Comparison of viscous-shock-layer heating analysis with Shuttle flight data in slip flow regime

Comparison of STS-2 Shuttle flight heating data along the windward centerline has been made with two-dimensional nonequilibrium viscous shock-layer solutions obtained with shock and wall-slip conditions at an altitude range of 90 to 110 km. The shock slip condition used is the modified Rankine-Hugoniot relations of Cheng as used by Davis, and the wall-slip conditions are based on the first order consideration derived from kinetic theory as given by Scott and Hendricks. The results indicate that the calculated heating distributions with slip boundary conditions agree better with the flight data than those without slip conditions. The agreement improves when the accommodation coefficient or freestream density is decreased to one-half, suggesting the possibility of less than full accommodation for the tile surface and (or) an overestimate of freestream density using the Jacchia-Roberts model. Heating reduction due to the slip effect becomes very pronounced as the flow becomes more rarefied, and the effect is more significant for the stagnation region than the aft region of the vehicle.

[1]  J. Moss.  Reacting viscous-shock-layer solutions with multicomponent diffusion and mass injection , 1974 .

[2]  D. Throckmorton.  Benchmark aerodynamic heat-transfer data from the first flight of the Space Shuttle Orbiter , 1982 .

[3]  G. D. Walberg,et al.  A review of aeroassisted orbit transfer , 1982 .

[4]  W. Hendricks.  Slip conditions with wall catalysis and radiation for multicomponent, nonequilibrium gas flow. [for predicting heat transfer to the space shuttle] , 1974 .

[5]  E. Anderson,et al.  Numerical solution of the steady-state Navier-Stokes equations for hypersonic flow about blunt axisymmetric bodies , 1974 .

[6]  R. Davis.  Hypersonic flow of a chemically reacting binary mixture past a bluntbody , 1970 .

[7]  R. Davis,et al.  Numerical solution of the hypersonic viscous shock-layer equations , 1970 .

[8]  R. C. Blanchard,et al.  Determination of atmospheric properties for STS-1 aerothermodynamic investigations , 1981 .

[9]  S. Singer,et al.  Molecular flow of gases , 1956 .

[10]  James N. Moss,et al.  Direct Simulation of Transitional Flow for Hypersonic Reentry Conditions , 1984 .

[11]  M. J. Lanfranco,et al.  Catalytic surface effects experiment on the Space Shuttle , 1981 .

[12]  C. Li.  Hypersonic nonequilibrium flow past a sphere at low Reynolds numbers , 1974 .

[13]  Edward A. Mason,et al.  Approximate Formula for the Thermal Conductivity of Gas Mixtures , 1958 .

[14]  W. L. Hendricks.  A similarity solution of the Navier-Stokes equations with wall catalysis and slip for hypersonic, low Reynolds number flow over spheres , 1975 .

[15]  S. H. Maslen.  On Heat Transfer in Slip Flow , 1958 .

[16]  J. T. Findlay,et al.  Shuttle /STS-1/ entry trajectory reconstruction , 1981 .

[17]  Robert E. Street,et al.  Introduction to the dynamics of rarefied gases , 1967 .

[18]  L. Jacchia,et al.  Thermospheric temperature, density, and composition: New models , 1977 .

[19]  J. J. Jones,et al.  Chemical Nonequilibrium Effects on Flowfields for Aeroassisted Orbital Transfer Vehicles , 1985 .

[20]  C. D. Scott.  Wall boundary equations with slip and catalysis for multicomponent, nonequilibrium gas flows , 1973 .

[21]  James N. Moss,et al.  Viscous-shock-layer heating analysis for the shuttle windward-symmetry plane with surface finite catalytic recombination rates , 1982 .