Hypersonic lee-surface heating alleviation on delta wing by apex-drooping
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Va.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.6442
Reference5 articles.
1. Effect of vortices on delta wing lee-side heating at Mach 6
2. The Theory of Laminar Boundary Layers in Compressible Fluids
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1. References;The Aerodynamic Design of Aircraft;2012-09-15
2. Types of flow on the lee side of delta wings;Progress in Aerospace Sciences;1997-03
3. Aerothermodynamic measurements on a proposed assured crew return vehicle (ACRV) lifting-body configuration at Mach 6 and 10 in air;5th Joint Thermophysics and Heat Transfer Conference;1990-06-18
4. Lee surface flow phenomena over Space Shuttle at large angles of attack at M infinity = 6;13th Aerospace Sciences Meeting;1975-01-20
5. Lee-side vortices on delta wings at hypersonic speeds.;AIAA Journal;1972-11
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