.
SMXZ = X(1) * Z(1)
SMXY = X(l) * Y(1)
SMZY = Z(1) * Y(1)
C SUMMATION : C C DO 30 I = 2,NCASE
SMX = SMX + X(1)
SMX2 = SMX2 + X(1) * * 2.
SMY = SMY + Y(1)
SMZ = SMZ + Z(1)
SMZ2 = SMZ2 + Z(1) * * 2.
SMXZ = SMXZ + X(1) * Z(1)
SMXY = SMXY + X(1) * Y(1)
SMZY = SMZY + Z(1) * Y(1)
x2 = X(1) ** 2 .
22 = Z(1) ** 2 .
xz = X(1) * Z(1)
XY = X(1) * Y(1)
ZY = Z(1) * Y(1)
30 CONTINUE 7 2 C C DEFINE ' A ' AND 'B' MATRICES C A(1,l) = FLOAT(NCASE) A(1,2) = SMX A(l,3) = SMZ A(2,l) = SMX A(2,2) = SMX2 A(2,3) = SMXZ A(3,l) = S M Z A(3,3) = SMZ2 A(3,2) = SMXZ B(l) = SMY B(2) = SMXY B(3) = SMZY IF (L.EQ.1)WRITE (7196) IF (L. EQ. 2 ) WRITE (7,97)
IF (L . EQ . 3 ) WRITE ( 7,98 )
IF (L . EQ. 4)WRITE (7,9 9)
WRITE(7,lOO) (A(l,J),J=l,3),B(l), (A(2,J),J=1,3),B(2), &(A(3,J) rJ=113),B(3) CALL SIMQ ( A,B ,3,0 ) C
C A IS DESTROYED, B IS REPLACED BY X (A * X = B)
C WRITE(7,200)B C c . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C * THE FOLLOWING LOOPS DETERMINE AND INITIALIZE WING WEIGHT *
C * PER GROSS WEIGHT FACTORS FOR EACH CASE, LINEAR AND LOGR. *
c . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C WGSI = WW(1) / GW(1) DO 17 I = 2,NCASE
17 WGSI = WGSI + WW(1) / GW(1)
WGSI = WGSI / (FLOAT(NCASE)) IF (LoEQ 1 ) WRITE (9,110)NCASE,WGSI 110 FORMAT(2X,'ARPLNE WGS(1) YCAL(WGS) ACT. WW/GW ', &'YCAL(ACT. WW/GW) YCAL (AVG)'//,12X,' (AVERAGE WW/GW FOR',I3, & ' AIRPLANES IS' ,F7.4, I ) I / / / ) DO 18 I = 1,NCASE WGS(1) = WGSI WGS2 (I) = WGSI 18 AGW(1) = WW(1) / GW(1) EPS = .0001 IF(L.NE.1)GO TO 41 DO411 = 1,NCASE 38 CALL WINC(NCASE,WGS,M,RHO,FW,FS,LAMDA,BW,SW,CR,CT, &TR,TT,X,Z)
YCAL(1) = B(1) + B(2) * X(1) + B(3) * Z(1)
IF (YCAL(I) GT.WGS (I) ) WGS (I) = WGS (I) + (YCAL(I)-WGS (I) ) /2.
= WGS ( I ) -
IF (YCAL ( I ) . LT. WGS ( I ) ) WGS ( I )
(WGS ( I ) -YCAL ( I ) ) /2.
39 IF(ABS(WGS(1)-YCAL(1)) .GT.EPS)GO TO 38 CALL WINC (NCASE, WGS2,N,RHO,FW,FS,LAMDA,BW,SW,CR,CT,TR, TT, X, Z )
YCCC(1) = B(1) + B(2) * X ( 1 ) + B(3) * Z(1)
7 3
CALL WINC (NCASE AGW, N RHO,FW , FS LAMDA,BW,SW CR CT , TR, TT X Z )
YCAV(1) = B(1) + B(2) * X(1) + B(3) * Z(1)
WRITE (9,111) I,WGS (I ) YCAL ( I ) AGW (I ) YCAV (I ) ,YCCC (I ) 111 FORMAT(2X,I3,5F12.4/) 41 CONTINUE IF(L.EQ.1)GO TO 44 DO441 = 1,NCASE WGS,N,RHOP,RHOR,ER,FF,LF,BF, IF (LeEQ 2)CALL FUSLGC (NCASE, &X,Z) IF (Lo EQ. 3 ) CALL HZTAIC (NCASE, WGS,N,RHOT,FT,FTS,LAMDATFBT,SW, &ST,CRT,CTT,TRT,TTT,X,Z) IF(L.EQ.4)CALL VTAIC(NCASE,WGS,N,RHOV,FV,FVS,LAMDAV,BV,SW, &SV,CRV,CTV,TRV,TTV, X, Z )
YCAL(1) = B(l) + B(2) * X(1) + B(3) * Z(1)
44 CONTINUE WRITE (7,300) DO 71 I = 1,NCASE
YYCAL(1) = YCAL(1) * GW(1)
YY(1) = Y(1) * GW(1)
71 YNORM(1) = YYCAL(1) / YY(1) YMEAN = YNORM (1) DO 73 I = 2,NCASE
73 YMEAN = YMEAN + YNORM (I)
YMEAN = YMEAN / NCASE DELPR = (YMEAN - 1.) * 100.
S2 = (YNORM(1) - 1.) ** 2
DO 81 I = 2,NCASE
81 = S2 + (YNORM(1) - 1.) * * 2
S2
S2 = S2 / (NCASE - 1)
SD = SQRT(S2) * 100.
YYCAL ( I ) YNORM ( I ) I=l,NCASE) WRITE ( 7,4 0 0 ) (A1 ( I ) A2 ( I ) YY ( I )
WRITE ( 7,4 0 4 ) YMEAN,DELPR , S2, SD
C C * * * * * * * * * * * e * * * * * * * * * * * C
C * LOGARYTHMIC VERSION *
. . . . . . . . . . . . . . . . . . . . . . .
C C C INITIALIZE SUMMATION ROUTINE C SMX = ALOG(X(1)) SMY = ALoG(Y(1)) SMZ = ALOG(Z(1))
SMX2 = SMX * SMX
SMZ2 = SMZ * SMZ
SMXZ = SMX * SMZ
SMXY = SMX * SMY
SMZY = SMZ * SMY
C C SUMMATION: C DO 31 I = 2,NCASE LNX = ALOG(X(1)) LNY = ALOG(Y(1)) LNZ = ALOG(Z(1)) 7 4
X2 = LNX * LNX
22 = LNZ * LNZ
XZ = LNX * LNZ
XY = LNX * LNY
ZY = LNZ * LNY
SMX = SMX + LNX
SMY = SMY + LNY
SMZ = SMZ + LNZ
SMX2 = SMX2 f X2
SMZ2 = SMZ2 + 22
SMXZ = SMXZ + XZ
SMXY = SMXY + XY
SMZY = SMZY + ZY
31 CONTINUE C C DEFINE 'A' AND 'B' MATRICES C A(I,1) = FLOAT(NCASE) A(lr2) = SMX A(2,l) = SMX A(2,2) = SMX2 B(1) = SMY A(lr3) = SMZ A(3,l) = SMZ A(3,3) = SMZ2 A(2,3) = SMXZ = SMXZ A(3r2) B(2) = SMXY B(3) = SMZY IF (L EQ 1 ) WRITE (6,19 6 ) IF (Lo EQ. 1) WRITE (7,196) IF (L. EQ - 2 ) WRITE (6,197 )
IF (L . EQ. 2)WRITE ( 7,197)
IF (L.EQ. 3)WRITE (6,198) IF (L.EQ. 3)WRITE ( 7,198)
IF (L. EQ . 4 ) WRITE (6,19 9)
IF (L.EQ. 4) WRITE (7,19 9) WRITE(7,lOl) (A(l,J),J=1,3),B(l), (A(2,J),J=1,3),B(2), *(A(3,J) rJ=lr3)rB(3) CALL SIMQ (A, B ,3,0 ) C C
A IS DESTROYED, B IS REPLACED BY X (A * X = B)
C B(1) = EXP(B(1)) WRITE (7,201) B IF(L.NE.1)GO TO 51 DO511 = 1,NCASE 4 8 CALL WINC(NCASE,WGS2,N,RHO,FW,FS,LAMDA,BW,SW,CR,CT, tTR,TT,X,Z)
YCAL(1) = B(1) * X(1) * * B(2) * Z(1) ** B(3)
IF (YCAL(I).GT.WGS2 (I))WGS2 (I) = WGS2 (I) + (YCAL(I)-WGS2 (I)) / 2 .
= WGS2 ( I ) -
IF (YCAL ( I ) . LT. WGS2 ( I ) ) WGS2 ( I )
(WGS2 ( I ) -YCAL ( I ) ) /2 .
49 IF(ABS(WGS2(I)-YCAL(I)) .GT.EPS)GO TO 48 51 CONTINUE IF(L.EQ.1)GO TO 54 7 5 DO541 = 1,NCASE IF(L.EQ.2)CALL FUSLGC(NCASErWGS2,N,RHOP,RHOR,ER,FF,LF,BF, &X,Z) IF(LoEQo3)CALL HZTAIC(NCASE,WGS2,N,RHOT,FT,FTS,LAMDAT,BT,SW,
&ST, CRT , CT TI TRT , TTT , X , Z )
IF (LoEQ. 4) CALL VTAIC (NCASE, WGS2, N, RHOV,FV,FVS,LAMDAV,BV, SW,
& I SV , CRV , CTV , TRV , TTV , XI Z )
YCAL(1) = B(1) * X(1) ** B(2) * Z(1) ** B(3)
54 CONTINUE WRITE(7,300) DO 75 I = 1,NCASE
YCAL(1) = YCAL(1) * GW(1)
Y(1) = Y(1) * GW(1)
75 YNORM(1) = YCAL(1) / Y(1) YMEAN = YNORM(1) DO 77 I = 2,NCASE 77 YMEAN = YMEAN + YNORM(1) YMEAN = YMEAN / NCASE DELPR = (YMEAN - 1.) * 100.
S2 = (YNORM(1) - 1.) ** 2
= 2,NCASE DO 83 I
83 S2 = S2 + (YNORM(1) - 1.) ** 2
S2 = S2 / (NCASE - 1)
SD = SQRT(S2) * 100.
WRITE(7,400) (Al(1),A2(I) ,Y (I) ;YCAL(I),YNORM(I) ,I=l,NCASE) WRITE (7,404) YMEAN,DELPR, S2, SD CONTINUE C C 1 FO M A T (8X,12) 2 FO M A T (2X, 2A4,6FlO 0) 3 FO M A T (1 OX,6F10.0 ) FO 3MAT('l'////,l5X,'REGRESSION VALUES FOR THE MAIN WING') 196 FO MAT( '1'////,15X, 'MAIN WING REGRESSION VALUES (CONT.) I ) FO WAT('l'////,l5X, 'REGRESSION VALUES FOR THE FUSELAGE') MAT( '1'////,15X, 'FUSELAGE REGRESSION VALUES (CONT.) ' ) 197 FO MAT('1'////,l5Xr 'REGRESSION VALUES FOR THE HORIZONTAL TAIL') 98 FO ?MAT( '1'////,15X, 'HZ. TAIL REGRESSION VALUES (CONT.) ' ) 198 FO WAT('l1////,l5X, 'REGRESSION VALUES FOR THE VERTICAL TAIL') 99 FO 199 FO ?MAT( 'l'////,lSX, 'VT. TAIL REGRESSION VALUES (CONT.) I ) FORMAT('01//,25X, 'THE LINEAR MATRICES'////,4X,3E12.4,9X, 'C1' , . . _ . .
* 9 X , E 1 2 . . 4 / , 4 X , 3 E l 2 . 4 , 4 X , '*',4X,'C2' ,4X,'=',4X,E12.4/,- *4X13E12.4,9X,'C3',9X,El2.4) 101 FOFtMAT('O'//,25X,'THE LOG MATRICES'////,4X,3E12.4,9X,'Cl', *9XIE12.4/,4X,3E12.4,4X,'*',4X,'C2',4X,'=',4X,El2.4/, *4X,3E12.4,9X,'C3',9X,E12.4) 200 FORMAT(///~OX,'Y = c1 + c2 * x + c3 * z :I//, *15X,'C1 = ',E14.6//,15X,'C2 = ',E14.6//,15X,'C3 = ',E14.6) 201 FORMAT(///~OX,'Y = ci * x * * c2 * z * * c3 :I//, *15X,'C1 = ',E14.6//,15X,'C2 = ',E14.6//,15X,'C3 = ',E14.6) 300 FORMAT('0'//,8X,' MODEL ACTUAL WEIGHT CALCULATED WE IGHT' , * I NORM I //) 400 FORMAT(11X,2A4,2X,F8.1,8X,F8.1,8X,F6.2) 404 FORMAT('0'//,5X,'MEAN:',F7.4,', DEL PRCT:',F5.2,'%, VARIANCE:', *F7.4,', STD. DEV.:',F7.2,'%') 7 6 S T O P END C C C SUBROUTINE WING(M,GW,WW,N,RHO,F,FS,LAMDA,BSPAN,SW,CR,CT,TR,TT, & X , Y , Z ) REAL G W ( 2 0 ) ,WW(20) , N ( 2 0 ) , R H 0 ( 2 0 ) , F ( 2 0 ) , F S ( 2 0 ) I &LAMDA(20) r B S P A N ( 2 0 ) r S W ( 2 0 ) r C R ( 2 O ) r C T ( 2 0 ) r T R ( 2 0 ) I T T ( 2 0 ) & X ( 2 0 ) r Y ( 2 O ) r Z ( 2 0 ) p A ( 2 0 ) t B ( 2 0 ) p D ( 2 0 ) DO 1 0 I = 1,M A ( 1 ) = R H O ( 1 ) / F ( 1 ) B ( 1 ) = R H O ( 1 ) / F S ( 1 ) D ( 1 ) = WW(1) / G W ( 1 )
X ( I ) = A ( 1 ) * N ( I ) * B S P A N ( 1 ) * S W ( 1 ) * ( 1 . - D ( 1 ) ) *
& ( C R ( 1 ) + 2. * C T ( I ) ) / ( ( C O S ( L A M D A ( I ) ) ) * * 2 . *
& ( C R ( 1 ) + C T ( 1 ) ) * ( 2 . * C R ( 1 ) + C T ( 1 ) ) *
61 ( 2 . * T R ( 1 ) + T T ( 1 ) ) )
Y ( 1 ) = WW(1) / G W ( 1 )
10 Z ( I ) = B ( 1 ) * B S P A N ( 1 ) * N ( 1 ) * ( 1 . - D ( 1 ) )
RETURN END C SUBROUTINE FUSLGE ( M ,GW,WW, N, RHOP, RHOR, ER, FF, L F , B F ,WACT, X , Y, Z ) REAL G W ( 2 0 ) t W W ( 2 0 ) , N ( 2 O ) f R H O P ( 2 0 ) t R H O R ( 2 0 ) p E R ( 2 0 ) , L F ( 2 0 ) , &FF ( 2 0 ) rBF ( 2 0 ) , X ( 2 0 ) , Y ( 2 0 ) ,Z ( 2 0 ) , A ( 2 0 ) , B ( 2 0 ) I D ( 2 0 ) ,WACT ( 2 0 ) DO 1 0 I = 1,M A ( 1 ) = R H O P ( 1 ) / F F ( 1 )
B ( 1 ) = R H O R ( 1 ) / E R ( 1 ) * * .5
D ( 1 ) = WW(1) / G W ( 1 )
X ( 1 ) = A ( 1 ) * N ( 1 ) * ( 1 . - D ( 1 ) ) * L F ( 1 ) * * 2. / B F ( 1 )
Y ( 1 ) = W A C T ( 1 ) / G W ( 1 )
10 z ( I ) ( B ( I ) / ( N ( I ) ** - 5 ) ) * B F ( 1 ) ** 2. / ( l . - D ( I ) ) ** . 5
RETURN END C SUBROUTINE H Z T A I L ( M I GW, WW, N, RHO F FS , LAMDA BSPAN, S W , S, CR, CT, &TR,TT,WACT,X,Y,Z) REAL G W ( 2 0 ) ,WW(20) , . N ( 2 0 ) , R H 0 ( 2 0 ) , F ( 2 0 ) , F S ( 2 0 ) , L A M D A ( 2 0 ) t B S P A N ( 2 0 ) & S W ( 2 0 ) ,S(20) , C R ( 2 0 ) , C T ( 2 0 ) , T R ( 2 0 ) , T T ( 2 0 ) , X ( 2 0 ) , Y ( 2 0 ) ,Z ( 2 0 ) , & W A C T ( 2 0 ) , A ( 2 0 ) , B ( 2 0 ) , D ( 2 0 ) DO 10 I = l,M A ( 1 ) = R H O ( 1 ) / F ( 1 ) B ( 1 ) = R H O ( 1 ) / F S ( 1 ) D ( 1 ) = WW(1) / G W ( 1 )
X ( 1 ) = A ( 1 ) * N ( 1 ) * (1. - D ( 1 ) ) *
& B S P A N ( 1 ) * S ( 1 ) ** 2 . * ( C R ( 1 ) + 2. * C T ( 1 ) ) /
& ( S W ( 1 ) * ( C O S ( L A M D A ( I ) ) ) * * 2 . * ( C R ( 1 ) + C T ( 1 ) ) *
& ( 2 . * C R ( 1 ) + C T ( 1 ) ) * (2. * T R ( 1 ) + T T ( 1 ) ) )
Y ( 1 ) = W A C T ( 1 ) / G W ( 1 )
10 Z(I) = B ( 1 ) * N ( 1 ) * B S P A N ( 1 ) * ( l . - D ( I ) ) * S ( 1 ) / S W ( 1 )
RETURN END C 7 7 SUBROUTINE VTAIL(M,GW,WW,N,RHO,F,FS,LAMDA,BSPAN,SW,S,CR,CT, &TR,TT,WACT,X,Y,Z) REAL GW(20) rWW(20) rN(20) tRHO(20)tF(20)rFS(20) tLAMDA(20) ,BSPAN(20), &SW(20)rS(20) rCR(20) fCT(20) rTR(20)jTT(20)rX(20) ,Y ( 2 0 ) ,Z ( 2 0 ) &WACT(20)rA(20) ,B (20),D(20) 10 I = l,M DO A ( I ) = RHO(1) / F(1) B(1) = RHO(1) / FS(1) D(1) = WW(1) / GW(1)
X(1) = A(1) * N(1) * (1. - D(1)) *
& BSPAN(1) * S ( 1 ) ** 2. * (CR(1) + 2. * CT(1)) /
& (SW(1) * (COS(LAMDA(I)))**2. * (CR(1) + CT(1)) *
& (2. * CR(1) + CT(1)) * ( 2 . * TR(1) + TT(1)))
Y(1) = WACT(1) / GW(1)
10 Z(1) = B(1) * N(1) * BSPAN(1) * (1.-D(1)) * S(1) / =(I)
RETURN END C SUBROUTINE WINC(M,WGS,N,RHO,F,FS,LAMDA,BSPAN,SW,CR,CT,TR,TT, & X , Z ) REAL WGS(20) ,N(20) vRHO(20) ,F (20)rFS(20) &LAMDA(2O)fBSPAN(20)rSW(20) ICR(20) fCT(20) fTR(2O),TT(20), &X(2O) ,Z(20) ,A(20) ,B(20) ,D(20) DO 10 I = 1,M A(1) = RHO(1) / F(1) B(1) = RHO(1) / FS(1) D(1) = WGS(1)
X(1) = A(1) * N(1) * BSPAN(1) * SW(1) * (1.-D(1)) *
E4 (CR(1) + 2. * CT(1)) / ((COS(LAMDA(I)))**2. *
& (CR(1) + CT(1)) * (2. * CR(1) + CT(1)) *
& (2. * TR(1) + TT(1)))
10 Z(1) = B(1) * BSPAN(1) * N ( I ) * (1.-D(1))
RETURN END C SUBROUTINE FUSLGC(M,WGS,N,RHOP,RHOR,ER,FF,LF,BF,X,Z) REAL WGS(20) ,N(2O) IRHOP(20) tRHOR(20)rER(20) tLF(20) &FF(20)rBF(20) pX(20) , Z (20),A(20),B (20),D(20) DO 10 I = 1,M A(1) = RHOP(1) / FF(1)
B(1) = RHOR(1) / ER(1) * * .5
D ( 1 ) = WGS(1)
X(1) = A(1) * N(1) * (1.-D(1)) * LF(1) ** 2. / BF(1)
10 Z(1) = (B(I)/(N(I) * * .5)) * BF(1) ** 2. / (1.-D(1)) ** .5
RETURN END C SUBROUTINE HZTAIC(M,WGS,M,RHO,F,FS,LAMDA,BSPAN,SW,S,CR,CT, &TR,TT,X,Z) REAL WGS(20) rN(20) ,RH0(20) ,F(20) rFS(20) tLAMDA(20) ,BSPAN(20), &SW(2O) rS(2O) rCR(20) tCT(20) fTR(20)rTT(20) rX(20) ,Z ( 2 0 ) f &A(20) ,B(20) ,D(20) DO 10 I = l,M A(1) = RHO(1) / F(1) B(1) = RHO(1) / FS(1) 7 8 D(1) = WGS(1)
X(1) = A(1) * N(1) * (1. - D(1)) *
& BSPAN(1) * S(1) * * 2. * (CR(1) + 2. * CT(1)) /
& (SW(1) * (COS(LAMDA(I)))**2. * (CR(1) + CT(1)) *
& (2. * CR(1) + CT(1)) * (2. * TR(1) + TT(1)))
10 Z(1) = B(1) * N(I) * BSPAN(1) * (1.-D(1)) * S(1) / SW(1)
RETURN END C SUBROUTINE VTAIC(M,WGS,X,RHO,F,FS,LAMDA,BSPAN,SW,S,CR,CT, &TR,TT,X,Z) REAL WGS(20) ,N(20) fRHO(20) p F ( 2 0 ) rFS(20) ILAMDA(20) ,BSPAN(20), &SW(2O) ,S(2O) ,CR(2O),CT(20),TR(20),TT(2O),X(2O),Z(20), &A(20) ,B(20) ,D(20) DO 10 I = l,M A(1) = RHO(1) / F ( 1 ) B(1) = RHO(1) / FS(1) D(1) = WGS(1)
X(1) = A(I) * N(1) * (1. - D(1)) *
E4 BSPAN(1) * S ( 1 ) ** 2 . * (CR(1) + 2 . * CT(1)) /
& (SW(1) * (COS(LAMDA(I)))**2. * (CR(1) + CT(1)) *
& (2. * CR(1) + CT(1)) * (2. * TR(1) + TT(1)))
10 Z(I) = B(I) * N(I) * BSPAN(1) * (1.-D(1)) * S(1) / SW(1)
RETURN END PHSEII FORTRAN C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C * THE FOLLOWING PROGRAM USES THE COEFFICIENTS OF *
C * THE GENREG PROGRAM TO CALCULATE AIRCRAFT COM- *
C * PONENT WEIGHTS (WING, FUSELAGE, VERTICAL AND *
C * HORIZONTAL TAIL). THE PROGRAM MAY BE USED IN- *
C * TERACTIVELY OR WITH A DATA SET (PHSEII DATA). *
C * *
C * THIS PROGRAM IS EXECUTED BY USE OF EXEC "PHSEII". *
C * *
C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C REAL N,LF,LAMDA,LAMDAT,LAMDAV LOGICAL *1 TITLE(60) DATA RHO/.l/,RHOP/.1/,RHOR/.l/~ER/lO.6/,RHOT/.l/,RHOV/.l/ DATA FW/65000./,FS/24200./,FT/65000./,FTS/24200./,FV/65000./ DATA FVS/24200./,FF/65000./ DATA C1/,0744046/, C2/.122482/, C3/1.19660/ DATA ClF/.o876243/,C2F/.217097/,C3F/.432849/ DATA ClH/.O120291/,C2H/-.234289/,C3H/2.37790/ DATA ClV/.O0835541/,C2V/.O203209/,C3V/3.80514/ WRITE (6,300) 300 FORMAT(/2X,'TO USE THIS PROGRAM WITH EXISTING DATA SET "PHSEII', t ' DATA",'/,' ENTER "1". FOR INTERACTIVE USAGE, ENTER "2".'/) READ (5, * ) NTR IF (NTR.EQ.1)GO TO 680 WRITE(6,310) 310 FORMAT(2XI'NAME OF AIRPLANE OR CASE?') READ(Sr311) (TITLE(KKK),KKK=1,60) WRITE (4,311)(TITLE(KKK),KKK=1,60) 311 FORMAT (60A1) WRITE(61320) 320 FORMAT(2X,'ENTER ESTIMATED GROSS WEIGHT AND DESIGN LOAD FACTOR:') *) GW,N READ (5, WRITE (4,317)GW,N
31 7 FORMAT (2F12 . 4)
WRITE(61325) 325 FORMAT(2X,'IF AIRPLANE IS ALUMINUM AND MATERIAL STRENGTHS ARE '/, & ' UNKNOWN, ENTER "1". TO SUPPLY MATERIAL VALUES, ENTER "2"'/, & ' (DEFAULT VALUES WILL BE SHOWN FOR EACH ENTRY):') (5, *)MTV READ IF(MTV.EQ.1)GO TO 649 WRITE (6,330) -1):') 330 FORMAT(' WING MATERIAL DENSITY IN PSI (FOR DEFAULT, ENTER READ (5,*)RHO WRITE(6,335) -1):') 335 FORMAT(' FUSELAGE PANEL MATERIAL DENSITY IN PSI (DFLT ENTR READ (5, * ) RHOP WRITE (6,340) 340 FORMAT(' FUSELAGE RIB MATERIAL DENSITY IN PSI (DFLT ENTR .l):') READ(5,*)RHOR WRITE(6,345) 8 0 345 FORMAT(' FUSELAGE R I B YOUNGS MODULUS I N PSI ( D F L T ENTR 1 0 . 6 ) : ' )
READ ( 5, * ) E R
WRITE ( 6 , 3 5 0 )
350 FORMAT( ' HORIZONTAL T A I L MATERIAL D E N S I T Y I N PSI ( D F L T ENTR .1) : I )
R E A D ( 5 , * ) R H O T WRITE ( 6 , 3 5 5 ) 355 FORMAT( I V E R T I C A L T A I L MATERIAL D E N S I T Y I N PSI ( D F L T ENTR . 1) : I ) READ ( 5 , *) RHOV WRITE ( 6 , 3 6 0 ) 360 FORMAT(' ALLOWABLE WING COVER S T R E S S I N PSI ( D F L T ENTR 6 5 0 0 0 ) : ' ) READ (5, *)FW WRITE ( 6 , 3 6 5 ) 365 FORMAT(' ULTIMATE WING SHEAR S T R E S S I N PSI ( D F L T ENTR 2 4 2 0 0 ) : ' ) READ (5, *) FS WRITE ( 6 , 3 7 0 ) 370 FORMAT(' ALLOWABLE T A I L COVER S T R E S S I N P S I ( D F L T ENTR 6 5 0 0 0 ) : ' ) READ ( 5 , *) FT WRITE ( 6 , 3 7 5 ) 375 FORMAT(' ULTIMATE T A I L SHEAR S T R E S S I N PSI ( D F L T ENTR 2 4 2 0 0 ) : ' ) READ ( 5 , *) FTS WRITE ( 6 , 3 8 0 ) 380 FORMAT(' ALLOWABLE FIN COVER S T R E S S I N PSI ( D F L T ENTR 6 5 0 0 0 ) : ' )
READ ( 5, * ) F V
WRITE ( 6 , 3 8 5 ) 385 FORMAT(' ULTIMATE FIN SHEAR S T R E S S I N PSI ( D F L T ENTR 2 4 2 0 0 ) : ' ) READ ( 5 , *) F V S W R I T E ( 6 , 3 9 0 ) 390 FORMAT(' ALWABLE FUSELAGE COVER S T R E S S I N PSI ( D F L T ENTR 6 5 0 0 0 ) : ' ) READ ( 5 , * ) F F 649 CONTINUE WRITE (4,318)RHO,RHOP,RHOR,ER,RHOT,RHOV WRITE(4,318)FW,FS,FT,FTS,FV,FVS C C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C * CONTINUE BY ENTERING GEOMETRIC VALUES FOR THIS CASE. *
C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C W R I T E ( 6 , 3 9 5 )
395 FORMAT( ' ENTER WING SPAN, WING AREA, T A I L S P A N , T A I L AREA, ' /
& ' F I N SPAN, AND F I N AREA, UNITS ARE I N C H E S OR SQUARE I N C H E S : ' ) READ ( 5 , *) BW, S W , B T , ST, BV, SV WRITE ( 4 , 3 1 8 ) BW, SW, B T , S T , B V , SV WRITE ( 6 , 4 0 0 ) 4 0 0 FORMAT(' ENTER FUSELAGE WIDTH AND LENGTH, AND 2 5 % CHORD S W E E P ' / , & ' OF THE WING, T A I L AND FIN. UNITS ARE I N C H E S AND R A D I A N S : ' ) READ (5, * ) B F , L F , LAMDA, LAMDAT, LAMDAV WRITE(4,318)BF,LF,FF,LAMDA,LAMDAT,LAMDAV W R I T E ( 6 f 4 0 5 ) 405 FORMAT(' ENTER WING ROOT CHORD, WING T I P CHORD, T A I L R O O T ' / , . .
AND TIP CHORDS, AND FIN ROOT-AND TIP CHORDS ( I N C H E S ) : ' )
READ ( 5 , *) CR, C T , CRT, C T T , CRV , CTV
WRITE ( 4 , 3 1 8 ) C R , C T , C R T , C T T , CRV,CTV W R I T E ( 6 , 4 1 0 ) 410 FORMAT(' ENTER WING ROOT MAXIMUM T H I C K N E S S , WING T I P MAXIMUM'/, & ' T H I C K N E S S , H Z . T A I L ROOT AND T I P MAXIMUM T H I C K N E S S E S , A N D ' / ,
* ' FIN ROOT AND TIP MAXIMUM THICKNESSES (IN INCHES):')
READ(5,*)TR,TT,TRT,TTT,TRVtTTV WRITE (4,3 18) TR,TT,TRT,TTT,TRV,TTV 318 FORMAT(6F12.4) TO 681 GO 680 CONTINUE C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C
C * THE FOLLOWING DATA IS READ FROM FILE #4, CALLED *
C * 'PHSEII DATA'. IT REPRESENTS TITLE, GW, MATR. *
C * PROPERTIES, AND GEOMETRIES OF THE AIRPLANE IN- *
C * TENDED FOR THE ANALYSIS. *
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C C
READ (4,311) (TITLE (KKK) , KKK=l, 6 0)
READ(4,*)GWrN READ(4, *)RHO,RHOP,RHOR,ER,RHOT,RHOV READ ( 4 , *) FW,FS,FT,FTS,FV,FVS READ (4, *) BW,SW,BT,ST,BV,SV READ(4,*)BF,LF,FF,LAMDA,LAMDAT,LAMDAV
READ (4, * ) CR,CT,CRT,CTT,CRV , CTV
READ ( 4 , * ) TR,TT,TRT, TTT, TRV, TTV 681 CONTINUE C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C
C * THE FOLLOWING SUBROUTINES ARE SEQUENTIALLY *
C * CALLED FOR THE PURPOSE OF EVALUATING AIRPLANE *
C * COMPONENT WEIGHTS. THE COEFFICIENTS C1, C2, AND *
C * C3 FOR THE EQUATION "YCAL = C1 + C2 * X + C3 * 2 " *
C * HAVE BEEN SUPPLIED. DIFFERENT COEFFICIENTS MAY BE *
C * USED AND DEFINED INTERACTIVELY. *
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
C C WRITE (6,458) 450 FORMAT(# THE COEFFICIENTS ci, c2, AND c3 FOR THE EQUATION'/, & ' "YCAL = C1 + C2 * X + C3 * 2 " HAVE BEEN SUPPLIED IN THIS'/, & ' PROGRAM (X AND 2 ARE DETERMINED PER AIRPLANE). TO PROVIDE'/, & ' DIFFERENT COEFFICIENTS, ENTER "1". TO CONTINUE WITH THE'/, & ' GIVEN COEFFICIENTS, ENTER " 2 " . I ) READ (5, * ) NCOF IF(NCOF.EQ.2)GO TO 691 WRITE (6,415) 4 1 5 FORMAT(' ENTER NEW WING COEFFICIENTS Cl, C2, AND C3:') READ (5,*)C1, C2,C3 WRITE(6r420) 420 FORMAT(' ENTER NEW FUSELAGE COEFFICIENTS ClF, C2F, AND C3F:')
READ ( 5, * ) C 1 F C 2F C 3 F
WRITE (6,425) 425 FORMAT(' ENTER NEW HZ TAIL COEFFICIENTS ClH, C2H, AND C3H:')
READ ( 5, * ) C 1 H , C2H , C3H
WRITE(6,430) 430 FORMAT(' ENTER NEW VT TAIL COEFFICIENTS ClV, C2V, AND C3V:') READ(5,*)C1VIC2V,C3V 691 CONTINUE WGS = .10 8 2 EPS = .0001 WRITE(6,92)
92 FORMAT(//2X,'ITERATION FROM WW/GW =.lo ( l o % ) : ' / )
38 CALL WINC(WGS,N,RHO,FW,FS,LAMDA,BW,SW,CR,CT, &TR, TT, X, 2 )
YCAL = c1 + c2 * x + c3 * z
IF (YCAL.GT.WGS)WGS = WGS + (YCAL-WGS)/2.
IF(YCAL.LT.WGS)WGS = WGS - (WGS-YCAL)/2.
WRITE (6 93)YCAL ,WGS 39 IF (ABS(WGS-YCAL).GT. EPS)GO TO 38
41 YCAL = YCAL * GW
93 FORMAT(2F14.4) CALL FUSLGC(WGS,N,RHOP,RHOR,ER,FF,LF,BF,X,Z)
YCFUS = ( C1F + C2F * X + C3F * Z ) * GW
CALL HZTAIC(WGS,N,RHOT,FT,FTS,LAMDAT,BT,SW, &ST,CRT,CTT,TRT, TTT, X, Z )
YCHZT = ( C1H + C2H * X + C3H * 2 ) * GW
CALL VTAIC(WGS,N,RHOV,FV,FVS,LAMDAV,BV,SW, &SV,CRV CTV TRV,TTV X, Z )
YCVTL = ( C1V + C2V * X + C3V * Z) * GW
4 4 CONTINUE WRITE (6,500) (TITLE (KKK) KKK=1,6O),YCAL,YCFUS,YCHZT,YCVTL WRITE ( '7,s 0 0 ) (TITLE(KKK ) KKK=1,6 0 ) YCAL,YCFUS YCHZT,YCVTL 500 FORMAT('11//,2X,'TITLE: ',60Al////,2X,'WING WEIGHT: I , &T2O,FlO.2,' P0UNDS1//,2X,'FUSELAGE WEIGHT: ',T2O,F10.2, & ' POUNDS1//,2X,'HZ. TAIL WEIGHT: ',T20,F10.2,' POUNDS1//,2X, &'VT. TAIL WEIGHT: ',T20,F10.2,' POUNDS') STOP END C C SUBROUTINE WINC(WGS,M,RHO,F,FS,LAMDA,BSPAN,SW,CR,CT,TR,TT, & X , Z ) REAL N,LAMDA A = RHO / F B = RHO / FS D = WGS
X = A * N * BSPAN * SW * (l.-D) * (CR + 2. * CT) /
&((COS(LAMDA))**2. * (CR + CT) * (2. * CR + CT) * (2. * TR + TT))
10 2 = B * BSPAN * N * (l.-D)
RETURN END C SUBROUTINE FUSLGC (WGS, M, RHOP,P.HOR, ER,FF,LF ,BF,X, 2 ) REAL N,LF ER = ER * 1000000.
A = RHOP / FF
B = RHOR / ER ** .5
D = WGS
X = A * N * (l.-D) * LF ** 2. / BF
Z = (B/(N ** -5)) * BF * * 2 . / ((l.-D) ** . 5 )
RETURN END C SUBROUTINE HZTAIC(WGS,N,RHO,F,FS,LAMDA,BSPAN,SW,S,CR,CT, 8 3 &TRrTTrXrZ) REAL N,LAMDA A = RHO / F B = RHO / FS D = WGS
X = A * N * (1. - D) * BSPAN * S ** 2. * (CR + 2 . * CT) /
&(SW*(COS(LAMDA))**2. * (CR 3 . CT) * ( 2 . * CR + CT) * (2.*TR + T T ) )
2 = B * N * BSPAN * (1.-D) * S / SW
RETURN END C SUBROUTINE VTAIC(WGSrMrRHOrFpFSrLAMDA,BSPAN,SW,SICRrCTr &TRrTTrXrZ) REAL N 8 L A M D A A = RHO / F B = RHO / FS D = WGS
X = A * N * (1. - D) "BSPAN * S ** 2. * (CR + 2. * CT) /
&(SW*(COS(LAMDA))**2. * (CR 3- CT) * (2. * CR + CT) * (2.*TR + TT))
2 = B * N * BSPAN * (I.-D) * S / SW
RETURN END 8 4 1. Report No. 2. Government Accession NO. 3. Rreipimt's C.t~log No.
NASA CR-178163 4. Title and Subtitle 5. Repor( Omto September 1986 Weight E s t i m a t i o n Techniques f o r Composite A i r p l a n e s i n General A v i a t i o n I n d u s t r y 6. Performing Organization cod.
7 Author(s) 8 PerformingOrpmization Report No.
T. Paramasivam, Walter J . Horn AR 86-1 and James R i t t e r 10. Work Unit No.
9 Perlormmg Organization Name and Address 1 1 Contract or Grant No.
T,he Wic,hita S t a t e U n i v e r s i t y NAG 1-452 W i c h i t a , KS 67208 13. Type of Repon and Period Covered .
12. Sponsoring Agency Name and Address Contractor Report N a t i o n a l Aeronautics and Space A d m i n i s t r a t i o n 14 S v o n r o r q Agency Code Idashington , DC 20546 505-43-43-01 Langley Technical M o n i t o r : Robert W . Koenig ~~ - -~ - I G Abrlraci C u r r e n t l y a v a i l a b l e weight e s t i m a t i o n methods f o r general a v i a t i o n a i r p l a n e s Mere i n v e s t i g a t e d . New equations w i t h e x p l i c i t m a t e r i a l p r o p e r t i e s were developed f o r t h e weight e s t i m a t i o n of a i r c r a f t components such as wing, f u s e l a g e and empen- iage. Regression a n a l y s i s was a p p l i e d t o t h e basic equations f o r a data base o f twelve a i r p l a n e s t o determine t h e c o e f f i c i e n t s . The r e s u l t i n g equations can be l s e d t o p r e d i c t t h e component weights of e i t h e r m e t a l l i c o r composite a i r p l a n e s .
Composite A i r p l a n e s U n c l a s s i f i e d - U n l i m i t e d Wei g h t E s t imat i on Subject Category 02 General A v i a t i o n
1 A05
Uncl ass i f i ed Uncl as s i f i ed
i
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