Graduate Fellowship in Hypersonics
Final rept. Jul 1986-Sep 1990,
NORTH CAROLINA STATE UNIV AT RALEIGH DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
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Research was performed to develop innovative means of computing flow over sustainer projectiles at high speed. A code was developed using Newton iteration applied to the steady Navier-Stokes equations. Roes upwind flux difference splitting was used for spatial discretization. Second order accurate values of the Riemann variables were obtained by Spekreijses interpolation procedure with Van Albadas limiter used to reduce spurious oscillations in the results. THe Jacobian Derivatives and the code necessary to compute the Jacobian elements were generated by use of the symbolic manipulation code MACSYMA. The Boeing package RSLIB was used to invert the Jacobian matrix. Computational results were obtained for flat plates, flat plate-ramp, and ogive-tangent- cylinder configurations at Mach numbers ranging from 2 to 14.1. These cases contained shock on shock interactions., viscous layer separations, and turbulent boundary layer transitions. Covergence was obtained in 15 to 200 iterations. Results agreed well with experiment or other computation and demonstrated that Newton iteration can produce results for complex high speed flows with shock waves.
- Numerical Mathematics
- Fluid Mechanics