A simplified analysis for re-entry stagnation point heat transfer from a viscous nongray radiating shock layer
Author:
Affiliation:
1. U.S. NAVY, ORDNANCE SYSTEMS COMMAND, NAVAL ORDNANCE LAB., AEROPHYSICS DIV., HYPERSONICS GROUP, SILVER SPRING, MD.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1968-164
Reference23 articles.
1. Study of equilibrium air total radiation.
2. Convective and radiative heat transfer during superorbital entry.
Cited by 14 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. PREDICTION OF THERMAL FLUXES TO VERY BLUNT PLANETARY ENTRY VEHICLES BY THE INTEGRAL METHOD;Proceedings of the XXth International Astronautical Congress;1972
2. Nongray radiative heat transfer in high- temperature nonisothermal CO2-N2 mixtures;AIAA Journal;1970-11
3. Influence of upstream absorption on the inviscid stagnation region shock layer radiation;AIAA Journal;1970-10
4. RADIATING FLOWS DURING ENTRY INTO PLANETARY ATMOSPHERES;Propulsion Re-Entry Physics;1970
5. An engineering survey of radiating shock layers.;AIAA Journal;1969-09
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