Stability Analysis of Hypersonic Boundary Layer over a Cone at Small Angle of Attack
An investigation on the stability of hypersonic boundary layer over a cone at small angle of attack has been performed. After obtaining the steady base flow, linear stability theory (LST) analysis has been made with local parallel assumption. The growth rates of the first mode and second mode waves...
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| Veröffentlicht in: | Advances in Mechanical Engineering 2014-01, Vol.6, p.217976 |
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| creator | Ji, Feng Liu, Xunhua Wang, Qiang Yuan, Xiangjiang Shen, Qing |
| description | An investigation on the stability of hypersonic boundary layer over a cone at small angle of attack has been performed. After obtaining the steady base flow, linear stability theory (LST) analysis has been made with local parallel assumption. The growth rates of the first mode and second mode waves at different streamwise locations and different azimuthal angles are obtained. The results show that the boundary layer stability was greatly influenced by small angles of attack. The maximum growth rate of the most unstable wave on the leeward is larger than that on the windward. Moreover, dominating second mode wave starts earlier on the leeward than that on the windward. The LST result also shows that there is a “valley” region around 120°~150° meridian in the maximum growth rates curve. |
| doi_str_mv | 10.1155/2014/217976 |
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After obtaining the steady base flow, linear stability theory (LST) analysis has been made with local parallel assumption. The growth rates of the first mode and second mode waves at different streamwise locations and different azimuthal angles are obtained. The results show that the boundary layer stability was greatly influenced by small angles of attack. The maximum growth rate of the most unstable wave on the leeward is larger than that on the windward. Moreover, dominating second mode wave starts earlier on the leeward than that on the windward. The LST result also shows that there is a “valley” region around 120°~150° meridian in the maximum growth rates curve.</description><identifier>ISSN: 1687-8132</identifier><identifier>ISSN: 1687-8140</identifier><identifier>EISSN: 1687-8140</identifier><identifier>EISSN: 1687-8132</identifier><identifier>DOI: 10.1155/2014/217976</identifier><language>eng</language><publisher>London, England: SAGE Publications</publisher><subject>Aircraft ; Boundary layer ; Experiments ; Growth rate ; Reynolds number ; Studies ; Vehicles ; Vortices</subject><ispartof>Advances in Mechanical Engineering, 2014-01, Vol.6, p.217976</ispartof><rights>2014 Feng Ji et al.</rights><rights>Copyright © 2014 Feng Ji et al. Feng Ji et al. 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After obtaining the steady base flow, linear stability theory (LST) analysis has been made with local parallel assumption. The growth rates of the first mode and second mode waves at different streamwise locations and different azimuthal angles are obtained. The results show that the boundary layer stability was greatly influenced by small angles of attack. The maximum growth rate of the most unstable wave on the leeward is larger than that on the windward. Moreover, dominating second mode wave starts earlier on the leeward than that on the windward. The LST result also shows that there is a “valley” region around 120°~150° meridian in the maximum growth rates curve.</description><subject>Aircraft</subject><subject>Boundary layer</subject><subject>Experiments</subject><subject>Growth rate</subject><subject>Reynolds number</subject><subject>Studies</subject><subject>Vehicles</subject><subject>Vortices</subject><issn>1687-8132</issn><issn>1687-8140</issn><issn>1687-8140</issn><issn>1687-8132</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2014</creationdate><recordtype>article</recordtype><sourceid>AFRWT</sourceid><sourceid>BENPR</sourceid><sourceid>DOA</sourceid><recordid>eNptkU1Lw0AQhoMoWGpP_oEFL4LE7vdmj7WoLRQ8tJ6XyWZTUtNs3U2F_HtTI8WDl5nZ4Zl3h3mT5JbgR0KEmFJM-JQSpZW8SEZEZirNCMeX55rR62QSY5VjgSXGUutRslm3kFd11XZo1kDdxSoiX6JFd3Ah-qay6MkfmwJCh1bQuYD8Vx8AzX3jELRovYe67ke3tTvNzdoW7MdNclVCHd3kN4-T95fnzXyRrt5el_PZKgVOeZuq0mleaJA2V1TonGEsSmWtthwopTbnrMi1BVYSYMJayRnu3wXTWWalxWycLAfdwsPOHEK17_c0Hirz0_BhayC0la2dYZZSpTUGnjGulQWpsCgKUGXJhaO817obtA7Bfx5dbM3OH0N_kmiIkEwJqZjuqYeBssHHGFx5_pVgc3LBnFwwgws9fT_QEbbuj94_6DcfXIPM</recordid><startdate>20140101</startdate><enddate>20140101</enddate><creator>Ji, Feng</creator><creator>Liu, Xunhua</creator><creator>Wang, Qiang</creator><creator>Yuan, Xiangjiang</creator><creator>Shen, Qing</creator><general>SAGE Publications</general><general>Sage Publications Ltd</general><general>SAGE Publishing</general><scope>AFRWT</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>8FE</scope><scope>8FG</scope><scope>ABJCF</scope><scope>ABUWG</scope><scope>AFKRA</scope><scope>AZQEC</scope><scope>BENPR</scope><scope>BGLVJ</scope><scope>CCPQU</scope><scope>DWQXO</scope><scope>FR3</scope><scope>H8D</scope><scope>HCIFZ</scope><scope>L6V</scope><scope>L7M</scope><scope>M7S</scope><scope>PIMPY</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PRINS</scope><scope>PTHSS</scope><scope>DOA</scope></search><sort><creationdate>20140101</creationdate><title>Stability Analysis of Hypersonic Boundary Layer over a Cone at Small Angle of Attack</title><author>Ji, Feng ; 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After obtaining the steady base flow, linear stability theory (LST) analysis has been made with local parallel assumption. The growth rates of the first mode and second mode waves at different streamwise locations and different azimuthal angles are obtained. The results show that the boundary layer stability was greatly influenced by small angles of attack. The maximum growth rate of the most unstable wave on the leeward is larger than that on the windward. Moreover, dominating second mode wave starts earlier on the leeward than that on the windward. The LST result also shows that there is a “valley” region around 120°~150° meridian in the maximum growth rates curve.</abstract><cop>London, England</cop><pub>SAGE Publications</pub><doi>10.1155/2014/217976</doi><oa>free_for_read</oa></addata></record> |
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| subjects | Aircraft Boundary layer Experiments Growth rate Reynolds number Studies Vehicles Vortices |
| title | Stability Analysis of Hypersonic Boundary Layer over a Cone at Small Angle of Attack |
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