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

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Therefore, these results, along with the stagnationpoint results (Fig. 19), suggest that the nonablating radiative heat load predicted with the VSL analysis would experience a very small reduction due to coupled carbon-phenolic injection. Remember, however, as was discussed previously, that the VSL radiative heating rates were significantly less than the corresponding inviscid values because of the strongly absorbing boundary layer. The reason that the boundary-layer absorption and the ablation-layer absorption are so similar is that the concentration of CO is substantial in both cases.

Measurements were made inside a constant-width cove gap between the wing and the flap for various angles of attack, flap deflections, freestream Reynolds numbers, and gap widths. Stern and Rowe2 analyzed the data of Ref. 1 and found that the heat flux to the cove walls increased with gap width, pressure, and Reynolds number. The pressure generally increased with flap deflection and angle of attack. However, the pressure in the cove was less than the upstream pressure except in cases of large flap deflection.

The final temperatures obtained during the simulations are discussed in the next section. Final Structural Temperatures Determinations of structural temperatures are obtained by three techniques. The first is by extrapolating the correlation parameter results, the second is from direct measurements in the trajectory simulations, and the third is by solving the three simultaneous equations (7-9) and calculating the temperature rise from the relation AT = (l/mT) J(m/L)h0 dt (11) The first two techniques will give local temperatures, whereas the latter technique will give only an approximate average over the entire structure of the wing/elevon junction.

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