An Approximate Solution of the Direct Supersonic Blunt-Body Problem for Arbitrary Axisymmetric Shapes
- 1 May 1960
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of the Aerospace Sciences
- Vol. 27 (5) , 361-370
- https://doi.org/10.2514/8.8540
Abstract
No abstract availableThis publication has 8 references indexed in Scilit:
- An Experimental Investigation of Blunt Body Stagnation Point Velocity GradientARS Journal, 1959
- On the Numerical Calculation of Detached Bow Shock Waves in Hypersonic FlowJournal of the Aerospace Sciences, 1958
- Inviscid Hypersonic Flow Past Blunt BodiesJournal of the Aeronautical Sciences, 1957
- Inviscid Hypersonic Flow Over Blunt-Nosed Slender BodiesJournal of the Aeronautical Sciences, 1957
- Investigation of Local Laminar Heat Transfer on a Hemisphere for Supersonic Mach Numbers at Low Rates of Heat FluxJournal of the Aeronautical Sciences, 1957
- Stagnation Point of a Blunt Body in Hypersonic FlowJournal of the Aeronautical Sciences, 1957
- The Rotational Field Behind a Curved Shock Wave Calculated by the Method of Flux AnalysisJournal of the Aeronautical Sciences, 1956
- Readers ForumJournal of the Aeronautical Sciences, 1956