Possibilities for predicting steady boundary layer behavior are inferred from consideration of case of cone at angle of attack to supersonic stream; semi-infinite cone is useful idealization of nose portion of spike inlet or of nose portion of fuselage of supersonic aircraft or missile.
Three-dimensional laminar boundary-layer flow
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 20 , n 8
1953
10 pages
Bibliography
Article (Journal)
English
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Three-dimensional compressible laminar boundary-layer flow
TIBKAT | 1951
|A Numerical Study of Three-Dimensional Laminar Boundary Layer Flow on Propellers
British Library Conference Proceedings | 1995
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