Tailless aircraft performance improvements with relaxed static stability

APPENDIX A

STABILITY & CONTROL DERIVATIVES

A- 1

LONGITUDINAL DERIVATIVES

A-2 A-3 a. cm, A-4 ORlG4NAL PAGE IS OF POOR QUALfTY A-5 Ch .

ORIGINAL PAGE I S OF POOR QUALtTY .

A-6 ORIGMAL PAGE I S OF POOR QUALITY A-7 A-8 ORIGINAL PAGE I S OF POOR QUALITY ORIGINAL PAGE IS OF POOR QUALITY A-9

LATERAL-DIRECTIONAL DERIVATIVES

A-1 0 J A-1 1 A-1 2 ORIGINAL PAGE IS OF POOR QUALITY ORIGINAL PAGE IS OF QUAL'Ty A-13

I

A

b

h

w

ORIGINAL PAGE IS OF POOR QUALITY A-1 4 - . O \ S 4 I

I - * 0 2 7 3 I

.L - . bqob

.3

- os34

- 5 0 7 'I

d

b (D r-i V bo e rl u) r-i F

*

. I' -4 cc)

cv

T

cu * a

0 00 0 0

O ! 3

0 ' 0 0 I I I I A-1 6 ORIGINAL PAGE I S OF POOR QUALITY A-1 7

CONTROL DERIVATIVES

A-18 ORIGINAL PAGE IS OF POOR QUALITY A-1 9 A-2 0 ORIGINAL PAGE I S OF POOR QUALITY

j c, cn

-.oo\

-. ootc

0 . ootq

-. W t \

- . Ooi7

- .\f

- . \o

- .t\

' e t 3 A-21

s

CQ

3. & = -Yo

b

s

A-2 2

b

a2 [

I C P cn

A-23

> = - . e Sblcod

A-24 I .

U

0 0 0 0 I 0

I I I I I I A-25 (3' W d - v I I I A-2 6 Review of NACA ACR 4411 Collection of balanced-ail test data to see if useful re C . 4 6 , on flying wing project.

Consider only non-protruding overhangs to begin with, e.g., C series, D series, E-V to V I I I : Look at: 1/2 span wings 1st with Cn (rather than CD) data.

Eliminate: C V I I I , X I V , XV, D I , 111, I X , D I V , V level TR E 111, I V , (1 0 ) V I I S V I 1 1 Search remaining for a n CL variations C36 plain sealed .155C aileron +20" -4.5- d6.6 37 1/3c internal bal aileron +14" -4.4 17.7 C40, 41 poor print Reasonable scale on Cn plots 42 internal .563 bal + 2 0 ' -.36 CCLC1.25 43 internal .563 bal +20° -.36 CCLC1.25 ail.extended to tip

C46a plain unbal .150C + 3 0 ' - 40" a - 1, 8, 15

46b .30 internal bal +20° - 3 0 ' a - 1, 8, 15

47 .35 internal bal +20" - 25" Q - 1, 8, 15 + inbd flap

C50 .29 internal bal .150C +20" a - 0, 8, 12

1/2 scale Cn plots C71 .30 internal bal .18C +30" -4.2 M 1 7 . 7 full span 72 .56 internal bal .18C +15" -4.2 M 1 7 . 7 ail 1/2 scale Cn plots

c75 .35 internal bal +15" a - .3, 5.7, 10.9

76; 77 ditto flaps - 50"; ditto bal plate removed (unsealed)

1/2 scale Cn plot E16 plain .155c +30 CL-0.1, 1.06 full span tab 17 .005C gap +30 CL-0.1, 1.06 full span tab 1/2 scale Cn plot

E20 internal .688 bal .15C +15" Cn - .02,? full span tab

21 internal .688 bal .15C +15" CL - .02 1/2 span tab

22 .563 bal .162C +20 CL - .02, .71, 1.25 1/2 span tab

A-27 CL -.25 .06 .39 .73 1.05 1.24

6 a - -4.5 0 -4.5 8.8 13.3 16.6

Left Wing

+20 - .0005 - 0022 - .0037 - 0045 - 0060

- 0070

16 0 - 0012 - .0027 - 0035 - 0050

- 0055

12 0 - 0008 - .0020 - 0025 - 0040

- 0040

8 0 - 0006 - .0012

- 0012 - 0025 - 0025

- +.0002

4 0 - .0002 - .0008 - 0006 - 0012 - 0012

0 0 0 0 0 0 0

0 - .0002

-4 - .0005 + 0006 0010 0014

- .0002 + .0004 0018

-8 - .OOl + 0012 0025

- 12 - .0015 - .0005 + .0004 +. 0015 0025

-16 - .002 - .001 +. 0004 + 0015 0030 0040

-20" - .003 - .0015 0 +. 0015 + 0037 + 0045

CP ( C , / C l ? ) vs 6,

- -

.0225 0232 +20 + 0225 0225 020

- -

.0205 0220 0205 0182 16 +.021

- -

.0167 0185 12 0168 0167 0147

- -

8 0120 0133 0120 0105

- -

.006 .0067 4 .006 .006 .0053

- -

0 0 0 0 0 0

- -

- .0053 - .0058

-4 - .0051 - .0059 - .0054

- 0105 - 0115 - 0108

-8 - 0102 - 0118

- -

- .0158 - 0172

- 12 - .0146 - 0177 - 0152

- -

- 16 - 0185 - .0208 - 0227 - 0194

- 0237

- -

- 20 - .021 - .025 - 0280 - 0295 - 0230

Q - +4.5 6a - '

Supposed trimmed:

at6 - -4O + 16 - +12 - 20

.0185 - ,0280

cQ

- .0020 0

C n

6 - 440 +20 - 12

.0232 - .0172

- .0037 + .0004

c* Consider + 6, on Ih wing; then

- + for - 6 , on rh wing .*. change s i g n s of C J , C n for

-6, and add both s i d e s : 6 , - -4 C I - .0455 cn - - .0020

- +4 C l - .0404 Cn - ,0041

A-28 Repeat Above

a - 4.5

8.8 13.3 6 1 -4" 6 9 +12 CQ 0185

c , - .0020

- .0025

- .0040

- 20 CQ - .0280 - 0295

- .0230

' n 0

+. 0015 + 0037

c CQ 0465 .0462 .0377

c , - .0020 - .0040

- .0077

C , / C Q -.0430 - .0866

- .2042

+4 O

6 - +20 CQ .0232

0225 0200 C , -.0037 -0045

- .0060

- 12 CQ -.0172

- .0177

- .0152

C , +.0004

+. 0015

+. 0025 .0402 c CQ .0404 0352

- .0060

C , -.0041 - .0085

- .1493

C,/CQ -.lo15 - .2415

Trimming with down elevon increases adverse yaw!

A-2 9 Aileron Characteristics of Model C-X With F l a p s Figure A - 4 .

ORIGINAL PAGE I S OF POOR QUALtTY A-3 0

APPENDIX B

FLIGHT CONDITION ANALYSIS

B-1 AlTF LONOINAL. LIFTDRAG "DIMENSIONAL D E R I V A T I V E S

Date: 3g - Fbb - g ~

d d - r m n r - y y Flight Condition Identifier; -1: 60 Characters or Numerals J I L I Y I I ~ u . h I I kJ I+ I/LLg h s , D , l ,N,61/,5~TAd3B L d IC10 I FI, r,i ,G, ',S,L,/~H,E,~ l\llyl I --.

S m tpn. 9 1: w/o saw Eqa, - 0

I

(define 6, below)

=a =a C'a

L 8 .74 : i n R+A Control Symbols (except thrust) 61.2,..a6. Use 3 characters; left justified: m s - * - S - 8 - 1 - B -3 A F T F F I L E NAME : A:FWLANSTA. INP F L Y I NGW I NG / L A N D I NG / ST'ABLECONF I G / SL / H E A V Y N O N - D I M E N S I O N A L D E R I V A T I V E S : C L A C L A D C L M C L

4 . .- ":!; y ( l )

0 . (j ( : I . 0

1 . 040

CMAD CMQ CMM CMA

- 33- (3 . 0 -1.560 (3 . (3

. AAV

CDA CDM TM TDTH C D

. 25at:j . 655(3 0 . 0 - 8 " " ' ar8. 0 1.000 -

CL.DEP CMDEP CDDEP

s 740 - . 26(:)

(3 . ( : )

D I MEiNS I WNAL DER I V A T I VES:

xu xu * x w TU

- . (58 176 . 06006 -. 00 12659

'I.. (313049 ZWD zw

ZU ZU *

0 . (3 ..-. 7250

-. 3245 -. 3245

Ivl u MU * MWD M W

0 , (j (1) . 0 0 . (j -. 004558 1 4 - 4

MAD MA MQ e;h (P4 'ban ( : ) . (5 -. y(:,25 .-. 42.34 4 I.

XDEF' ZDEP MDEP I . 3 , gee\ hj4

- -> r )

- 1 ,0666

(3 . (1) r r . 8 6

Y L ) T t i Z D T H MDTH ( 5 t a )

. (j(jt:) 16572 ( : I , ( : I 0 . 0

(&$c Goih\) T R F " DATA F I L E NAME : A:FWLANSTA.SAV .

O L D file, w r i t e ovet- i t ( Y / N 1'7 Y U , W ,THE,DD , A Z , A Z ' , H D , E n t e r - no. o f eqns t o output from 4 thtw 7 '7 FLYINGWING/LANDING/STABLECONFIG/SL/HEAVY

3 w e0P.t Inm

DENOM I NATOR : C .1268;. 1972 .0250;. 19hdS C . 539; 1.107 . 5 9 0 ; . 9361

q: . 0476:) &z% ~ 0 : ~

ORIGINAL PAGE IS OF POOR QUALtTY B -4 FLYINGWING/LANDING/STflBLECONFIG/SL/HEAVY DEF' NUMERATORS:

-&awn ( S + * ) ($4 a ~ x t n

N(U-DEP) -1.373(.962) (-16.32) (21.5:) N (W-DEP) -22.9 (9.67) C ,1703;. 225 -0382:. 221 1 <:-11.14> N(THE-DEF') -1.067(.1202) t . 5 8 9 ) <-.0755> N (DD-DEP) 50.1 (. 0291) (-1.348) (1.935) <-.3.8Q> N (AZ-DEP) -22.9 (0.0) (. 0288) (-2.18) ( 2 . 6 5 ) ~z.3.80) N ( A Z '-DEP) -1.523(0.0) (.0286) (8.23) (-10.61) <3.80> N (HD-DEP) 22.9(. 0288) (-2.18) (2.65) <-3.80> FLYINGWING/LANDING/STABLECONFIG/SL/HEAVY DTH NUMERATORS: N(U-DTH) .OOO1657(O.O) C.522; 1.10 .574; .9383 <.00020> N (W-DTH) -. 538E-4 (0.0) (. 42.3) <:-. 228E-4).

N (THE-DTH) .245E-6 <. 245E-6>

N(DD-DTH) .538E-4C. 1617; .950 -1536; .9381 <.485E-4>.

N(AZ-DTH) -.538E-4(0.0)[.223;.950 .212: .9263 1;-.485E-4>* N ( A Z ' - D T H ) -.538E-4(0.0) C.271; .950 .257; .9151 (-.485E-4>

N (HD-DTH) . 538E-4C. 223;. 950 .212;. 9261 <. 485E-4)

F L Y I N G W I N G / L A N D I N G / S T A B L E C O " E A V Y B-5 rd (w-DEFVDD-DTH) N(W-DEP/AZ-DTH) N(W-DEP/AZ'-DTH) N (W-DEP/HD-DTH) N (THE-DEP/DD-DTH) ( THE-DEF/ A 2 -DTH 1 N N(THE-DEF/AZ '-DTH) N (THE-DEP/HD-DTH) N (DD-DEP/AZ-DTH) N (DD-DEP/AZ '-DTH) N (DD-DEP/HD-DTH) N (CIZ-DEF'/AZ '-DTH) N (AZ-DEF/HD-DTH) N ( A Z '-DEP/HD-DTH) 02-26-88 10: 36: 25 AFTF completed B - 6 B -7

t

I 1 I lee 2 - 1 - F i g u r e B - 1 . S t a b l e Configuration P i t c h Rate Feedback Loop Root Locus ORIMNAL PAGE IS

OF POOR QUALtTY

B -8 B-9 (a) Root Locus iheta Feedback L o p , Stable I h ! 9 Q P (b) Bode Plot Figure B-2. Stable Configuration Pitch Angle Feedback Loop Root Locus and Bode Plot ORIGINAL PAGE S S OF POOR QUALITY B-10 -.

>' -.-- 0-

-

I I 1 I

- 20 I

Tine H at Pilot Response to a 4 des Theta Cormand ~ i ...* i ! - I j I 1 I I j -4 I 8 1 2 3 4 I Figure B-3.

Change I n A l t i t u d e A t The P i l o t Location For The S t a b l e Configuration .

B-11 H at CG Response to a 4 de4 Theta Command H at CG Response to a 4 de4 Theta Command 0 128; 4 0 128; 4 u u I -

----

t 1 0 0 1 /-- I

: leet-

P U U

-------

--- -.

t 8 0 b Ad- /- ..-'

,-- 801 60 i

60 i-

i I I I ! I i I I I

- 28

0 18 28 30 Time

- 2 , L

L i -4 1 I I I I I I I 8 1 2 3 4 fine Change I n A l t i t u d e A t The CG F i g u r e B-4.

. For The S t a b l e Configuration B-12 H at Prop Tip Response t o a 4 deq Theta Conmand -/&

----- /-

CI /--

/= *F

,-/

r

i , =

40 I -

./-

+- /' *-

/=

0 +---

c -2a I I I I I I 1 I 8 10 28 3e 4 Tine U ,/ 8 - / Y F i g u r e B - 5 . Change I n A l t i t u d e A t The Prop Tip For The The S t a b l e Configuration B-13 B-14 Elevator Response to a Unit Step Theta Connand

o 4

c U

I -2 ! I I I I I I I e 10 28 38 4 0 50 Tine Elevator Response to a Unit Step Theta Connand 0 . 4 1 U U t -.4 i Tine F i g u r e B-6. S t a b l e Configuration E l e v a t o r Response (Higher Gain Case) B-15 P L U

- / /-- \

t

-------

to a Unit Step Theta Comand Theta Response 1 cc L 0 1 1 - - - -

-----

/--- ---

2 '

/

t - , 2 t I I I I I I I i fa 1 2 3 4 Tine Figure B-7. S t a b l e Configuration Pitch Angle Response (Higher Gain Case) R - I 6 U

-

t 68 I H at Pilot Response to a Unit Step Theta Comand 0 101 U t P U

8l

T

-2 c , I I I I I !

-4 I a 1 2 3 4 Tine F i g u r e B-8. Change I n A l t i t u d e A t The P i l o t Location For The S t a b l e Configuration (Higher Gain Case) B-17 H at CG Response to a Unit Step Theta Cornand 0 78 U t 68 P ! - U t H a t CG Response to a Unit Step Theta Command & U t P L u t

T 4 r

----- -e---

-2 1

I I I 1 I I I !

-4 L 4 0 1 2 3 Tine Ffgure B-9. Change In A l t i t u d e A t The CG For The S t a b l e Configuration (Higher Gain Case) B-18 H at Prop Tip Reswnse to a Unit Step Theta Connand o 7 8 1 u t 6 0 1 P u t

-re ! I i I I 1 I ! I I

B re 20 30 40

Tine H at h p Tip Response to a Unit Step Tkta Connand ’ 0 10 & U t P

* t-

U t

-2 L

I i- -4 I i I I , 1 I I e 1 2 3 4 Time Figure B-10. Change I n A l t i t u d e A t The Prop T i p For The S t a b l e Conf t g u r a t i o n (Higher Gain Case) B-19 B-20 ORlOlNAL PAGE IS OF POOR QUALITY Elevator Response to a Unit Step Theta Connand 0 11 lcsi U I t r I\.

P l i -3 1 * I I l a I ! I i a le 28 38 48 50 Tine Elevator Reswnse to a Unit Step Theta Connand

1 I 1 2

I .

L ' 1 I ,

-3 1 -. I I ! I I !

0 1 2 3 4 Tim Figure B-11. Stable Configuratfon Elevator Response (Highest Gain Case) B-21 ORIGINAL PAGE I S

OF POOR QUALtTY

H a t P i l o t Response to a Unit S t e p Theta Cownand 1 2 o 781 U t MI-- P U

58 L I

t

r

48 t -

38 c

L

20 I"

r /'

0 r---

I 1 ! I I I 1 -18.

0 18 28 3e 40 5 Time H a t P i l o t Response to a Unit S t e p Theta Comand o 181 i- 1I t Y U t I - 2 r i I I I I I t -4 !

0 1 2 3 4 Time Figure B-12. Change In Altitude A t The P i l o t Location For The Stable Configuration (Highest Gain Case) B-22 H at CC Reswnse to a Unit Step Theta Colmand L

-re i ! I I I I

8 10 28 38 40 5 t Tine H at CC Response to a Unit Step Theta Comnnd c -4 1 I ! I I I I I 0 1 2 3 4 i Tine Figure B-13. Change In Altitude A t The CG For The Stable Conf iguratlon (Highest Gain Case) B-23 H at Prop Tip Response to a Unit Step Theta Comand 0 79 !

P U t

--- /--

---- /-- H a t Prop Tip Response t o a Unit Step Theta Command 0 101 i Ef LL: u I- t P 1 1 t

I

- 2 r

t

I I I I I I j -4 !

0 1 2 3 4 Tine Figure B-14. Change In A l t i t u d e A t The Prop Tip For The S t a b l e Configuration (Highest Gain Case) B-24 LCtuOidb, U N S T A ~ ~ (iC IS-1) Input File Name; ~ l l l J I L I ~ I N I U ~ S ~ d ~ . ~ ) ~ P J ~ ~ ~ Output F i l e Name; I , , I I I I I . 1 ,

Date: ?r( - hb - a

AFTF LONGITUDINAL LIlT/DRAG NONDIMENSIONAL DERIVATIVES d d - m m m - y y 60 Characters or Numerals Flight Condition I d e n t i f i e r ; GCI: l c l L I Y I / I M I ~ I ~ I ~ I N I ~ I ! IL, C ;EI,o .I H .L, /, V,fJ,f , I , P , U IL * & , L ,a I # , /%I ILI Itsir i I i H i 6 i f i i V i Y i __.

W i t h Gusts - 1; WIO Gusts - 0

P O l y n ~ i d Coeff. -.l; W i t h o u t - 0

w i t h CPLG m - 1; w i t h o u t - 0

0 NRHS NG NPC 1 0 ICC IS 0 l a 1 0 I D s L * O I 1 l - I (define 6, below) $6 c%

d , fi , - . 2 D : ELEVON I H P I T C H

Control Symbols (except thrust) 61,2,...6. Use 3 characters; l e f t j u s t i f i e d : & & & * - I I - J I ~ I I t i l A 1 1 - ORlGlPZAL PASE IS B-25 OF POOR Q U A L m AFTF F I L E NGME : A:FWLANUSA. INP 10: 23: 26

(:)z - 2 6 - 88

GEOMETRY: LX A V T ALPHA GAMMA i6.70

178.(1 ( j . r j ( 3 . (j

RHO MACH X I 0 ZJ A

0.0 -

0 . (1

.17735

1116.5 . 0(:)2377

IY ALT I TUDE C W E I GHT S

0.0 -

834300.

(j 21.90 1 94 1 40.

280C) .

DEE I VAT I VES : NON-DIMENSIONAL CLM C L A CLAD CL 4.396 0. 0 0. 0 1.480 CMM CMA CMAD CMQ

( : I . 0

(1. (2 -1.380 .350 TM TDTH CDA CDM CD

-9417.0 1 . 000 -

. 4(:)70 , 932(:) 0. C)

C L E F CMDEP CUDEF'

( : I . ( : ) . 74(l - . 26(j

DIMENS IONfiL D E R I V A T I V E S : X W

XU xu *

-. (3888Ei -. 159(j28 . 05984

ZWD

ZU z u *

- 7.7-n

-. 32.32 . .-,-.>A

i ) . o MWD

MU MU *

(j . (j

(j . (j (1) . (3

MAD MA MQ

-.- . x . , 14

(j . (j 1.1986

MDEP XDEF' ZDEP

-. 8904

i j . -15.999

MDTH XDTH ZETH (5 ,

! : I . ( : I

. i:)O(:) 16572

DATA F I L E NAME : A:FWLANUSA.SA O L D file, w r i t e over- it Y / N ) ' ? Y I.J , W , T " E . D D , A Z .AZ',HD , E n t e r no. 5 f eqns to o u t p u t ft-om 4 thr-u 7 F L Y INGW I NG/L_UND TNGiUNSTABLECt"IG/SL/HEAVY

i-. 745) ( 1. so1 ! c .251: .237

DEPJDEl IPJATOR: ORlGlNAL PAGE !S OF POOR QUALtTY B-26 FLYINGWING/LANDING/UNSTABLECONFIG/SL/HEAVY DTH NUMERATORS: FLYINGWING/LANDING/UNSTABLECONFIG/SL/HEAVY DEF'IDTH COUPLING NUMERATORS: N (L!-DEP/W-DTH) N CC!-DEF'/THE-DTH) N (U-DEP/DD-DTH) N i U--DEP/AZ-DTH) N (LJ-DEF'/AZ '-DTH) N iU-DEF'!HD-Ul'Hi Pl iW-DEPiTHE-DTH!

B-27 N ( W-DEF i'DD--DTH i N (W-sEP/AZ-DTH) N(W-DEP/AZ'-DTH) NIW-DEP/HD-DTH) N (THE-DEP/DD-DTH) N (THE-DEF/AZ-DTH) N (THE-DEP/AZ '-DTH) N (THE-DEF/HD-DTH) N (DD-DEP/AZ-DTH) N(DD-DEP/AZ'-DTH) N(DD-DEP/HD-DTH) N (AZ-DEF/AZ '-DTH) N(AZ-DEP/HD-DTH)

rd ( ~ z '-IIEP/HD-DTH)

B-28

-

I I) a P 3 - w 3 . 5 2 - La1 s Figure B-15. Unstable Configuration Root Locus P l o t B-3 0

ORIGINAL PAGE I S

OF POOR QUALITY Elevator Response to a Unit Step Theta Comand 0 1 2 r u t

-6 P I I i I I I I I i

a i0 20 38 48 Tine Elevator Response to a Unit Step Theta Cowand 0 12 1 .:cl .--

U - I *. 1

I

-24 I I I I I I I I I I

Q 1 2 3 4 5 Tine Figure B-16. Unstable Configuration Elevator Response B-3 1 Iheta Response to a Unit Step Theta Colmand &

-

. 2 8 - - - . 2 . I I I I I I I I I

e 10 2a 30 40 5

Tine Theta Response to a Unit Step Theta Connand 0 1 . 6 I l!?

U ./.=------- t 1 . 4

---

--- '-.- -.

: 1.2

1 ; 1%

t

- - -

.8 . 6 .¶ . 2 I I I 1 I I I i I - . 2 8 1 2 3 4 F i g u r e B-17. Unstable Configuration P i t c h Angle Response B-32 1 C f L

68 58 - - ff ---- //

--.--.

48- -.---- /-

- /- /

/-

-4 I 1 I I I I I 1 1

a 1 2 3 4 5 Tine Figure B-18.

Change In Altitude A t The Pilot For The Unstable Configuration B-3 3 H a t CC Response to a U n i t Step Theta Comand ! cc 0 70 /--- L U /--- t 60 /-.---- /” -----

p t t !ieC z . e/-

---e- .--.

./-- 4 q - /- -e--

30 1 ---*

/--- -.-, c

4- ,-=

lfd 1 -/

-10 ! ! I 1 I I I I f I 9 10 28 38 40 5 Tine -4 I I I I i I I I i 0 1 2 3 4 Time F i g u r e B-19. Change I n A l t i t u d e A t The CG For The Unstable C o n f i g u r a t i o n B-34 /' /-.---/- 20-

- /-

- / J e

-

i I I I i I I 1 I I -10 I f CI // 8 - I- -4 I I I I I , I I 0 1 2 3 4 T i m e Change I n A l t i f u d e A t The Prop Tip F i g u r e B-20.

For The Unstable Configuration B-3 5 E l e v a t o r - TF: Stable ( h i g h gain case) E l e v a t o r TF: Unstable

ORlGlNAL PAGE I S

OF POOR QUALKY B-3 6

CRUISE

B-37 GPI)O€, STfi&E [if Is-1)

Input File Name; ,f I \ J , ~ lfflT~ -1 \ I . I I I&& Output File Name; , I I , I , I I I

AFTF LATERAL NONDIMENSIONAL I N P U T Flight Condition Identifier; G C I : 60 Characters or Numerals \ J l \ lt4 bl / I f I R t U t \ IS L I I I S rTrA16 IL 16 I / ICI L I= I, 13Gl /I LInlfrDII I f 1 l F * L t Y I I I I I 1 -e.

# of Controls b u t not Gust: S 6

With Gusts - 1: WIO Gusts - 0

Polynomial Coeff. 8 - 1; Without 0 0

I

w i t h C K G NIW - 1: without - 0

Savr Eqn. - 1; WlO Save Em. 0

Lat.

-

1 NRHS NG NPC 1 0 I C C IS I,( slg- f t2) I,(slg-ft2) Ixz(slg-ft2) W( l b ) S ( f t 2 ) b( f t )

59pqa23- I 4&5f2ilz 9 0 , w t !i@L , 1 7 2

(hCft) if p - 0 ) MACH Control Symbols (except thrust) 61,2,. ..6. U s e 3 characters; l e f t justified: ~ ~ ~ 9 - 9 - 9 - ~ ~ B-38 ORIGINAL PAGE IS OF POOR QUALITY # of Controt but not Gust; I 6

w i t h Gust8 - 1 : w/o Gusts - 0

Po1ynd.l CoeZf. .- 1; Without - 0

Save Eqn. .I 1 : WlO Save Eqn. 0 I,( slg-f tZ) I,(slg-ftz) I,, (slg- f t2) W ( lb) S ( f ~ ' ) b ( f t) 3\a= 8 9 - , b BW3 * . I r ) L ) . , Control Symbols (except thrust) 61,2,.,.s. Use 3 characters; l e f t justified:

Q A i & ! ! I - - - -

B-3 9 FiFTF F I L E NAME : GEDMETRY : V T ALPHA GAMMA L X L Z

629.0 0 . (j (j . 0 (j . (j (1) . 0

I X I Z I X Z AG A L T I T U D E

..39 1 1 E+7 .43 15E+7 0 . 0 (j . ( : )

s B RHO W A

28Wj. I:) 144. (3 . 0(:)0589(:, 194140. 968.1

N0I.J-D I MENS I O N A L C Y B

-. 152(j

C L F

- . 343:)

CYDEA

(j . (j

CYDSR

(:I . (1)

TPFN O A T A F I L E lzlAME : A : F W L A T C B l . S A V ilL.0 -File? wt-itcl llvet- i t i Y / N j.7 Y € 3 ?F' . R . F H I , A Y , i A L i ?

Entei. no. of eqns t u o u t p u t ; from 4 t h r u 6 6

ORIG4NAL PAGE I S

B-40 OF POOR QUALITY F L Y I NGW I NG/CRUISE/UNSTABLE/CL=. 3 7 / L A T D I H DEA NUMERATORS: FLYINGWING/CRUISE/UNSTABLE/CL=.37/LATDIR DSR NUMERATORS:

- .(:I762 ( - . 0 1 1 1.3 1 ( .483 1 e : . 000409>

N (E-DSR 1 N (P-DSR 1 . 00799 (0. 0 ) ( 5 . 27) -<. 0 4 2 1 > .

0 2 - 0 8- 8 8 10: 14: 38 AFTF completed B-41 I X I Z I X Z AG ALTITUDE

. S579E+7 .6156E+7 (1) , 1 : ) ( : I . (3

NON-DIMENSIONAL CYE

-. 138(3

CLF

-. 543(:)

CYDEA

. i:)

CYDSR

0 . 0

UNFR I MED I> I MENS I ONAL DER I VAT I VES: ii v LE NB

- . 0 16344 -. 4712 . 2(:) I &

L F' NP LR N W

-. 6738 -. (54664 .14102 -. (:)13351

YDEA LDEA NDEA

( : ! . r : , . b0Sb -. (:)zv(jb

YDSR LDSt7 m s R

1 : ) . ( : )

0 , ( 1 , . iI9 1 1 4

TRFN D A T A F I L E NAME : A: F W L A T C c i l . SAV

OLD t'ile, wt-ite o v e r i t i Y/" i ? Y Y ?F' .R ! F " I , A Y , L A D , En h e r - nu. o f eqns t u o u t p u t f r o m 4 t h r - u 5 6 B-42 DSR NUMERATORS: N ( E-DSR i N ( P-DSR 1 N ( Fi-DSR) N !PHI -DSRj N (Ai/-DSHj 1\1( I.-AL!-liSFi: AF'TF c o m p 1 et ed 8-43 GEOMETRY: LX LZ VT QLPHA GAMMA

5) , (j 0. (2 (2 . 0

456. 0 (I. i) I X IZ IXZ AG ALTITUDE

.5579E+7 .6156E+7 0 . (1) . 0

W A S B RHO

4 i : ) (1) (:I . ( : I 172.0 , 1 C t 3 6 . 9

(3:) 1267.3 1941.10.

NON-DIMENSIONAL CYE

-. 152(:)

CLF

- . 3433

CYDEA

. (1)

CYDSR

( : I . (j

- r w N D A T A FILE NAME : A : F ' W ~ - A T C A ~ . ' S A V OLD file, wt-ite over- i t i i ' / N ) ' ? Y B ,I:- , i ~ ,F"I,AY ,LAD, E n t e r no. o f eqns t o o u t p u t ft-om 4 tht-u b L ~

FLY I NEW I NG ,' S -iXiJ I SE / STABLE / CL= .3 7 / L A T D I Fi

B-44 ORIGINAL PAGE IS OF POOR QUALITY AFTF completed B-4 5 GEOMETRY : V T ALPHA GAMMA LX L Z c ,J39 a 0

< : ) . t : ) ( : ! . (5 (5. 0 0.0

I X IZ I X Z AG CILT I TUDE

.39 1 1 E+7 .43 15E+7 0 . 0

0 . 0

TRFI'J D A T G F I L E NAME : A: FWLATCB2. SAV 01-11 f i l e , w r i t e o v / e t - i t 'Y/N i ' 7 Y B ,P ,I3 , F ' ! - I I , A Y , L A @ , E n t e r - ni3. Pqns ta o u t p u t $t-orn 4 t h r u S 4

--. 01879; .6191

B-4 6 B-4 7 A F T F F l L E N A M E : 0 2 -i:I8--88 10: 17: 45 N O N - D I M E N S I O N A L C Y E

- . 1 520

c L I='

-. 3430

CY D E A

( 1 ) . i:)

CYIjSR

0 . (7

, B-48 .

B-49 .

AG I X IZ IXZ ( 3 . 0

. 11683E+7 . 12892E+7 ( : ) . ( : I

UNF'RIMED O I M E N S I O N A L D E R I V A T I V E S : Y s LB NB

-. (134652 -. 9706 .3278

LF' NP L R NR

.3736 - . (113 1 ( 1 1 6

-1.6756 -. 12.3.37

L D E A NDEA 'YDEA

-. 11 117

1. C)152 ( 1 ) . i : , L D S R NDSR YDSFi

. 13418

(2. (2

( 1 ) . ( 1 5

B-50

ORIGINAL PAGE I S

OF POOR QUALITY C ORIGINAL PAGE I S OF POOR QUALITY B-51 2. Government Accuion No. 3. R r i o m t ' s Gulag No.

1. Report No.

NASA CR-181806 March 1989 Tailless Aircraft Performance Improvements with Relaxed Static Stability 8. Performing Organization R I p o n No.

7. Author(s) Irving L. Ashkenas and David H. Klyde STI-TR-1252-1 10. Work Unit No.

9. Performing Organization Name and Address 505-66-01-02 c Systems Technology, Inc.

11. Contrm or Grant No.

13766 South Hawthorne Boulevard NAS1-18524 Hawthorne, CA 90250 13. T y p of R m n d Parid Covwd 12. Sponsoring Agency Name n d Addrar

CONTRACTOR REPORT

National Aeronautics and Space Administration 14. Sponuwing Agrncy b6 Langley Research Center

Hampton, VA 23665-5225 I

-.

1s. S u ~ e m e n t a r y Notes Langley Technical Monitor: William D. Grantham 16. Abstract The purpose of the work reported here is to determine the tailless aircraft performance improvements gained from relaxed static stability, to quantify this potential in terms of range-payload improvements, and to identify other possible operational and handling benefits or problems. Two configurations were chosen for the study: a "modern" high aspect ratio, short-chord wing proposed as a high-altitude long endurance (HALE) RPV; a wider, lower aspect ratio, high volume wing suitable for internal stowage of all fuel and payload required for a manned long-range reconnaissance mission. Flying at best cruise altitude, both unstable configurations were found to have a 14 percent improvement in range and a 7 to 9 percent improvement in maximum endurance compared to the stable configurations. The unstable manned configuration also shows a 15 percent improvement in the 50 ft takeoff obstacle distance and an improved height response to elevator control. However, it is generally more deficient in control power due t o its larger adverse aileron yaw and its higher takeoff and landing CL, both due to the downward trimmed (vs upward trimmed for stable configurations) trailing edge surfaces.

17. Key Words isuggested by Authork) J 1 18. Distribution Statement

tailless, relaxed stability,

UNCLASSIFIED - UNLIMITED

improved performance, flying wing, Subject Category 08 control power 19 Security O m f . (of rhis rcmrtt 20. security Clauif. (of this page) 21. No. of Plgar 22. Rice

Unclassified 1 140 A0 7

Unclassified I For sale by the Nailonal T e c h n c a l Inforrnatlon Servlce. S p r q f l e l d . Vlrgl'nla 22161