A Study of Second-order Supersonic-flow Theory PDF Download

Author: Milton Van Van Dyke
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 73

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Second-order solutions of supersonic-flow problems are sought by iteration, using the linearized solution as the first step.

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: 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: Milton D. Van Dyke
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 95

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Author: Milton Van Dyke
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36

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Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes.

Author: David A. Caughey
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 98

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This report investigates the mathematical analysis of wave structure in supersonic flow.

Author: James Dewey Revell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 180

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Author: Alan King King
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 376

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Author: David Harry Lee
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Alfred John Eggers (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 298

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