Wind-tunnel investigation of an NACA full-span high-lift lateral-control combination I : section characteristics, NACA 23012 airfoil

Section liff coefficient, c2 cbj S q = / O o ; pap = O . O / G c - FtcuRE 7- Contiwued.

I ' I - 5ection l i f t c o e f f i c i e n t , c2 C C ) S , = / 5 " j p a p = 0 . 0 / 8 C .

F G U ~ . E 2 - Gontifiued ~~ ~~ ~~ f;- L

*

w Section Iif t toefficient, cz (d. 1 Sa= IS O; 6 , . 40'.

~ ~ G U R E ?*- co#c/uded.

~ e c t i o n iift coefficient cL

FIGURE 8 - Aerad’namic s e c t i o n characterisfics of an N A C A 23012

airfoil w i t h a 0 . 2 S c r e t r a c t a b l e slotfed f h p and an 0108~ S4- 30; p a p w (3.0/4 c .

s l o t f e d aileron E .

Section lift coefficient, c2 Ca.1 &= O:j qap= 0.0/5c.

F i w R E 9- Aero&namic section characteristic s o f an NACA 230/E airfoil w i t h a O.l& r e t r a c t a b l e slothd f l a p and a n 0 . 0 8 ~ plain a i h o n .

5ec t ion Iif t coefficient ,, cz SP=/50; pap- O . O / B c .

F/GU+E 9 . - Conc/oded.

Section lift coefficient, c Z EGURE lO.-Aerod>numic s e c t i o n c h a r a c t e r / s f i c s of an NACA 23012 a i r f o i l with Q 0 . 1 5 ~ retractable slofted flap a n d a n 0.08~ 30; g a p z 0.014 c.

slofted ‘aileron 2 .