The laminar compressible boundary-layer in the stagnation-point region of an axisymmetric blunt body including the second-order effect of vorticity interaction-Reference-Cited by-同舟云学术

The laminar compressible boundary-layer in the stagnation-point region of an axisymmetric blunt body including the second-order effect of vorticity interaction

Published:1964-03 Issue:3 Volume:7 Page:341-370
ISSN:0017-9310
Container-title:International Journal of Heat and Mass Transfer
language:en
Short-container-title:International Journal of Heat and Mass Transfer

Author:

Davis R.T.,Flügge-Lotz I.

Publisher

Elsevier BV

Subject

Fluid Flow and Transfer Processes,Mechanical Engineering,Condensed Matter Physics

Reference22 articles.

1. Hypersonic Flow Research;Van Dyke,1962

2. Hypersonic Flow Theory;Hayes,1959

3. S. H. Maslen, Second-order effects in laminar boundary layers. American Rocket Society Preprint 2208-61.

4. Hypersonic shock-layer theory of the stagnation region at low Reynolds number;Cheng,1961

5. Blunt-body heat transfer at hypersonic speed and low Reynolds numbers;Ferri;J. Aerospace Sci.,1961

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1. Second-Order Boundary-Layer Theory;Analytical Fluid Dynamics, Second Edition;2000-12-21

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4. Effect of nose bluntness and cone angle on slender-vehicle transition;AIAA Journal;1988-10

5. Unsteady laminar compressible stagnation-point boundary-layer flow over a three-dimensional body: Higher order effects;International Journal of Engineering Science;1988-01