Author: P. Garcia Fogeda
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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.
Unsteady Transonic Aerodynamics of Pointed Bodies of Revolution in Supersonic Freestream
Author: P. Garcia Fogeda
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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.
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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.
Unsteady Aerodynamic Forces on a Slender Body of Revolution in Supersonic Flow
Author: Reuben Bond
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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).
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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).
Unsteady Aerodynamics Forces on a Slender Body of Revolution in Supersonic Flow
non- steady supersonic flow about pointed bodies of revolution
Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds
Author: William A. Cassels
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
Book Description
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.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
Book Description
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.
Scientific and Technical Aerospace Reports
Second Order Theory for Unsteady Super-sonic Flow Past Slender, Pointed Bodies of Revolution
Author: James Dewey Revell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 180
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 180
Book Description
Handbook of Supersonic Aerodynamics
Author: D. Adamson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
Velocity Potential and Forces on Oscillating Slender Bodies of Revolution in Supersonic Flow Expanded to the Fifth Power of the Frequency
Author: Donald L. Lansing
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
Book Description
Analysis of the Linearized Supersonic Flow about Pointed Bodies of Revolution by the Method of Characteristics
Author: Alan D. Sherer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description