Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher
By L. S. Fletcher
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Extra resources for Aerodynamic Heating and Thermal Protection Systems
Figure 15 displays the radiative heating-rate distributions at various times during entry for the large probe (results for the small probes are given in Ref. 17) • The radiative distributions shown are those obtained assuming the flow to be laminar. When the flow is assumed to be turbulent, the radiative heating-rate distributions are approximately the same as those for laminar flow. The results show that the radiative heating-rate distributions are nonsimilar. 0 Fig. 0 Radiative heating-rate distributions during entry (VSL results, large probe).
A calibration panel, mounted in the wall of the duct opposite the test article, contained an array of heating rate sensors and pressure transducers to measure experimental conditions. The geometry of the supersonic duct and location of the calibration panel transducers are shown in Fig. 2. TE ST STATIONO HEAT TRANSFER RATE SENSORS A PRESSURE TAPS Fig. 2 Schematic of duct giving pertinent dimensions and locations of heat-transfer rate sensors and pressure taps. 32 SCOTT, MURRAY, AND MILHOAN Analysis There are two aspects of the analysis of the cove seal measurements.
The significance of radiation cooling, together with the development of the entropy layer, has important implications^^ for the calculation of convective heating rates. The nature of the inviscid flow for the present probe configurations is characterized by large density, temperature, enthalpy, and velocity gradients within the inviscid entropy layer near the body surface. Evidence of the inviscid (approximate solution) temperature and velocity gradients for the large probe (time = 18 sec) is shown in Figs.