By L. S. Fletcher
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1971, pp. 122-130. 12 Zoby, E. V. , "Empirical Stagnation-Point Heat-Transfer Relation in Several Gas Mixtures at High Enthalpy Levels ," NASA TN D-l+799, 1968. Lees , L. , "Laminar Heat Transfer Over Blunt-Nosed Bodies at Hypersonic Flight Speeds," Jet Propulsion, Vol. 26, April 1956, pp. 259-269. Libby, P. A . , June 1958. Marvin, J. G. and Derwert, G. S . , "Convective Heat Transfer in Planetary Gases," NASA TR R-22^, 1965. "Pioneer Venus," NASA TM X-62379, 1972. 17Moss, James N. , Zoby, E. Vincent, Sutton, Kenneth, and Anderson, E.
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. and Olstad, W. B. , July 197U. Brewer, R. A. , May 1975. 7 Moss, J. N . , Anderson, E. C . , a n d B o l z , C. W . , "Aerothermal Environment for Jovian Entry Probes," AIAA Progress in Astronautics and Aeronautics: Thermophysics of Spacecraft and Outer Planet Entry Probes , Vol.
Knowing m from the solution of Eqs. (7), (8), and (9), the discharge coefficient is obtained through Eq. (2). 34 SCOTT, MURRAY, AND MILHOAN Results and Discussion Two categories of experiments were performed on the test article in the supersonic duct. In the first category, a series of short experiments was conducted in which the external flow parameters and the seal gap width were varied to determine their effects on the internal heating in the test article. From these measurements, the internal heating rate could be correlated with environmental parameters.
Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher