NOSE BLUNTNESS EFFECTS ON CONE PRESSURE AND SHOCK SHAPE AT M EQUALS 8
Author:
Affiliation:
1. The War Office, Royal Armament Research and Development Establishment, Fort Halstead, England
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.1963
Reference10 articles.
1. Blunt-Cone Pressure Distributions at Hypersonic Mach Numbers
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1. Combustion Characteristics of Fast Pyrolysis Oils Derived from Hybrid Poplar;Developments in Thermochemical Biomass Conversion;1997
2. CURRENT STATUS OF DROPLET AND LIQUID COMBUSTION;Energy and Combustion Science;1979
3. Measurements of the Flow Field on a 15° Semi-Vertex Angle Blunt Cone at M=8.6;Aeronautical Quarterly;1969-02
4. Hypersonic Laminar Heat Transfer and Boundary Layer Transition on Blunted Cones;Aeronautical Quarterly;1968-11
5. A pneumatically operated `semi-dynamic' calibrator for pressure transducers;Journal of Physics E: Scientific Instruments;1968-11
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