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

By L. S. Fletcher

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The duration of the simulation was chosen so that the total internal heat load was simulated approximately, the experiment being about 93% of flight in terms of the correlation parameter Jp^Ffdt. The effect of variations in the flight elevon deflection is included in the pressure, since the test article elevon was not deflectable. The total external surface heat load during the experiment reached the flight value after 1100 sec. Since the total simulation of 1800 sec exceeded 1100 sec, the total surface heat load was about twice the flight external heat load.

Concluding Remarks Heating results are presented for the forebody of each of the four Pioneer Venus probes entering the atmosphere of Venus at four different entry angles. Solutions, "both laminar and turbulent, are obtained with a viscous-shock-layer (VSL) analysis where the flow is assumed to he in chemical equilibrium. Also, radiative and laminar convective heating results obtained with an approximate analysis are presented. The approximate convective heating results are obtained by using nonadiabatic inviscid values in the convective heating correlations.

Eq. (12) is plotted in Fig. 9 against the seal gap width D, for both cases, together with the measured final mean temperature 42 SCOTT, MURRAY, AND MILHOAN 10000r 8000 - 6000 - 4000 - 2000 - 2000 Fig. 8 Local flight and experimental environment in terms of correlating parameter of the rub tube. For some gap widths, the points are obtained by extrapolating the temperatures to 1800 sec, where the full simulation was not achieved because of premature termination of the run. Good agreement between the measured and predicted temperature is seen in this figure except at large gap widths.

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