The Potential Theory of Unsteady Supersonic Flow PDF Download
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Author: John Wilder Miles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 220
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Book Description
Author: John Wilder Miles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 220
Get Book Here
Book Description
Author: John Wilder Miles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 244
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Book Description
Author: pseud Armiger
Publisher:
ISBN:
Category :
Languages : en
Pages : 220
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Book Description
Author: Planjery V. Sankaranarayana
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 150
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Book Description
Author: Reuben Bond
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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Book Description
Linearized slender-body theory is applied to the computation of aerodynamic forces on an oscillating, or deforming, body in supersonic flow. The undeformed body is a body of revolution and the deformed body is represented by movement of a line through the centers of the cross sections which are assumed to remain circular. The time dependence is based on sinusoidal motion. For a body of vanishing thickness the slender-body theory yields the apparent mass approximation as it is obtained for incompressible crossflow around a cylinder. Both linearized slender-body theory and the apparent mass approximation are used to calculate the pitching-moment coefficients on a rigid slender body with a parabolic arc nose cone, and these coefficients are compared with some experimental results. (Author).
Author: G. F. TELENIN
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Book Description
Author: John Miles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 606
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Book Description
"The following monograph is intended to survey they application of the theory of perfect fluid flow to the prediction of the aerodynamic forces that act on thin wings and slender bodies as a result of small, unsteady motions with respect to an equilibrium configuration of uniform, supersonic flight. In addition, certain aspects of the corresponding subsonic problem are taken up (in Chapters 1 and 2) insofar as they afford informative comparisons with their supersonic counterparts."--Preface.
Author: Francis Pierre Mosnier
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: M. N. Shneider
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: C. J. Chen
Publisher:
ISBN:
Category :
Languages : en
Pages : 89
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Book Description
The strength of the shock wave in the vicinity of a gun is predicted. The energy release is considered to be a function of time. As the shock wave reaches the point of analysis the energy is still being released. It is found that the energy release by the after-flashing will not significantly alter the shock strength but will affect the flow behind the shock wave. The pressure behind the shock wave will decrease slower if the energy is released continuously. The strength of the shock wave in general decreases with increase of the length of tube and is proportional to the total energy released.
