Analytic Corrections to Computational Heating Predictions Accounting for Changes in Surface Catalysis

A new approach for combining the insight afforded by integral boundary-layer analysis with comprehensive (but time-intensive ) computational e uid dynamic e owe eld solutions of the thin-layer Navier ‐Stokes equations is described. The approach extracts computationally simulated quantities at the wall and at the boundary-layer edge for inclusion in a postprocessing boundary-layer analysis. It allows a designer at a workstation to address the question, given a single computational solution, “ How much does the heating change for a thermal protection system with catalytic properties different from those used in the original numerical simulation?” Capabilities of this approach for application to reusable launch vehicle design are demonstrated. If the dee nition of surface catalysis is uncertain early in thedesign process, results show that fully catalyticwall boundary conditionsprovide the best baseline for computationally simulated design points.

[1]  H. C. Yee,et al.  On symmetric and upwind TVD schemes , 1985 .

[2]  P. A. Gnoffo,et al.  Point-implicit relaxation strategies for viscous, hypersonic flows , 1989 .

[3]  Peter A. Gnoffo,et al.  Analytic corrections to CFD heating predictions accounting for changes in surface catalysis , 1996 .

[4]  R. Goulard,et al.  On Catalytic Recombination Rates in Hypersonic Stagnation Heat Transfer , 1958 .

[5]  Peter A. Gnoffo,et al.  Code calibration program in support of the Aeroassist Flight Experiment , 1990 .

[6]  Peter A. Gnoffo,et al.  Navier-Stokes simulations of Orbiter aerodynamic characteristics including pitch trim and bodyflap , 1994 .

[7]  Peter A. Gnoffo,et al.  Hypersonic entry heating with discontinuous surface catalycity - A combined analytic/CFD approach , 1996 .

[8]  J. Elder,et al.  Recombination-Dominated Nonequilibrium Heat Transfer to Arbitrarily Catalytic Hypersonic Vehicles , 1991 .

[9]  Peter A. Gnoffo,et al.  Multiblock analysis for Shuttle Orbiter reentry heating from Mach 24 to Mach 12 , 1994 .

[10]  Aeroassisted Flight Experiment aerodynamic characteristics at flight conditions , 1990 .

[11]  David A. Stewart,et al.  Surface Catalysis and Characterization of Proposed Candidate TPS for Access-to-Space Vehicles , 1997 .

[12]  Peter A. Gnoffo,et al.  Application of the LAURA code for slender-vehicle aerothermodynamics , 1992 .

[13]  Paul Kolodziej,et al.  Thermal response of integral multicomponent composite thermal protection systems , 1986 .

[14]  George R. Inger,et al.  Nonequilibrium Boundary-Layer Effects on the Aerodynamic Heating of Hypersonic Waverider Vehicles , 1995 .

[15]  P. Gnoffo An upwind-biased, point-implicit relaxation algorithm for viscous, compressible perfect-gas flows , 1990 .

[16]  P. Roe Approximate Riemann Solvers, Parameter Vectors, and Difference Schemes , 1997 .

[17]  G. Inger,et al.  Nonequilibrium Stagnation Point Boundary Layers with Arbitrary Surface Catalycity , 1963 .