Laminar boundary layer on a cone at incidence in supersonic flow
Author:
Affiliation:
1. General Electric Company, Philadelphia, Pa.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.6203
Reference39 articles.
1. AN INTEGRAL METHOD FOR CALCULATION OF SUPERSONIC LAMINAR BOUNDARY LAYER WITH HEAT TRANSFER ON YAWED CONE
2. Laminar Heat Transfer on Three-Dimensional Blunt Nosed Bodies in Hypersonic Flow
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