Mckinney, Marion O , Jr

English

NASA Technical Reports Server

ARR No. L5J02 
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS 
ORIGINALLY ISSUED 
January 1946 as 
-Report L5J02 
EXPERIMEIJTAL -ION OF TEE EFFECT OF 
mEGATIyE DIIEDRAL OR LATERAL STABII,m7c-_- 
AATD COIWROL CHARAC7REUSTICS KC HIGH 
LIFT COEFFICIEmrS 
By Marion 0. McKinney, Jr. 
Lan&ey Memorial Aeronautical Laboratory 
LRng7ey Field, Va. 
WASHINGTON 
NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of 
advance research results to an authorized group requiring them for the w a r  effort. They were pre- 
viously held under a security status but are now unclassified. Some of these reports were not tech- 
nically edited. All  have been reproduced without change in order to expedite general distribution. 
L - 54 
https://ntrs.nasa.gov/search.jsp?R=19930092558 2020-06-17T01:12:50+00:00Z
NACA A-F~ NO. ~ 5 ~ 0 2  
N AT I ON AL AD'J I S 02Y C OV?: ITTEE 7 0 E AT30 N AUT I C 3 
The e f f e c t s  of  nego t ive  uihedre.1 011 1Ptejqal s k e b i l i t y  
and c o n t r o l  c h a r a c t e r i s t i c s  at h i g h  l i f t  c o e f i ' i c i e n t s  nave 
.been  d e t e r n i n e d  by f l l g h t  t e s t s  o f  e zodsl i n  t!:~ Lansley 
f r e e - f l i g h t  t u n n e l .  The geometr ic  dihsdr-c.1 ai1El.e of  the 
model wing was v r r i e d  from 00 t o  - 2 O O  aiid the v e r - t i c e l -  
t a i l  a r e a ,  f rom 0 t o  35 .percent of  the wing area.. The 
model wzs f l o ~ f ~ i ?  tvith v c r i o u s  coxb inz t ions  o f  d i h e d r a l  angle  
and v e r t i c a l - t s i l  s r e a  a t  l i f t  coef$fcLer;ts  of  l.G, l..k, 
and 1.2. 
I n c m a s i n g  t h e  d i r e c t i o n 2 1  s t e b L l i t g  reduced  t h e  
nafgnitude c:" t h e  sideslip snci i m . ~ r o v e a  t h e  g e n e r a l  f l i g h t  
behEvior .  I n  t h e  nepa-Live e f f e c t i v e - d i h e d r a l  rang,e, 
i nc rea . s ing  t h e  l i f t  coe:f'i?icierit from 1-0 t o  1.8 had E 
slli,r,htlg d e t r i m e n t e l  e f f e c t  on t h e  g s n e r a l  f l i g h t  e k a v f o r  
of t h e  model S t  any g ivgn  v z l : ~  of e f f e c t i v e  d i h e d r a l  aiid 
d i r e c t i o n a l  st a b i l i t y .  
2 
V 
m 
s 
St 
b 
v 
m 
x k 
kZ 
R 
D 
x 
p 
Y 
r 
;pass of  n o d e l ,  slclgs 
wing s r e z ,  s y u ~ r s  ? e e t  
v e r t i c a l - t a i i  a r e ? ,  square f e e t  
wing span,  f e e t  
f r e e - s t r e a n ,  v e l s c i t p ,  f e e t  second 
3 
r s d i u s  of g ; r ~ ; t i o n  of xoc!el aSo-Lt Lopg i tud ina i  m i s ,  
f e e t  
c o e f f i c i e n t  i n  s t a b i l i t g  quart i .c  e q u s t i o n ,  g ivan  in 
r e f s r e r l ce  2 
coel"f l c i s n t  ir, s t ,c ib i l i ty  qus-tTc e q u c k i o c ,  g iven  i:i 
r e f e r e n c e  2 
roots of  s t a S i i i t g  quFr t i c  s q u a t i o n  
gawfng angul?F v s l o c i t g ,  radians F e r  second 
4 NACA A X  Fo. L5ZO2 
- CL aiT.aplene r e12 t ive -de rLs i tp  f o c t o r  
7 
CL 
CY 
i m  
\PSV t iiie - c onve ?- s i o n  f ac t o r  \ -) 
l i f t  c o e f f f c i e c ,  
l a t c r z l - P o r c e  c o e f f i c i e n t  - ' qs ' L a t e r a l  f o r c e  -j \ qs 
30 11 in. aonsnt )  
C rolling-,nori,ent coei'f i c i s n t  -------- (, qSb / 
r a t e  of chsnge of ro l l ing-moxent  coef f ' i c  ie r , t  w l t h  
2, C 
. I  
I 
Tha c o n t r c l  used 011 f r e ~ - C l i & t - t i x x > e l  n o 2 e l s  i s  a 
f f f l . ickep 11 ( f f ;~. l I . -on cr f u l l - o f f )  s y s t e x .  During a?iy one 
Tau . t i ca l2 r  r l icht  t k s  c o c t r o l  d e f l e c t  i o m  i n  t i ie f u l l - o n  
p o s i t i c i i s  ?re c o n s t e n t  ~ . n d  the ainount of control a2;lied 
t.o the no&.el is r e = u l e t e d  by th.e l e n g t h  of  t i p i e  tiis con- 
trols me hs ld  on r e . t h z r  t h r a  'cy tho c o r i t ~ ~ 1  d e f l e c t i o n s  
used. 
. 
S c c p  of  T e s t s  
i i 2  
! 
. o j  
05 
I i 0, -5, -x9 -15, -20 I 
, c y  -5, -10 I I I 
NASA A?? f T O r  L5 JC2 7 
Test ing  Procedure 
The genera 1 o s  c f li at or:: s t aSi 1.; t y c1ie.r actorJ  i s  t f cs  
were judged by ths p i l o t  f rom th3 clxqii::g of t k e  l a t e r a l  
o s c i l l s t i o n s  cf the m i e 1  ~ f t s r  a dis tu?bzcce.  The x o d e l  
coulc! never be a1lov;ed t o  f l y  with conti.cls f i x e d  for 
s u f f i c i e n t  tflne t o  allow n:ea::urement c t  ;!eriod a.nd iimbi5rig 
froin t h e  niotion-yjisture recozds. 
VACh K?.i No. LTJ'32 8 
* 
I t  
NACA A?? No. L5JG2 
H2SUSTS AND DTSC!JSSIOY 
9 
The v a r i s t i o n s  of s f : ' ec t ive-dfhe&ral  p a r a n e t e r  
C z p  
a nci d i r e  c t  i o n a l - s  t ab i li  b y  p s r  2uie t e r  Cno wera o b t a i n e d  
, 
i n  t h e  ? r e s e n t  
d ihe? . rn l  angle  
c h a r s c t e r i s  t i c s  
inva  s i; i 3 2.t. i o n  by ch angi  ng t h e  g e  one-L r i c 
znd v e r t i c a l - t a i l  aiqe8. The, f l y i n g  
, hoi-Tever, de?end on t h e  vsl.l;ss of the 
stab4.1-ity d e r i v s t i v e s ,  not, on t h e  inethod by which t>iey 
v;:ere ob t , ; iced; kence t h e  flyin;;  cha r sc , t e - l s  t i c s  of t!-e 
model mag be ? .ysl i$d t o  condi t5ons - szch 8.s -xaT,r2-o1'f', 
t a k e - o f f ,  and lending-ac?ro&ch - i n  which naZa"si.ve 
e f f e c t i v e  d i h e d r a l  i s  or5en C ~ : L S P , ~  by Lhe hi@ power end 
h i g h  l i f t  c o e f f i c i e n t .  
The pr inc i - ; ?a l  res:j.lts of t h e  ;?L-asent i n r z s t i g s t i o n  
m e  g i v e n  i n  f i g u r e  6 i n  t h e  i'orn- of r a t i n g s  of t h e  
g e n e r e l  flight Seha.vior. All flight ratings riot i n  
? m e n t h e s e s  weye o S t s i m d  c i t h  a to t2 . l  ? . i l e ron  d e f b c t i o n  
of 300; t hose  i n  ?n:.-enthsses xe re  obtp.ined w i t h  8 t o t r . 1  
aflei-or, d e f l e c t i o n  of 50'. Tile naxir! iu~ v a l u e s  of  7b/2V 
co r re spond ing  t o  t h e  a . i l 4 ron  d e f l s c t i o n s  cf 30c and 50° 
were determined t o  be e'bout 0.08 end 0.12, r e s p e c t i v e l y ,  
f rom roll-offs st a geometr ic  CiihedrP1 a n s i a  of O o ,  with 
t h e  v e r t i c e l  t a i l  ha.ving - - 0.15, with cool3dlnated 
rudder .  I t  I ~ " A S ,  p z r k a ? s ,  no t  n e c s s s a r y  to use  Rn aileron 
e s f l e c t i o n  of 50° f o r  sll t h a  t e s t  p o i n t s  a t  vk~ ich  t h i s  
i n c r e a s e d  t r a v e l  was used. .&hen it  was fourid necesse ry  
t o  u se  500 t r a v e l  1tiith a. c e r t a i n .  cornbination of d i h e d r a l  
angle end v e r t i c a l - t a i l  w e 2  a t  a l i f t  c o s f f i c i e n t  of 1.8, 
t h s  sprne t r a v e l  wzs used a t  lower l i f t  c o e f f i c i e n t s .  
.3 t 
S 
E f f e c t  olf Dihedpal 
10 L5 502 
s t p b l e  a n d  i n  the? n o r m 1  p e t y  air 0;' t n e  t u n n e l  d i d  n o t  
eeom t o  requii-e more f r e q u e n t  co r - t ro l  t h a n  In a spirally 
s t a b l e  c o n d i t i o n .  
BACA km Y O .  ~5 ~ 0 2  11 
12 
\ 
E.fI 'ect  of D i r e c t i o n a l  S t a b i l i t y  
inpraoved 
Cn$ 
Tacrea.siric the d i m c t ; i o n a l  s t a b i l i t y  
the geneTa.1 f l i g h t  behev io r  of the iyodel ove r  the range 
of dihedi-a1 sn53.e~ and lift c o e f f i c i e n t s  t e s t o d ,  as s h ~ m  
i n  figure c.  f-l 
. 
E f f s c t  of  L i f t  f7oe f f i c i en t  
The f l i g h t  r a t f l i p s  of f i g m e  8 show t h a t  i m r a 2 s i n g  
t h s  l i f t  c c e f f i c i e n t  f r o x  1.0 Lo 1.3 p.t coilstant; v a l a e s  
2nd C h a d  a slightly dekrirnentel  c f f e c t  on of czp "r, 
P 
t h e  gene ra l  f l i & t  behavior* of t h e  m o 6 e l  over die  ridgstive 
effectiv3-dihi3drs. l  r,?fig$. This det?fc;entsil e f f e c t  is 
b l l e v e d  t o  be csused by $he increa.ze i n  t h e  i-R-Le of' s p i r a l  
uivergence ind?lcc.ted by t he  caicullateci l i n a s  31' coirs-La.nt 
dmpkrig shown ir, ficum 9. 
. 
2. 'Lirmerran, C h e r l e s  5.: An ka1:Tsi.s o f  L a t e r a l  S t a b i l l t y  
iil  Fowsr-Off Flight w i t h  Chapts f o r  Tlse i n  Design. 
Y X k  Rep. No. 563, 1937. 
N A C A  A R R  NO. L5J02 16 
-0,066 
- e o 8 0  
-00 7 
-.060 - 04i 
-.03 
-0025 
-.015 
- 0  -*:% 
-.oi3 
TABLE 1,- STABILITY DERIVATIVES OF MODEL USED I N  CALCULATIONS 
- 
0.340 -0 . 040 
342 - . 048 
-. 115 347 354 . 360 -0153 
367 . 380 
343 - 053 
- *% . 
::g; :E 
0.07 
-0491 -412 
Ealues were arbitrhri ly  assigned to Cn , 
was used aa the dependent variable. 
the independent var iab le ;  
p = 8.12; 
P 
kx/b = 0.165; 
kz,& = 0. a 4  
CI = 1.0 
-0 . 108 
- e  121 
-0  135 
-0  175 -. a2 - . 308 
-0378 
::E2 
-0775 
-0909 
0 . 005 
0010 
.025 
050 
075 . 100 . 150 . 200 
. 300 
-0.49 
0.49 
0.49 
0.49 
0.49 
0.49 
0.49 
9.49 
0.49 
-049 
-049 
0 
-005 . 010 
.025 . 050 
075 . 100 . 150 . 200 . 250 
.300 
-0 49 
-049 
-049 
0.49 
-049 
-049 
-*49 
9-49 
-049 
-049 
-49 
0 . 005 . 010 . 025 
050 
075 . 100 . 150 . 200 
250 . 300 
~~ ~ 
-0.49 
0.49 
0.49 
-*49 
-049 
-049 - 049 
0.49 
0.49 
0.49 
-049 
'p I s  mbasured i n  radians.  
-0.060 
-.056 
-.031 
. 015 
- 058 
-00 's" 0 
. e  *% 
-. 921 
-.002 
C r  = 1.4 
0.&6 
248 
-250 
303 . 320 
337 
353 
-0 . 040 - 0048 
-.07 
-.115 
-0153 -. 190 
- e  265 
-.491 
-0053 
-*Jg . 
-0.14 -. 113 -. 112 -. 110 -. 106 -. 103 
0.099 
-.082 
-.0g2 0  5 
- 0  078 
-11.6 
-13.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-.11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-11.6 
-0 040 
-.07 -. 115 
- 0  153 
-. 340 
-.413 - 0491 
- 048 
-.053 
-*lZO 0.2 5 
-13 5 
-13.5 
-13.5 
-13.5 
-13.5 
-13.5 
-13.5 
-13.5 
-13.5 
-13 5 
-13.5 
NATIONAL ADVISORY 
COMMITTEE FOR AERONAUTICS 
Fig. 1 NACA ARR No. L5J02 
c 
I 
7 20' 
J NATIONAL ADVISORY COMMITTEE FOI AERONAUTICS 
Fiyure l. - Three- view sketch of model fesfed In L a n  ley 
free - f//phf funnel rhowing ran9 e of d'hedral 04us P menf 
and olfernafe vert ical-  fa// arrongemenfs. 
N A C A  A R R  NO. L5J02 Fig. 2 
NACA A R R ' N o .  L5J02 
. 
i 
Fig. 3 
4 
W ' a  
0 
E 
k 
0 
3 a), 
* .rl 
N A C A  ARR NO. L5J02 Fi g .  
r i  
a, 
E: 
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3 
4 
4 
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an
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Fig. 6 N A q O  ARR No. L5J02 
Fig. 7 NACA ARR No. L W 0 2  
. 
NACA ARR N 6 *  L5J02 ' 
6.p rn 


Experimental determination of the effect of negative dihedral on lateral stability and control characteristics at high lift coefficients

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