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

By L. S. Fletcher

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2) into Eq. (1) and assuming that Tcav is proportional to hcav, To quantify further the heat absorbed from the gas, the rub tube was assumed to be a calorimeter of a known thermal mass. The net heat transferred to it is then Q = mT(dT/dt) where mT is the thermal mass per unit length of elevon, and dT/dt is the rate of temperature rise. , - Q0 (5a or mT(dT/dt) - (m/L)h0 (5b Combining this with Eq. (3), mr(dT/dt) - (pcavCDDh0/V'hcav) (6) Total Convected Heat Flux Estimate As mentioned before, the convected heat flow into the cove is rhh0.

2). 5 kg/sec. The test article was installed in one wall of the duct with the pan side of the test article open to the interior of the test chamber, which allowed the critical area around the rub tube to be viewed during testing and provided a pressure difference across the seal (since the flow in the duct was at a higher pressure than in the chamber). A calibration panel, mounted in the wall of the duct opposite the test article, contained an array of heating rate sensors and pressure transducers to measure experimental conditions.

J. , Button, K. , and Walt erg, G. D. , "Langley Research Center Entry Aerothermodynamic Technology Development in Support of Pioneer Venus Multiprobe Mission Studies," AIAA Paper 75-ll6l, St. Louis, M o . , Sept. 1975. Sutton, K . , July 1973; also AIAA Journal, Vol. 12, Aug. 197^, pp. 1033-1105. Sutton, K. and Falanga, R. A . , "Stagnation Region Radiative Heating With Steady-State Ablation During Venus Entry," Journal of Spacecraft and Rockets, Vol. 10, Feb. 1973, pp. 155-157. ^Falanga, R. A.

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