The Linearized Wing Theory of the Supersonic Flow with the Karman's Fourier Integral Method PDF Download
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Author: Chieh-chien Chang
Publisher:
ISBN:
Category :
Languages : en
Pages : 172
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Book Description
Author: Chieh-chien Chang
Publisher:
ISBN:
Category :
Languages : en
Pages : 172
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Book Description
Author: Chieh-Chien Chang
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
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Book Description
The theory is also applied to find the downwash distribution in the plane of the wing on which the pressure distribution is preassigned. A number of examples are given.
Author: Carlo Ferrari
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
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Abstract: A discussion is given of the application of Fourier series techniques to the problems of linearized supersonic flow. The formulation presented is an extension of the doublet type of "fundamental solution" to higher order types of singularity. The equations developed have application to wing theory but are primarily of importance in wing-body interaction problems. A specific example of a wing-body interference problem is discussed in light of the presented methods.
Author: John Wilder Miles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 244
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Author: Wallace Dean Hayes
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 348
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 436
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Author: Sydney Goldstein
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56
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Author: Joseph Henry Clarke
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
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A general reverse-flow relation is obtained within the framework of second-order (in surface deflection) supersonic flow theory. From this it is shown that the second-order increment in the drag of an arbitrary quasicylindrical body can be expressed as surface and volume integrals of the first-order solutions corresponding to forward and reverse flow past the body. Analogous results are obtained for second-order transverse forces and moments on an arbitrary quasiplanar wing, except the first-order reverse flow must correspond to certain zero-thickness wings. Other similar results are possible. Thus, second order aerodynamic forces on bodies may be obtained from first-order solutions by quadrature. It is also shown that the reverse-flow integral relation can yield the pressure distribution on the surface by inversion of an integral equation constructed therefrom. It is thought that these results should be particularly useful for the Mach number range between that of linearized theory and that of full hypersonic small-disturbance theory. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 102
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In the first formulation. the integral equation for linearized steady supersonic flows appears in a form where it is necessary to approach the planform from above or below by a limiting process. In the present report, the problem is transformed analytically in such a manner that this limiting process no longer appears and that the resulting expressions are numerically tractable. It is believed that such a formulation gives more freedom to take the particularities of a given problem into account. The formulation is applied to compute the conical field which arises at the top of an airfoil. A possible numerical approach to the solution of the integral equation in the general case is described, but only in a rough outline.
Author: Simon Ostrach
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 646
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