By L. S. Fletcher
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Extra info for Aerodynamic Heating and Thermal Protection Systems
556, 90-10 atm). 15 AEROTHERMAL ENVIRONMENT Figure 9 shows a comparison of the VSL and the approximate inviscid temperature profile at the end of the conical flank. These results are presented both with and without radiation. For the VSL results, the boundary-layer edge location occurs near the location of maximum temperature. Note that the inviscid results are in good agreement with the VSL results at the boundary-layer edge location. With the approximate convective heating analysis , it also was found that good agreement with the VSL solutions was obtained if the boundary-layer edge conditions were taken to be the inviscid wall conditions computed with the approximate adiabatic inviscid flowfieId analysis.
Reasons for the pressure drop at the cove inlet also are discussed. Nomenclature A c CD Cp D Dc f h hy K = = = = = = = = = = area of seal gap constant orifice discharge coefficient specific heat at constant pressure seal gap width cove gap width mean friction coefficient specific enthalpy total specific enthalpy in nozzle freestream constant Presented as Paper 77-757 at the AIAA 12th Thermophysics Conference, Albuquerque, N. , June 27-29, 1977. , 1977. All rights reserved. ^Research Engineer. tTest Program Manager.
And Sutton, K. , "Turbulent Viscous-Shock-Layer Solutions With Strong Vorticity Interaction," AIAA Paper 76-120, Washington, D . C . , Jan. 1976; also Journal of Spacecraft and Rockets, Vol. lU, Jan. 19775 pp. 32-37Q Nicolet, W. , "Advanced Methods for Calculating Radiation Transport in Ablation-Product Contaminated Boundary Layers," NASA CR-1656, 1970. Maslen, S. H. , "Inviscid Hypersonic Flow Past Smooth Symmetric Bodies," AIAA Journal, Vol. 2, June 196U, pp. 10551061. 26 MOSS, ZOBY, SUTTON, AND ANDERSON Olstad, W.
Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher