Study on Flowfield around Hypersonic Vehicle with Forward Swept Wing
Project/Area Number |
04650058
|
Research Category |
Grant-in-Aid for General Scientific Research (C)
|
Allocation Type | Single-year Grants |
Research Field |
Aerospace engineering
|
Research Institution | Fukuyama University |
Principal Investigator |
NISHIO Masatomi Fukuyama Univ.Faculty of Engineering Associate Professor, 工学部, 助教授 (40031132)
|
Co-Investigator(Kenkyū-buntansha) |
NISHIO Masatomi Fukuyama Univ.Faculty of Engineering Associate Professor (40031132)
|
Project Period (FY) |
1992 – 1994
|
Project Status |
Completed (Fiscal Year 1994)
|
Budget Amount *help |
¥2,100,000 (Direct Cost: ¥2,100,000)
Fiscal Year 1994: ¥400,000 (Direct Cost: ¥400,000)
Fiscal Year 1993: ¥400,000 (Direct Cost: ¥400,000)
Fiscal Year 1992: ¥1,300,000 (Direct Cost: ¥1,300,000)
|
Keywords | Hypersonic Vehicle / Forward Swept Wing / Shock Wave / Streamline / Pressure Distribution / 温度分布 / 極超音速飛翔休 / 極超音速流 |
Research Abstract |
Cross sectional shock shapes over a hypersonic forward swept wing have been visualized under the condition of various kinds of the angle of attack of the wing. Moreover, cross sectional shock shapes over hypersonic forward swept wings have been visualized under the condition of various kinds of the forward swept wings' shape. In order to visualize the cross sectional shock shapes, the two electric discharge methods (the first electric discharge methods and the second electric discharge method) have been used.
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Report
(4 results)
Research Products
(28 results)