The Effect of Diamond Injector Geometry on Supersonic Jet Interaction Secondary Flow
保存先:
| 出版年: | 44th AIAA Aerospace Sciences Meeting and Exhibit; Reno, NV; USA; 9-12 Jan. 2006 (Jan 9, 2006), p. 1-17 |
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| 第一著者: | |
| その他の著者: | , |
| 出版事項: |
American Institute of Aeronautics and Astronautics, 1801 Alexander Bell Drive, Suite 500, Reston, VA, 20191-4344, USA, [URL:http://www.aiaa.org]
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| 主題: | |
| オンライン･アクセス: | Citation/Abstract |
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| 抄録: | Reynolds averaged Navier-Stokes simulations of transverse gaseous injection into high-speed flows were performed. Diamond shaped injector orifices with different half-angles were used in these simulations. The GASP flow solver was used in this study. The results obtained were compared to the baseline case of the 15 deg half-angle, Mach 5.0 test case reported in a previous study. The goal of this work was to examine the near field flow structures around the injector and compare them to the structures observed in the baseline case. The results obtained indicate that the barrel shock shape and the LCVP flow structure seen in the baseline case was not observed when the injector half-angle was changed to either 10 or 20 deg, at Mach 5.0. However, at a freestream Mach number of 2.0 and injector half-angles of 10 and 15 deg, the near field structures resembled the baseline case. In addition to these studies, two dual injector configurations were studied and results indicate that the fusion of the interaction shocks generated by the injectors leads to a quasi-planar shock that can be used as a flow turning device in high-speed aircraft. |
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| ISSN: | 0146-3705 |
| ソース: | Advanced Technologies & Aerospace Index |