By L. S. Fletcher
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Extra resources for Aerodynamic Heating and Thermal Protection Systems
9," NASA TM 74095, 1978. 10 Brown, R. D. and Jakubowski, A. , "Heat Transfer and Pressure Distributions for Laminar Separated Flows Downstream of Rearward-Facing Step with and without Suction," NASA TN D-7430, 1974. u Jakubowski, A. K. and Lewis, C. , "Rearward-Facing Steps in Laminar Supersonic Flows with and without Suction," NASA CR-132476, 1974. 12 Inger, G. , "Supersonic Laminar Flow Past a Small RearwardFacing Step," AJAA Journal, Vol. 12, June 1974, pp. 739-740.
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. 6 Local environment for elevon seal during orbiter flight and simulation. A typical response of the test article temperatures is given in Fig.
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. With the VSL analysis, the convective heating-rate values (both laminar and turbulent) are essentially the same, whether radiation is or is not included in the calculation.
Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher