Supersonic combustion tests with a double- oblique-shock SCRAMjet ina shock tunnel
Author:
Affiliation:
1. ARO, Inc., Arnold Air Force Station, Tenn.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.5970
Reference11 articles.
1. An interaction model of a supersonic laminar boundary layer on sharpand rounded backward facing steps.
2. Higher-Order Boundary-Layer Theory
3. Higher approximations in boundary-layer theory Part 1. General analysis
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