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A finitc, element approach for integrated fluidthermal-structural analysis of aerodynamically heated leading edges is presented. The Navier-Stokes equations for high speed compressible flow, the energy equation, and the quasi-static equilibrium equations for the leading edge are solved using a single finiite element approach in one integrated, vectorized computer program called LIFTS. The fluidthermal-structural coupling is studied for Mach 6.47 flow over (a 3-inch diameter cylinder for which the flow behavior and the aerothermal loads are calibrated by experimerrtal data. Issues of the thermal-structural response are studied for hydrogen cooled, super thermal conducting leading edges subjected to intense aerodynamic heating.

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