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

By L. S. Fletcher

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7-9). 53 mm. The 6 heat-transfer distributions in the cove were taken from Duffy and are plotted in Fig. 3. 8 Note that the inlet enthalpy h0 lies between the wall enthalpy hs and the total enthalpy hj, as would be expected. The mea- 44 SCOTT, MURRAY, AND MILHOAN 2 3 4 5 6 GAP WIDTH D, mm 7 9 10 Fig. 10 Temperature rise of aluminum structure during simulation at 1800 sec. sured cavity temperatures are not accurate because of radiation heat transfer to the thermocouple, differing from the calculated values by as much as 350 K.

7-9). 53 mm. The 6 heat-transfer distributions in the cove were taken from Duffy and are plotted in Fig. 3. 8 Note that the inlet enthalpy h0 lies between the wall enthalpy hs and the total enthalpy hj, as would be expected. The mea- 44 SCOTT, MURRAY, AND MILHOAN 2 3 4 5 6 GAP WIDTH D, mm 7 9 10 Fig. 10 Temperature rise of aluminum structure during simulation at 1800 sec. sured cavity temperatures are not accurate because of radiation heat transfer to the thermocouple, differing from the calculated values by as much as 350 K.

Duffy6 inferred heat-flux distributions for the present experiments using a trial-and-error procedure in which a constant relative distribution in the cove was assumed and the time-dependent thermal response of the elevon cove seal test article was calculated. The heat-flux distribution was adjusted until the calculated and measured temperatures agreed reasonably well. References 1-3 and 5 have limited application to the current problems in that the heat-flux distributions were measured on cold surfaces and on geometries that differed from the proposed Orbiter elevon cove seal design.