Aeronautics Astronautics

Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher

By L. S. Fletcher

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0 Fig. 0 N Convective heating-rate distributions during entry (VSL results, large probe). 0 MOSS, ZOBY, SUTTON, AND ANDERSON 20 the stagnation-point value, varies substantially during the heating pulse. Figure 16 presents "both laminar and turbulent convective heating-rate distributions at various times during entry for the large probe (results for the small probes are given in Ref. 1. The turbulent heating-rate values at the aft end of the probes range from about two to five times the corresponding laminar values.

The effect of variations in the flight elevon deflection is included in the pressure, since the test article elevon was not deflectable. The total external surface heat load during the experiment reached the flight value after 1100 sec. Since the total simulation of 1800 sec exceeded 1100 sec, the total surface heat load was about twice the flight external heat load. However, this had little effect on the results of internal heating for a nonzero seal gap. 8 Laminar Probably transitional SCOTT, MURRAY, AND MILHOAN 40 5000 4000 3000 2000 1000 0 0 200 400 600 ) 1000 TIME, SEC 1200 1400 1600 1800 2000 Fig.

10, Feb. 1973, pp. 155-157. ^Falanga, R. A. and Olstad, W. B. , July 197U. Brewer, R. A. , May 1975. 7 Moss, J. N . , Anderson, E. C . , a n d B o l z , C. W . , "Aerothermal Environment for Jovian Entry Probes," AIAA Progress in Astronautics and Aeronautics: Thermophysics of Spacecraft and Outer Planet Entry Probes , Vol. 56, edited by A. M. Smith, 1977, PP- 333-35^. o Anderson, E. C. , Moss, J. N. , and Sutton, K. , "Turbulent Viscous-Shock-Layer Solutions With Strong Vorticity Interaction," AIAA Paper 76-120, Washington, D .

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