A Program for Computing Steady Inviscid Three-dimensional Supersonic Flow on Reentry Vehicles PDF Download
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Author: J. M. Solomon Publisher: ISBN: Category : Aerodynamics, Hypersonic Languages : en Pages : 236
Book Description
A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a FORTRAN computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. In this report (Vol. I) the analytical and numerical development of the procedure is presented and the associated computer code is described. A comparison report (Vol. II User's Manual) contains detailed instructions for operating the code and interpreting the output results. (Author).
Author: J. M. Solomon Publisher: ISBN: Category : Aerodynamics, Hypersonic Languages : en Pages : 236
Book Description
A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a FORTRAN computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. In this report (Vol. I) the analytical and numerical development of the procedure is presented and the associated computer code is described. A comparison report (Vol. II User's Manual) contains detailed instructions for operating the code and interpreting the output results. (Author).
Author: J. M. Solomon Publisher: ISBN: Category : Boundary value problems Languages : en Pages : 106
Book Description
A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a fortran computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. This volume contains detailed instructions for operating the code and interpreting the output results.
Author: Anthony L. Laganelli Publisher: ISBN: Category : Ballistic missiles Languages : en Pages : 184
Book Description
An experimental program was conducted at the AEDC von Karman facility, Tunnels A and B, in which acoustic pressure fluctuation data were acquired on a 7 degree half-cone-angle model featuring a control surface. The objective was to define the aeroacoustic environment applicable to re-entry vibration response analysis for both ballistic and maneuvering vehicles. Wind tunnel measurements were obtained at Mach 4 and 8 for several values of freestream Reynolds number and model angle of attack. Stationary zones of laminar, transitional, and turbulent flow over the model were achieved. Acoustic data were reduced to rms fluctuating pressure, and power and cross-power spectral densities. Results were normalized using local boundary layer parameters for comparison with previous high speed measurements. The present study re-examined the aeroacoustic environment prediction capability relative to compressible flow conditions. Moreover, boundary layer characteristic lengths and velocities were reviewed in order to develop normalization procedures required for development of appropriate aeroacoustic scaling laws. It was determined that fluctuating pressure characteristics described by incompressible theory as well as empirical correlations could be modified to a compressible state through a transformation function. In this manner, compressible data were transformed to the incompressible plane where direct use of more tractable prediction techniques are available for engineering design analyses.
Author: J. M. Solomon
Author: J. M. Solomon
Author: J. M. Solomon
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Author: Anthony L. Laganelli
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