| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 8055694 | Acta Astronautica | 2018 | 7 Pages |
Abstract
A light and small gas supply device, which uses fuel gas generating with solid fuel as coolant gas, is introduced for opposing jet thermal protection in hypersonic vehicles. A numerical study on heat flux reduction in hypersonic flow with opposing jet is conducted to investigate the cooling efficiency of fuel gas. Flow field and cooling efficiency at different jet temperatures, as well as the effect of fuel gas, are determined. Detailed results show that shock stand-off distance changes with an increase in jet pressure ratio and remains constant with an increase in jet temperature. Cooling efficiency weakens with an increase in jet temperature and can be strengthened by enhancing jet pressure. Lastly, a remarkable heat flux reduction is observed with fuel gas injection with respect to no fuel gas injection when jet temperature reaches 900â¯K, thereby proving the positive cooling efficiency of fuel gas.
Related Topics
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Authors
Binxian Shen, Weiqiang Liu,