Design of the thermal protection system for any hypersonic flight vehicle requires determination of both the peak temperatures over the surface and the heating-rate history along the flight profile. In this paper, the process used to generate the aerothermal environments required for the X-34 Testbed Technology Demonstrator thermal protection system design is described as it has evolved from a relatively simplistic approach based on engineering methods applied to critical areas to one of detailed analyses over the entire vehicle. A brief description of the trajectory development leading to the selection of the thermal protection system design trajectory is included. Comparisons of engineering heating predictions with wind-tunnel test data and with results obtained using a Navier-Stokes flowfield code and an inviscid/boundary layer method are shown. Good agreement is demonstrated among all these methods for both the ground-test condition and the peak heating flight condition. Finally, the detailed analysis using engineering methods to interpolate the surface-heating-rate results from the inviscid/boundary layer method to predict the required thermal environments is described and results presented.


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    Engineering Aerothermal Analysis for X-34 Thermal Protection System Design

    Wurster, Kathryn E. / Riley, Christopher J. / Zoby, E. Vincent | NTRS | 1998


    Engineering Aerothermal Analysis for X-34 Thermal Protection System Design

    K. E. Wurster / C. J. Riley / E. V. Zoby | NTIS | 1998


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    Kathryn E. Wurster / Christopher J. Riley / E. Vincent Zoby | AIAA | 1999


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    Wurster, K. E. / Riley, C. J. / Zoby, E. V. et al. | British Library Conference Proceedings | 1998


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    Wurster, Kathryn / Riley, Christopher / Zoby, E. | AIAA | 1998