Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness PDF Download
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Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
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Book Description
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
Get Book Here
Book Description
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
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Book Description
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 86
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Book Description
In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock ... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.
Author: Maurice Holt
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Author: Bohyun Yim
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 134
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Book Description
In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.
Author:
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ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 1756
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Book Description
Abstracts of dissertations and monographs in microform.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 788
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Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 252
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Author: United States. Air Force. Office of Scientific Research
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 940
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
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