NACA-RM-L7A02 · 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

NASA (NTRS) · 1947

Open the PDFPublic domain · NASA (NTRS)Technical Reports

Overview

An investigation has been made in the Langley two-dimensional low-turbulence tunnel to develop the optimum configuration of a 0.35-chord slotted flap on an NACA 65 (112)-111 airfoil section modified by removing the trailing-edge cusp. The results of the investigation indicate that for the optimum…

Pages: 13
Chapters: 2

Key points

The study investigates a modified NACA 65(112)-111 airfoil with a 35-percent-chord slotted flap.
The optimum flap configuration for high lift at a Reynolds number of 2.4 million was found to be a flap deflection of 45 degrees.
The flap leading-edge radius center was located 0.73 percent chord behind and 4.46 percent chord below the slot lip.
The research was conducted at the Langley Aeronautical Laboratory.
The results provide insights into flap configurations that enhance lift characteristics of the airfoil.

Frequently asked questions

What airfoil was tested in this investigation?

The investigation focused on a modified NACA 65(112)-111 airfoil section.

What was the Reynolds number during the tests?

The tests were conducted at a Reynolds number of 2.4 million.

What flap configuration was determined to be optimal?

The optimal flap configuration was a deflection of 45 degrees.

Where was the research conducted?

The research was conducted at the Langley Aeronautical Laboratory.

What does the study aim to determine?

The study aims to determine the optimum flap configuration for high lift.

Section 1

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

Next: section with a O.3whord elotted flap indioate the follming →

Section 2

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 .

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Fig. 3