Investigation on Low-Reynolds Number Aerodynamic Characteristics of Low-Aspect Ratio Thin Wings PDF Download
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Author: 劉益仲
Publisher:
ISBN:
Category :
Languages : en
Pages : 221
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Author: 劉益仲
Publisher:
ISBN:
Category :
Languages : en
Pages : 221
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Author: Marvin P. Fink
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Author: 陳崇海
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
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Author: Bernard Spencer
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92
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Author: John P. Mugler
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 44
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An investigation was conducted in the Langley 8-foot transonic tunnel to determine the aerodynamic characteristics of a thin 60 degree delta wing with two leading-edge modifications (conical leading-edge camber and leading-edge droop) in combination with bodies with and without body indentation in accordance with the transonic-area-rule concept. The tests covered a Mach number range from 060 to 1.15 and an angle-of-attack range from -4 to 20 degrees at a Reynolds number of about 3,000,000 based on the wing mean aerodynamic chord. The wing had an aspect ratio of 2.31, a taper ratio of 0, and, without modifications, had NACA 65A003 airfoil sections parallel to the model plane of symmetry.
Author: William P. Henderson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
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Author: George E. Bartlett
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Category :
Languages : en
Pages : 33
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Author:
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ISBN:
Category :
Languages : en
Pages : 38
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Author: Thomas J. Mueller
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ISBN:
Category :
Languages : en
Pages : 32
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A description of the micro-air vehicle (MAV) concept and design requirements is presented. These vehicles are very small and therefore operate at chord Reynolds numbers below 200,000 where very little data is available on the performance of lifting surfaces, i.e., airfoils and low aspect-ratio wings. This paper presents the results of a continuing study of the methods that can be used to obtain reliable force and moment data on thin wings in wind and water tunnels. To this end, a new platform force and moment balance, similar to an already existing balance, was designed and built to perform lift, drag and moment measurements at low Reynolds numbers. Balance characteristics and validation data are presented. Results show a good agreement between published data and data obtained with the new balance. Results for lilt, drag and pitching moment about the quarter chord with the existing aerodynamic balance on a series of thin flat plates and cambered plates at low Reynolds numbers are presented. They show that the cambered plates offer better aerodynamic characteristics and performance. Moreover, it appears that the trailing-edge geometry of the wings and the turbulence intensity up to about 1% in the wind tunnel do not have a strong effect on the lilt and drag for thin wings at low Reynolds numbers. However, the presence of two endplates for two-dimensional tests and one endplate for the semi-infinite tests appears to have an undesirable influence on the lift characteristics at low Reynolds numbers.
Author: Robert S. Osborne
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20
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