A NASA team of engineers has been organized to design a crew return vehicle for returning International Space Station crew members from orbit. The hypersonic aerothermodynamic characteristics of the X-23/X-24A derived X-38 crew return vehicle are being evaluated in various wind tunnels in support of this effort. Aerothermodynamic data from two NASA hypersonic tunnels at Mach 6 and Mach 10 has been obtained with cast ceramic models and a thermographic phosphorus digital imaging system. General windward surface heating features are described based on experimental surface heating images and surface oil flow patterns for the nominal hypersonic aerodynamic orientation. Body flap reattachment heating levels are examined. Computational Fluid Dynamics tools have been applied at the appropriate wind tunnel conditions to make comparisons with this data.


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    Title :

    Overview of X-38 Hypersonic Aerothermodynamic Wind Tunnel Data and Comparison with Numerical Results


    Contributors:
    C. Campbell (author) / J. Caram (author) / S. Berry (author) / T. Horvath (author) / N. Merski (author)

    Publication date :

    2004


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Overview of X-38 Hypersonic Wind Tunnel Data and Comparison with Numerical Results

    Campbell, C. / Caram, J. / Berry, S. et al. | British Library Conference Proceedings | 1997


    Overview of X-38 Hypersonic Wind Tunnel Data and Comparison with Numerical Results

    Campbell, Charles H. / Caram, Jose / Berry, Scott et al. | NTRS | 1997