Author: Maurice HoltPublisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness. Part I: Linear Variation
Author: Maurice HoltSupersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Maurice HoltPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
Book Description
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Maurice HoltPublisher:
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 HoltPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
Book Description
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Bohyun YimPublisher:
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.
International Aerospace Abstracts
Author: AFOSR.
Author: United States. Air Force. Office of Scientific ResearchPublisher:
ISBN:
Category : Research
Languages : en
Pages : 940
Book Description
OAR Cumulative Index of Research Results
Author: United States. Air Force. Office of Aerospace ResearchPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 550
Book Description
U.S. Government Research Reports
Author: Proceedings
Author: United States. National Congress of Applied MechanicsPublisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 760
Book Description