Measured and Predicted Shock Shapes and Aerodynamic Coefficients for Blunted Cones at Incidence in Helium at Mach 20.3 PDF Download
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Author: Robert L. Calloway
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 84
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Book Description
Experimental values of shock shapes (alpha = 0 degrees and 10 degrees) and static aerodynamic coefficients (alpha = -4 degrees to 12 degrees) for sharp and spherically blunted cones having cone half-angles of 30, 45, 60, and 70 degrees and nose bluntness ratios of 0, 0.25, and 0.50 are presented. Shock shapes were also measured at 0 degree angle of attack by using a flat-faced cylinder (90 degree cone) and a hemispherically blunted cylinder (sphere). All tests were conducted in helium (gamma = 5/3) at a free-stream Mach number of 20.3 and a unit free-stream Reynolds number of 22,400,000 per meter. Comparisons between measured values and predicted values were made by using several numerical and simple engineering methods.
Author: Robert L. Calloway
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 84
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Book Description
Experimental values of shock shapes (alpha = 0 degrees and 10 degrees) and static aerodynamic coefficients (alpha = -4 degrees to 12 degrees) for sharp and spherically blunted cones having cone half-angles of 30, 45, 60, and 70 degrees and nose bluntness ratios of 0, 0.25, and 0.50 are presented. Shock shapes were also measured at 0 degree angle of attack by using a flat-faced cylinder (90 degree cone) and a hemispherically blunted cylinder (sphere). All tests were conducted in helium (gamma = 5/3) at a free-stream Mach number of 20.3 and a unit free-stream Reynolds number of 22,400,000 per meter. Comparisons between measured values and predicted values were made by using several numerical and simple engineering methods.
Author: Robert L. Calloway
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 76
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 308
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1346
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Author: Charles G. Miller (III.)
Publisher:
ISBN:
Category :
Languages : en
Pages : 302
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Author: Charles George Miller
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 300
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 410
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 396
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Author: Clark H. Lewis
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 1
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Pressure distributions and shock shapes were measured over spherically blunted and flat-nosed 9-det half-angle cones at Mach numbers from 16 to 19. The pressure distributions for the flat-nosed cone show an overexpansion followed by a pressure peak above the conical value and then an approach to the constant cone value. This experimenatal observation is generally in agreement with recent theoretical studies which consider the inviscid induced pressure field produced by nose bluntness at hypersonic speeds (blast wave effect). The results of the pressure distribution over the spherically blunted cone agree well with a characteristic solution but do not agree with theoretical estimates from nose-bluntness-induced theories. The shock shape for the flat-nosed cone is displaced farther from the body than the nose-bluntness-induced theory predicts; however, the slope of the shock wave is well predicted by the theory. The shock shape over the spherically blunted model agrees well with the theory, and the slope agrees with both theory and a characteristic solution.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 396
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