Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section

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National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] , Washington, D.C, [Springfield, Va
Aerofoils., Wind tun
StatementRobert J. McGhee and William D. Beasley.
SeriesNASA technical paper -- 1919.
ContributionsBeasley, William D., Langley Research Center., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
The Physical Object
Pagination84 p. :
ID Numbers
Open LibraryOL15261762M

Additional Physical Format: Online version: McGhee, Robert J. Wind-tunnel results for a modified percent-thick low-speed airfoil section. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. Wind-tunnel results for a modified percent-thick low-speed airfoil section / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and.

Sep 01,  · Low-Speed Wind Tunnel Testing, Wind-Tunnel Results for a Modified Percent-Thick Low-Speed Airfoil Section Experimental Results for the Eppler Airfoil at Low Reynolds Number in the Langley Low-Turbulence Pressure Tunnel,” NASA Technical MemorandumLangley Research Center, Hampton, VA.

Cited by: Wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)) designed for general aviation.

Wind Tunnel Wind Turbine Aerodynamic Force Rotor Power Blade Pitch These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

McGhee, R. C.; Beasley, W. D.: Wind Tunnel Results for a Modified Percent-Thick Low-Speed Airfoil Section. NASA Technical PaperGoogle Scholar Author: Erich Hau. Wind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a percent-thick low-speed airfoil.

A wing with a NACA airfoil section was also tested to provide baseline comparison data for the other wings. The tests were conducted in the Langley V/STOL wind tunnel through an angle-of- attack range of -4° to 22° and a sideslip range of -5° to 5°.

Reynolds number based on wing chord was also varied from x 10® to x 10®. AERODYNAMIC CHARACTERISTICS OF A LARGE AIRCRAFT TO The wing airfoil section was the percent-thick GA(W)-1 (ref.

3) low-speed section and was constant across the span. The wing-root incidence was 2O, and the angle varied linearly to a tip incidence of 0'. The vertical and horizontal tails used the NACA airfoil section. The LS series was developed by McGhee at NASA for low-speed general purpose aviation.

The symmetric airfoil with 17% thickness was compared with NACAand The results demonstrate that instantaneous power coefficient, normal and tangential force coefficients are smoothly distributed with smaller papercitysoftware.com: Palanisamy Mohan Kumar, Krishnamoorthi Sivalingam, Teik-Cheng Lim, Seeram Ramakrishna, He Wei.

Check your modified code.

Details Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section EPUB

Run the airfoil you ran previously with internal coordinate generation. This time use an input file with the same coordinates as external inputs. Submit a description of your work, and assess your results. Assess the accuracy of incompressible potential flow theory.

This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. Robert J. McGhee and William D.

Description Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section PDF

Beasley, Low-Speed Aerodynamic Characteristics of a Percent-Thick Airfoil Section Designed for General Aviation Applications, NASA TN D, Decemberpp. Robert J. Pegg and David A. Hilton, Comparison of Acoustic Performance of Five Muffler Configurations on a Small Helicopter, NASA TN D, May With these promising results in hand, the interest turned to flight verification of the wind-tunnel results.

Basic T-2 (left) and modified T-2 with percent-thick supercritical wing (right). The test aircraft for the project was a T-2C Buckeye trainer aircraft on loan from the Navy.5/5(2).

In this case the actual results are found to be about 60% of the inviscid prediction at low speed. Pick a NASA or NACA report describing wind tunnel results for a simple one or and Beasley, William D., “Low Speed Aerodynamic Characteristics of a Percent-Thick Airfoil Section Designed for General Aviation Applications.

Full text of "NASA scientific and technical publications: A catalog of Special Publications, Reference Publications, Conference Publications, and Technical Papers, " See other formats. Reference book of policies and guidance for implementing the Endangered Species Act (ESA) Wind-tunnel results for a modified percent-thick low-speed airfoil section NAS The Saturn system NAS Off-the-job noise and hearing loss.

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Initial wind-tunnel tests by North American Rockwell, Columbus Division, of wings with this range of thickness values indicated that the drag-divergence Mach number of a percent-thick supercritical airfoil shape was equal to that for a conventional percent-thick airfoil, that the buffet onset was considerably higher, and that the low 5/5(3).

Section (Figsa and b) give the definitions of some additional terms regarding the wing. Airfoil selection Large airplane companies like Boeing and Airbus may design their own airfoils. However, during the preliminary design stage, the usual practice is to choose the airfoil from the large number of airfoils whose geometric and.

The use of swept wings for high subsonic speeds was contemplated by Busemann but the first wind tunnel tests on a swept wing model were performed by Betz and Ludwieg in December in a new wind tunnel with a test section measuring 11 x 11 cm.

This first swept wing model had a span b = cm and the tests were performed at Re = x At low speed, th e wing's angle of attack mu st increase, as does its lift coefficient, and the downwash angle is high. At top speed, th e reverse is true, and the downwash angle is low.

At low speed, the hori zontal tail's downward lift must be increased to force th e wing's airfoil to a h igh er AoA. The test model is a NACA 63(sub 2) Hicks Mod-B main-element airfoil with a half-span Fowler flap.

Air is blown from small slots located along the flap side edge on either the top, bottom or side surfaces. The test set up is described and flow measurements for.

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