Graduate Fellowship in Hypersonics
Abstract
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. Roe's 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 Albada's 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 30, 1990
- Accession Number
- ADA231263
Entities
People
- D. S. Mcrae
- Paul D. Orkwis
Organizations
- North Carolina State University