Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 86
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.
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
Book Description
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
Book Description
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 86
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.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 86
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.
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness. Part I: Linear Variation
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Bohyun Yim
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 134
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.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 134
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.
AFOSR.
Author: United States. Air Force. Office of Scientific Research
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 940
Book Description
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 940
Book Description
Dissertation Abstracts
Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 1756
Book Description
Abstracts of dissertations and monographs in microform.
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 1756
Book Description
Abstracts of dissertations and monographs in microform.
OAR Cumulative Index of Research Results
Index to American Doctoral Dissertations
Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 252
Book Description
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 252
Book Description
Annual Report
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
Book Description