Laminar boundary layer on a cone at incidence in supersonic flow
Author:
Affiliation:
1. GENERAL ELECTRIC CO., RE-ENTRY AND ENVIRONMENTAL SYSTEMS DIV., PHILADELPHIA, PA.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1970-48
Reference31 articles.
1. AN INTEGRAL METHOD FOR CALCULATION OF SUPERSONIC LAMINAR BOUNDARY LAYER WITH HEAT TRANSFER ON YAWED CONE
2. Chang, P. K., Smith, R. A.,Cassarella, M. J., and Oh.Y. H. "Analysis of Laminar Flow and Heat Transfer on a Hypersonic Cone at High Angle of Attack," Technical Report No. 2, MechanicalEngineeringDepartment,Catholic University of America, August 1968.
3. Laminar Heat Transfer on Three-Dimensional Blunt Nosed Bodies in Hypersonic Flow
Cited by 4 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献
1. The solution of sharp-cone boundary-layer equations in the plane of symmetry;Journal of Fluid Mechanics;1972-08-22
2. Supersonic laminar boundary layer near the plane of symmetry of a cone at incidence;Journal of Fluid Mechanics;1972-01-11
3. Boundary layer on a hypersonic sharp cone at small angle of attack;AIAA Journal;1971-02
4. Hypersonic boundary layer studies on a spinning sharp cone at angle of attack;9th Aerospace Sciences Meeting;1971-01-25
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