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By L. S. Fletcher

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The extent to which the convective heating rate is influenced by radiation transfer is dependent upon the gas composition and entry conditions. 10 n/RN Fig. 556, 90-10 atm). 16 MOSS, ZOBY, SUTTON, AND ANDERSON heating results with and without radiation transfer are significantly different for other planetary entry conditions (different atmospheric gas composition). 3. \j I 30 - fi / 1 ii ! 7° Aj f\ \ 1 / - /I \ 1 8 Fig. 3 (90-10 atm, approximate analysis). 4 0 -4 10 Fig. 44 X1'01525 1 ID'3 1 1 ID'2 Stagnation radiative cooling correlation for a 90-10 atm (approximate analysis ) .

C. , Moss, J. N. , 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.

Along the conical flank, the radiative heating-rate reduction is almost negligible. Therefore, these results, along with the stagnationpoint results (Fig. 19), suggest that the nonablating radiative heat load predicted with the VSL analysis would experience a very small reduction due to coupled carbon-phenolic injection. Remember, however, as was discussed previously, that the VSL radiative heating rates were significantly less than the corresponding inviscid values because of the strongly absorbing boundary layer.

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