SUPERSONIC FLOW PAST BLUNT BODIES WITH LARGE SURFACE INJECTION
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Publisher
Elsevier
Reference13 articles.
1. Finite difference method for numerical computation of discontinuous solutions of fluid dynamics;GODUNOV;Mat. Sbornik,1959
2. Helium injection into the boundary layer at an axisymmetric stagnation point;FOX;Journal of Aerospace Sciences,1962
3. The Downstream Influence of Mass Transfer at the Nose of a Slender Cone, Polytechnic Institute of Brooklyn, PIBAL Rep. No. 634, WADD TR 60–892 (May 1961); also;CRESCI;Journal of the Aerospace Sciences,1962
4. The homogeneous boundary layer at an axi-symmetric stagnation point with large rates of injection;LIBBY;Journal of the Aerospace Sciences,1962
5. Experimental investigation of the downstream influence of stagnation point mass transfer;LIBBY;Journal of the Aerospace Sciences,1961
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