Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher PDF
By L. S. Fletcher
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This small ebook function is to hide an important facets of flight mechanics for complex undergraduate scholars. to maintain velocity with this target, the mathematical point is lovely obtainable and not not easy ( simply uncomplicated derivatives and nearly no indispensable, the few ones have ideas defined within the textual content ).
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Extra info for Aerodynamic Heating and Thermal Protection Systems
72 during the earlier portion of the heat pulse. 4 (pv) wa|| , kg/m2 - s Fig. 6 Effect of carbon-phenolic injection on stagnation-point radiative heating for the large probe (VSL results). 0 Fig. 0 Effect of coupled carbon-phenolic injection on heating rate (large probe, time = 18 sec, VSL results). k sec. The results in Fig. 19 also show that, for most of the radiative heating pulse, the radiative blockage due to carbonphenolic injection reaches a maximum value for a very small mass injection rate and then remains approximately constant as the injection rate is increased.
TTest Program Manager. 27 28 SCOTT, MURRAY, AND MILHOAN L i m mj M p q g Q Q0 Re Re = = = = = = = = = = = = s St t T v V y p 0 = = = = = = = = = length of seal and cove (width of test article) length of seal gap mass flow rate through seal thermal mass of structure = pCpV Mach number pressure heat load on surface Jqdt heat flux heating rate to rub tube total energy convected into cove Reynolds number based on hydraulic diameter Reynolds number of local freestream based on distance from leading edge or nozzle throat distance along cove from e=0 Stanton number time temperature bulk velocity Volume ratio of specific heats density angle around cove from horizontal tangent Subscripts o s w cav = = = = conditions at cove inlet surface upstream of cove inlet wall condition cavity condition Introduction During atmospheric entry of the Shuttle Orbiter, a significant part of the heat load to the internal structure of the wings may be caused by the leakage of hot gases through discontinuities such as the interface gaps at the wing elevons.
Engineering Dept. 13881, Vol. 1, Sept. 1969. 2 Stern, I. and Rowe, W. , "Effect of Gap Size on Pressure and Heating Over a Flap of a Blunt Delta Wing in Hypersonic Flow," Journal of Spacecraft and Rockets, Vol. 4, Jan. 1967. pp. 109-114. , Jr. and Hamilton, H. 4," NASA TN D-4911, Nov. 1968. ^Cooper, L. and Putz, K. , "Generalized Flow in Gaps and Slots Including the Effects of Ablation," Journal of Spacecraft and Rockets, Vol. 11, May 1974, pp. 287-294. 5 Kirlin, R. L. and Schmitt, D. , MCR-73-117, June 1973.
Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher