Two-Dimensional Wind-Tunnel Investigation of Modified NACA 65(112)-111 Airfoil with 35-Percent-Chord Slotted Flap to Determine Optimum Flap Configuration at Reynolds Number of 2.4 Million

configuration that is the optimum for high l i f t at lm Reynold8 m ~ b e r 8 is still the opthum coafiguration B t nuoh M a r Reynolds nWem section angle of attack, degress d r f o i l chord eect.ian l i f t coefficient horlzon"a1 end vertical positiom, reepeatively, of the flap leaCing-e&e railiua cen%er with reagect to upper lip of 810% in perneat c, positive fxward. of and below slot l i p , respectively (fig. I) W A RM No, L7A02 MODEL AND TESTS

4 NACA m NO. ~ 7 ~ c 2

CONCLCSIOYS The results of t e a t s of a modlfied I U C A 65(112j-A 11 alrf o i l section with a O.3whord elotted flap indioate the follming O C ; k G l ~ i O R f ? a 1 p r the optfmum configuration at a Reynol &E m b e r of 2 , 4 X 10 the flap deflection was 45" and the flap leadi;.-Qe radlus center vae 0,73 percentrchord behind end 4,46 perceahhord below the slot l i p .

Langley MemrL&l. Aer%nautlcal La3oratorg Baticnal Advisory Ccmmlttee f o r Aeronautice Langley Field, Va;

NACA RM No. L7A02

~ L . E . rad Upper surfaoe fairs i n t o p l a i n a i r f o l l s e o t l o n at station 8a.W I ( a ) A i r f o i l with 0.350 s l o t t e d f l a p .

(b)Variables w e d t o define f l a p conflguration.

Flgure I.- Profile o f the nodifled HACA 65(u2)-111 a l r f o i l section with 0.35~ d o t t e d f l a p .

I . . . . .

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F

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.

.. ...

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Fig. 3

NACA E L M No. L7A02

x 3 r ' (peroent c ) 0.10 L.87 I ..

I ...

a _ !

J r I

NATiONAL kDVlSdRY i COHHITTEE FOR AERONAUTICS I !

Figure 3.- S e c t i o n lift ch&racteristics of the modified MACA 65(1~)-111 airfoil s e c t i o n

with a 0.35~ slotted f l a p . R = 2 . 4 x 10 6