Direct Calculation of Pressure Distribution on Blunt Hypersonic Nose Shapes With Sharp Corners
- 1 November 1961
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of the Aerospace Sciences
- Vol. 28 (11) , 872-876
- https://doi.org/10.2514/8.9227
Abstract
No abstract availableKeywords
This publication has 2 references indexed in Scilit:
- Transonic rotational flow over a convex cornerJournal of Fluid Mechanics, 1960
- An Approximate Solution of the Direct Supersonic Blunt-Body Problem for Arbitrary Axisymmetric ShapesJournal of the Aerospace Sciences, 1960