Unsteady Aerodynamic Forces on a Slender Body of Revolution in Supersonic Flow PDF Download
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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: Reuben Bond
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Get Book Here
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: Reuben Bond
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Book Description
Author: Donald L. Lansing
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 984
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Book Description
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: Johns Hopkins University. Applied Physics Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 420
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Book Description
Author: D. Adamson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
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Book Description
Author: w. h. dorrance
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
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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: Robert T. Jones
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 18
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Book Description
The theory of small disturbances is applied to the calculation of the pressure distribution and drag of a closed body of revolution traveling at supersonic speeds. It is shown that toward the rear of the body the shape of the pressure distribution is similar to that for subsonic flow. For fineness ratios between 10 and 15 the theoretical wave drag is of the same order as probable values of the frictional drag.
