Stagnation Point Heat Transfer Measurements at Super Satellite Speeds

Abstract

Recent lunar and planetary return vehicle studies have stimulated interest concerning the effect upon stagnation point heating due to electronic heat conduction associated with re-entry at speeds greater than 30,000 ft./sec. In order to provide experimental data for comparison with theory, a series of experiments was undertaken in which shock tube techniques were utilised for the measurement of the stagnation point heating of a blunt body over a stagnation enthalpy (Hst/RT0) range of 650 to 900, corresponding to velocities between 32,000 ft./sec. and 39,000 ft. /sec. respectively. The tests were performed in a 1·5 inch diameter shock tube with 3 foot length driver and 16 foot length driven section.

Compilation and correlation of stagnation convective heating rates on spherical bodies

“…4 While diffusion between the condenser and reservoir can be controlled by using a capillary isolation tubing for some applications, sizing based on diffusion is inadequate to prevent the dynamic mass transfer which may accompany equipment or environment mission duty cycles. 5 ' 6 Analytical techniques have been proposed which predict the change in thermal control associated with changes in the external thermal environment, in the heat input to the heat pipe, or with changes such as those which would accompany space radiator degradation. 6 Such analyses are sufficiently detailed, however, that a significant effort may be required to characterize the entire system.…”

“…5 ' 6 Analytical techniques have been proposed which predict the change in thermal control associated with changes in the external thermal environment, in the heat input to the heat pipe, or with changes such as those which would accompany space radiator degradation. 6 Such analyses are sufficiently detailed, however, that a significant effort may be required to characterize the entire system. The following description defines an approximate technique so that set point drift predictions can be made easily.…”

Compilation and correlation of experimental, hypersonic, stagnation point convective heating rates

“…In order to evaluate and compare Eqs, (5) and (6), we have selected a trajectory defined by P =1 atm. Using real-gas, equilibrium, 2 3 ^ normal-shock tabulations ' the resulting total conditions behind the shock as a function of U are presented in Table I.…”