NACA-WR-L-288 · Wind-tunnel investigation of an NACA full-span high-lift lateral-control combination I : section characteristics, NACA 23012 airfoil

NASA (NTRS) · 1942

Open the PDFPublic domain · NASA (NTRS)Technical Reports

Overview

The Wind-tunnel investigation of an NACA full-span high-lift lateral-control combination I : section characteristics, NACA 23012 airfoil (NACA-WR-L-288) is a public-domain NASA (NTRS) technical report, republished here as a free chaptered HTML edition with a linked table of contents and the official PDF.

Pages: 31
Chapters: 3

Key points

The investigation was conducted in the NACA 7- by 10-foot wind tunnel to determine the aerodynamic section characteristics of a full-span high-lift lateral-control combination using the NACA 23012 airfoil.
The combination consists of a full-span flap that retracts ahead of a narrow-chord full-span aileron, which provides lateral control in all flight conditions.
Tests showed that the combination produced lift coefficients comparable to other slotted flaps while also providing effective lateral control.
The study included various aileron and flap angles and slot widths to determine the optimum arrangement for high lift and lateral control.
Results indicated that while the combination offered satisfactory lateral control, there was an increase in pitching-moment coefficients compared to the Fowler flap.

Frequently asked questions

What is the purpose of the wind-tunnel investigation?

The purpose of the investigation was to determine the aerodynamic section characteristics of a full-span high-lift lateral-control combination using the NACA 23012 airfoil.

What are the main components of the high-lift lateral-control combination?

The main components are a full-span flap that retracts ahead of a narrow-chord full-span aileron, which provides lateral control during flight.

How does the performance of the combination compare to other flaps?

The combination produced lift coefficients as high as other slotted flaps while also providing effective lateral control.

What variations were tested in the investigation?

The investigation tested various aileron and flap angles and slot widths to determine the optimum arrangement for achieving high lift and adequate lateral control.

What was a noted drawback of the high-lift combination?

A noted drawback was an increase in pitching-moment coefficients compared to those of the Fowler flap.

Section liff coefficient, c2

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 .

Next: Section lift coefficient, c2 →

Section lift coefficient, c2

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.

Next: Section lift coefficient, c Z →

Section lift coefficient, c Z

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 .