Experimental Determination of Aerodynamic Drag on a Blunted 10-deg Cone at Angles of Attack in Hypersonic, Rarefied Flow PDF Download
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Author: David E. Boylan
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 40
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Book Description
Author: David E. Boylan
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 40
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 2180
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
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Book Description
Author: Peter F. Intrieri
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 36
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 914
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1284
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Book Description
Author: Marvin I. Kussoy
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 20
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 410
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 31
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A free-flying instrumented model was tested in a hypersonic facility at M = 5.30, 6.34 and 9.94 and Re = 300,000 to 1,200,000 ft. Aerodynamic lift, total drag and base drag coefficients were obtained together with detailed base pressure distribution measurements at angles of attack from 0 to 60 deg. The measured lift and drag coefficients showed good agreement with the modified Newtonian theory. The centerline base pressure/free-stream static pressure, psia distribution was nearly independent of the angle of attack from -10 to -30 deg but increased rapidly for all test conditions beyond alpha = -30 deg. For similar conditions at angle of attack and Reynolds number, an increase in Mach number resulted in an increase of the base pressure ratio. The measurements indicated a highly complex base flow region, and tentative explanation of the observed results was offered.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 988
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