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  1. 1
    Effect of fin leading edge sweep on shock-shock interaction at Mach 6 /
    by Berry, Scott A.
    Published 1996
    Government Document Book
  2. 2
    Results of aerothermodynamic and boundary layer transition testing of 0.0362-Scale X-38 (Rev 3.1) vehicle in NASA Langley 20-inch Mach 6 tunnel /
    Published 1997
    Government Document Book
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