Supersonic Flow Past Pointed Bodies of Revolution at Small Angles of Attack PDF Download
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Author: Keiichi Karashima
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
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Book Description
Author: Keiichi Karashima
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
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Book Description
Author: Charlie M. Jackson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 106
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Book Description
Author: Alan D. Sherer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
Author: w. h. dorrance
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
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Book Description
Author: Antonio Ferri
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 53
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Book Description
The method of characteristics has been applied to rotational supersonic flow around bodies of revolution at a small angle of attack. The practical numerical calculations are similar to those for zero angle of attack. A method for determining supersonic flow around circular cones at an angle of attack is also given.
Author: M. J. Lighthill
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Benjamin R. Briggs
Publisher:
ISBN:
Category : Numerical analysis
Languages : en
Pages : 34
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Author: William A. Cassels
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
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Book Description
Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Author: Milton Van Dyke
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
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Book Description
Some 100 numerical computations have been carried out for unyawed bodies of revolution with detached bow waves. The gas is assumed perfect with y=5/3, 7/5, or 1. Free-stream Mach numbers are taken as 1.2, 1.5, 2, 3, 4, 6, 10, and [infinity symbol]. The results are summarized with emphasis on the sphere and paraboloid.
