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By L. S. Fletcher

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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.

Figure 20 presents downstream coupled results for the large probe at 18 sec. The radiative and convective heatingrate distributions are compared with the corresponding noinjection values. Also, the coupled carbon-phenolic injectionrate distribution is presented. The coupled carbon-phenolic injection rate causes a 20% reduction in the radiative heating at the stagnation point; however, the reduction decreases with increasing distance from the stagnation point until the sphere-cone tangency point is reached.

10-12 indicate that the pressure drop increases with smaller 6/D. This reduced pressure may not be as significant in the flight case where the boundary layer is thicker than in the experiments. For example, in flight the boundary-layer thickness 6 near the elevon hinge line is estimated to be from 5to 15 cm, depending on the time during the trajectory and the particular location. 457 cm, the ratio 6/D in flight is from 10 to 30, and 6/D in the experiments is about 1 to 2. From Fig. 85. Therefore, the inlet pressure in flight may be about twice that in the experiments for large gap widths.

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