Unsteady Transonic Aerodynamics of Pointed Bodies of Revolution in Supersonic Freestream PDF Download
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Author: P. Garcia Fogeda
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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Book Description
A method to determine the aerodynamic forces acting on oscillating pointed bodies of revolution in transonic-supersonic flight has been developed. The nonlinear equation for the mean-flow perturbation potential and the time linearized equation for the cross-flow perturbation potential are both of hyperbolic type, for the Mach number range of interest, and have been solved by the method of characteristics. The method is valid for arbitrary frequencies of oscillation and can be applied for rigid or flexible body motions. Results are presented for the stability force coefficients, unsteady pressure distributions and shock deformations for various body shapes and Mach numbers.
Author: P. Garcia Fogeda
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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Book Description
A method to determine the aerodynamic forces acting on oscillating pointed bodies of revolution in transonic-supersonic flight has been developed. The nonlinear equation for the mean-flow perturbation potential and the time linearized equation for the cross-flow perturbation potential are both of hyperbolic type, for the Mach number range of interest, and have been solved by the method of characteristics. The method is valid for arbitrary frequencies of oscillation and can be applied for rigid or flexible body motions. Results are presented for the stability force coefficients, unsteady pressure distributions and shock deformations for various body shapes and Mach numbers.
Author: Reuben Bond
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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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: Reuben Bond
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Author: w. h. dorrance
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
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Author: William A. Cassels
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ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
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Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Author: James Dewey Revell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 180
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Author: D. Adamson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 324
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Author: Donald L. Lansing
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Author: Alan D. Sherer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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