Research on cooling effect with coolant groove structure parameters in platelet transpiration cooled nosetip
Author:
Publisher
Springer Science and Business Media LLC
Subject
Condensed Matter Physics
Link
http://link.springer.com/content/pdf/10.1007/s11630-010-0406-9.pdf
Reference11 articles.
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2. Salas, M. D., A Review of hypersonics aerodynamics, aerothermodynamics and plasmadynamics activities within NASA’s fundamental aeronautics program. AIAA 2007-4264, 39th AIAA Thermophysics Conference 25–28 June 2007, Miami, FL.
3. Neely, A. J. and Tjong, W. C., Calibration of thermal paints for hypersonic flight test. AIAA 2008-2664 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 28 April–1 May 2008, Dayton, Ohio
4. Glass, D. E., Ceramic matrix composite (CMC) thermal protection systems (TPS) and hot structures for hypersonic vehicles. AIAA-2008-2682, 15th AIAA Space Planes and Hypersonic Systems and Technologies Conference, 28 April–1 May 2008, Dayton, Ohio
5. Glass, D. E., Heat-pipe-cooled leading edges for hypersonic vehicles. NASA/CR-2006, July 2006.
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2. Research progress on active thermal protection for hypersonic vehicles;Progress in Aerospace Sciences;2020-11
3. Self-pumping transpiration cooling with a protective porous armor;Applied Thermal Engineering;2020-01
4. Research on thermal protection by opposing jet and transpiration for high speed vehicle;Aerospace Science and Technology;2016-01
5. Film Cooling Effect on the Nosetip in Hypersonic Flow;Applied Mechanics and Materials;2013-09
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