A Second-order Theory of Unsteady, Supersonic Flow PDF Download
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Author: Alan King King
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 376
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Book Description
Author: Alan King King
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 376
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Book Description
Author: James Dewey Revell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 180
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Book Description
Author: John Wilder Miles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 244
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Book Description
Author: John Wilder Miles
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 220
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Author: Joseph Henry Clarke
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
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Book Description
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: Stanford University. Department of Aeronautics and Astronautics
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 106
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Book Description
A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for 45 degree delta wings of 5% and 10% thicknesses, which indicate a substantial difference between the linearized and nonlinear lifting potential distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type. (Author).
Author: Milton D. Van Dyke
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
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Methods are studied for imporving the existing perturbation theories of axial and inclined supersonic flow past bodies of revolution. For axial flow, a second-order solution is developed using an interation procedure based upon the linearized solution. The resulting second-order problem is reduced to an equivalent first-order problem by discovery of a particular solution. The second-order supersonic flow can then be computed with slight modification of the Karman-Moore procedure. For inclined flow, no particular solution of the second-order equation has been discovered. The second-order solution is derived for a cone, and agrees well with the exact solution. The slender-body series expansion of the second-order solution is found to cause large inaccuracies in both the axial and inclined flows. The conclusion that first-order theory predicts the inclined flow no better than slender-body theory is shown to be erroneous. Non-linearity in lift is shown to result primarily from viscous separation of the crossflow along the after portions of the body. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 482
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Author: David Harry Lee
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: David A. Caughey
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 98
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Book Description
This report investigates the mathematical analysis of wave structure in supersonic flow.
