[PDF] WIND TUNNEL TESTS OF THE GA (W)-2 AIRFOIL WIH 20% AILERON, 25

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WIND TUNNEL TESTS OF THE GA (W)-2

AIRFOIL WIH 20% AILERON, 25% SLOTTED FLAP,

30% FOWLER FLAP, AND 10% SLOT-LIP SPOILER

WICHITA STATE UNIVERSITY

WICHITA, KS

AUG 76

AR 76-2 Aeronautical Report 76-2

Wind Tunnel Tests of the GA(W)-2

Airfoil with 20% Aileron, 25% Slotted Flap,

30% Fowler Flap, and 10% Slot-Lip Spoiler

by

W. H. Wentz, Jr.

(NASA-CR-145139) WIYD TOTINEL TESTS OP THE N79-100 2 1

GA(P)-2 AIRFOIL WITH 20% AILERON, 25%

SLOTTED FLAP, 30% FOWLER FLAP AND 10%

SLOT-LIP SPOILER (Wichita State Unir.) 75 p Unc las

HC A04/tlIP A01

Report of Research Conducted Under NASA Grant NSG 1165

Prepared

by

Wichita State University

CSCL 01A 63/02 35694

___--- - - -- L - - - - - - .

Wichita, Kansas

for

NASA Langley Research Center

August

1976

WRODUCfD BY

NATIONAL TECHNICAL INFO

R M AT I ON S ER VICE

us mawmi i mutnct &RMCllttD. \A 22161

4 Tire Wd Subtitle

WIND TUNNEL TESTS OF THE GA(W)-2 AIRFOIL WITH 20"; AILERON, 25': Slotted Flap, 30% Fowler Flap and 10%

Slot-Lip Spoiler

W. H. Wentz, Jr.

7 Ab:horlsi

Wichita State University

Wichita,

KS 67208

12 Sponsor,ng Agency Yame and Address

National Aeronautics & Space Administration

Washington,

DC 20546

Langley

Monitqr: Robert J. McGhee

15 LcCte~e-ldry Nio:cS

3. Recipient's Catalog No.

5. Repon Oete

Januarv 1977

6. Performing Orpanization Code

8 Performtng Organoation Report No

AR 76-2

10 Work Unit No.

505-06-33-1 0

11 Contract or Grant No

NSG-1165

13 Type of Repon and Period Cavefed

Contractor Report

14 7:torwving 4gency Code

:6 Ahi*a:l Tw3-dimensicnal wind tunnel tests have been conducted for the GA(W)-2 airfoil section with: spoiler.

Number

of 0.13. the slotted and Fowler flap configurations. obtained by integration of surface pressure measurevents.

20@! aileron, 25'; slotted flap; 30" Fowler flap and 10'1 slot-lip

All tests were conducted at a Reynolds number of 2.2 x lo6 and a Mach In addition to force measurements, tuft studies were conducted for

Aileron

and Spoiler hinge moments were

Tests results show

that a chax value of 3.82 was obtained with 30% Fowler flap. Aileron control effectiveness and hinge moments are similar to other airfoil

The slot-lip spoiler provides powerful, positive

roll control at all flap settings.

I! Kek Words (Sugges:ed by Autborls))

Airfoil , aileron, flap, spoiler Two-dimensional force measurements

Flow visualization

Optimized

s 1 o t geometry

Unclassified

I Uncl as si f i ed I

For Sale by Industrial Applications Centers

4

INTRODUCTION

As part of NPSA's recent program for developing new air- foil sections for general aviation applications (Ref. 1) , Wichita

State University

is conducting flap and control surface research for the new airfoils. This report documents two-dimensional wind tunnel tests of the GA(W)-2 airfoil section with: (a) 20% chord aileron; (b) 25% chord slotted flap, (c) 30% chord Fowler flap; and (a) 10% chord slot-lip spoiler. A11 experimental tests reported herein were conducted in the Walter Beech hlemorial Wind Tunnel at Wichita State Univer- sity. High Reynolds number tests of the GP(W)-2 airfoil have been reported in reference 2.

SYMBOLS

The force and moplent data have been referred to the .25c location on the flap-nested airfoil. Dimensicnal quantities are given in both International (SI) Units and U.S. Customary

Units. Measurements

were made in U.S. Customary Units. Con- version factors between the various units may be found in ref- erence

3. The symbols used in the present re?,ort are defined

as follows:

C Airfoil reference chord (flap-nested)

C Airfoil fomard section chord

a 'd Airfoil section drag coefficient, section drag/ (dynamic pressure x chord)

Flap chord Cf

2 C Control surface morent coefficient about hingeline section moment/(dynamic pressure x reference chord

C Airfoil section lift coefficient, section lift/

(dynamic pressure x chord) 1 I * Lift coefficient based upon airfoil plus flap chcr2, 7, (Ca + Cf)/C) C Airfoil section pitching moren'l coefficient with re- m spect to the .25c locaticn, section monent/(dynanic pressure x chord21

Coefficient

of pressure, (p-p,) /dynamic pressure P C h Spoiler projection heiuht normal to local contour

P Pres sure

X Coordinate parallel to airfoil chord

Z Coordinate normal to airfoil chord

ry Angle of attack, degrees

A Increment

6 Rotation of surface from nested positj.cn, deqress.

Subscripts:

a Ai le ron € Flap max Maximum n Nose

P Pivot

S Spoiler

m Free stream condition

APPARATUS AND TEST PETHODS

Model Description

The GA(W)-2 airfoil section

is a 139 maximum thickness section derived from the

17% thick GA(W)-1 section (Ref. 4).

For tests in the WSU two-dirensional facility, the models are sized with 91.4 cm (36 inch) span and 61.0 cm (24 inch) chord. 2 The forward 70% of the airfoil was fabricated from laminated mahogany bonded to a 2.5 cm x 34.8 cm (1 inch x 13.7 inch) aluminum spar. Trailing edge sections were fabricated from solid aluminum for each trailing edge device. Configuration geometric details are given in figure 1. The 20% chord aileron is designed with a 0.5% leading- edge clearance gap. Earlier tests (Ref. 5) have shown that a gap this size has little effect on aileron performance. The 25% slotted flap design is used with an airfoil forward section terminating at 87.5% chord. The 30% Fowler flap is fitted with an airfoil forward section which extends to the full

100% chord location. The 10% spoiler is arranged in a

slot-lip configuration with the

25% slotted flap.

All models are equipped with 1.07 mm (.(I42 inch) diameter pressure taps for pressure distribution surveys. Flap and aile- ron positioning is provided throuqh a set of guide rails mounted on the outside of the end plate disks (external to the test sec- tion). Test models are attached to the tunnel main balance sys- tem through a set of 1.07 m (42 inch) diameter aluminum end plate disks. Yodel pivot location is the airfoil 50% chord station.

The end plates are fitted with foam seals around

the circumference. The seals are carefully adjusted during static calibration to avoid interference friction forces.

Instrumentation

The tunnel

is equipped with an automated data system which converts analog force and pressure transducer output signals to digital fcrm, and records the data on punched cards. Force measurements are made using a pyranidal balance.

Computation

work is done through the University Digital COF- puting Center. 3

Test Procedure

Lift, drag and pitchinq mon'ent data

are obtained from direct force measurements. For each airfoil section to be tested, a wake survey is conducted with a traversinq 5-tube probe (Ref.

6) to obtain section total drag coefficient as a

function of lift coefficient. The difference between the wake survey drag and the balance force measured drag is end platequotesdbs_dbs13.pdfusesText_19