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Record Nr. |
UNINA9910781414703321 |
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Titolo |
Hypersonic flow research [[electronic resource] ] : a selection of technical papers based mainly on a symposium of the American Rocket Society held at Massachusetts Institute of Technology / / edited by Frederick R. Riddell |
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Pubbl/distr/stampa |
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New York, : Academic Press, 1962 |
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ISBN |
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1-60086-481-3 |
1-60086-262-4 |
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Descrizione fisica |
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1 online resource (768 p.) |
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Collana |
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Progress in astronautics and rocketry ; ; v. 7 |
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Altri autori (Persone) |
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Disciplina |
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Soggetti |
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Lingua di pubblicazione |
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Formato |
Materiale a stampa |
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Livello bibliografico |
Monografia |
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Note generali |
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Sponsored jointly by the Air Force Office of Scientific Research and the American Rocket Society. |
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Nota di bibliografia |
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Includes bibliographical references. |
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Nota di contenuto |
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""Cover""; ""Title""; ""Copyright""; ""Hypersonics Committee""; ""Preface""; ""Contents""; ""The ARS � AFOSR International Hypersonics Conference: Summary and Comments""; ""A. Hypersonic Flow at Low Reynolds Number""; ""Introduction""; ""Density Behavior along the Stagnation Line of a Blunt Body in Hyperthermal Flow""; ""Second-Order Compressible Boundary Layer Theory with Application to Blunt Bodies in Hypersonic Flow""; ""Comment on above paper""; ""Rarefied Hypersonic Flow over a Sphere""; ""The Rayleigh Problem for a Dissociated Gas""; ""B. Chemical Kinetic Effects in Hypersonic Flow"" |
""Introduction""""Chemical Kinetics: A General Introduction""; ""Chemical Kinetics of High Temperature Air""; ""Chemical Effects in External Hypersonic Flows""; ""Radiation at Hypersonic Speeds""; ""Radiation from the Nonequilibrium Shock Front""; ""C. Inviscid Hypersonic Flow""; ""Introduction""; ""Slender Wings at High Angles of Attack in Hypersonic Flows""; ""Newtonian Theory of Hypersonic Flow at Large Distances from Bluff Axially Symmetric Bodies""; ""Shock Layer Structure and Entropy Layers in Hypersonic Conical Flows""; ""Theory of Entropy Layers and Nose Bluntness in Hypersonic Flow"" |
""D. Experimental Techniques I""""Introduction""; ""Aerodynamic Testing at Mach Numbers from 15 to 20""; ""The Duration and Properties of the |
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