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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
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- http://id.loc.gov/authorities/subjects/sh85113557
- http://experiment.worldcat.org/entity/work/data/45042687#Topic/boundary_layer_transition
- http://id.worldcat.org/fast/798683
- http://experiment.worldcat.org/entity/work/data/45042687#Topic/aerothermodynamics
- http://experiment.worldcat.org/entity/work/data/45042687#Topic/aerodynamic_heating
- http://id.worldcat.org/fast/798175
- http://id.loc.gov/authorities/subjects/sh85049293
- http://experiment.worldcat.org/entity/work/data/45042687#Topic/flow_visualization
- http://id.loc.gov/authorities/subjects/sh85001429
- http://id.loc.gov/authorities/subjects/sh85001291
- http://experiment.worldcat.org/entity/work/data/45042687#Topic/angle_of_attack
- http://experiment.worldcat.org/entity/work/data/45042687#Topic/wind_tunnel_tests
- http://experiment.worldcat.org/entity/work/data/45042687#Topic/reynolds_number
- http://id.worldcat.org/fast/1096833
- http://id.worldcat.org/fast/927795
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- "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"@en