Abstract
The reduction of aerodynamic heating by opposing jet was experimentally investigated. Geometric ratio of diameters and Mach numbers were fixed, and the flow stability was determined by the total pressure ratio of freestream to opposing jet. It was observed that the reduction of aerodynamic heating caused by the opposing jet proved to be quiet effective at the nose of the blunt body. As the pressure ratio is increased, the heat flux decreases over the model surface, and remarkable reduction of aerodynamic heating was observed in nose regions at high pressure rate.
| Original language | English |
|---|---|
| Pages (from-to) | 233-236 |
| Number of pages | 4 |
| Journal | Journal of Spacecraft and Rockets |
| Volume | 43 |
| Issue number | 1 |
| DOIs | |
| Publication status | Published - Jan 1 2006 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science
Cite this
Experimental study on thermal protection system by opposing jet in supersonic flow. / Hayashi, Kentaro; Aso, Shigeru; Tani, Yasuhiro.
In: Journal of Spacecraft and Rockets, Vol. 43, No. 1, 01.01.2006, p. 233-236.Research output: Contribution to journal › Article
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TY - JOUR
T1 - Experimental study on thermal protection system by opposing jet in supersonic flow
AU - Hayashi, Kentaro
AU - Aso, Shigeru
AU - Tani, Yasuhiro
PY - 2006/1/1
Y1 - 2006/1/1
N2 - The reduction of aerodynamic heating by opposing jet was experimentally investigated. Geometric ratio of diameters and Mach numbers were fixed, and the flow stability was determined by the total pressure ratio of freestream to opposing jet. It was observed that the reduction of aerodynamic heating caused by the opposing jet proved to be quiet effective at the nose of the blunt body. As the pressure ratio is increased, the heat flux decreases over the model surface, and remarkable reduction of aerodynamic heating was observed in nose regions at high pressure rate.
AB - The reduction of aerodynamic heating by opposing jet was experimentally investigated. Geometric ratio of diameters and Mach numbers were fixed, and the flow stability was determined by the total pressure ratio of freestream to opposing jet. It was observed that the reduction of aerodynamic heating caused by the opposing jet proved to be quiet effective at the nose of the blunt body. As the pressure ratio is increased, the heat flux decreases over the model surface, and remarkable reduction of aerodynamic heating was observed in nose regions at high pressure rate.
UR - http://www.scopus.com/inward/record.url?scp=33644746286&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=33644746286&partnerID=8YFLogxK
U2 - 10.2514/1.15332
DO - 10.2514/1.15332
M3 - Article
AN - SCOPUS:33644746286
VL - 43
SP - 233
EP - 236
JO - Journal of Spacecraft and Rockets
JF - Journal of Spacecraft and Rockets
SN - 0022-4650
IS - 1
ER -