Experimental flowfield visualization of a high alpha wing at Mach 1.62
Experimental oil-flow and tuft patterns and vapor-screen flow-visualization data were obtained on a cambered wing model at Mach = 1.62 for an angle-of attack range of 0-14 deg. These data were used as flow diagnostic tools along with surface-pressure and force data and full-potential theory calculat...
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| Veröffentlicht in: | Journal of aircraft 1987-05, Vol.24 (5), p.335-341, Article 335 |
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| container_end_page | 341 |
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| container_issue | 5 |
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| container_title | Journal of aircraft |
| container_volume | 24 |
| creator | Pittman, James L |
| description | Experimental oil-flow and tuft patterns and vapor-screen flow-visualization data were obtained on a cambered wing model at Mach = 1.62 for an angle-of attack range of 0-14 deg. These data were used as flow diagnostic tools along with surface-pressure and force data and full-potential theory calculations. A large separation bubble was found on the lower wing surface at low angle of attack. The high-angle-of-attack flowfield was characterized by a large attached-flow leading-edge expansion followed by a crossflow shock. At alpha = 14 deg the crossflow shock apparently induced discrete regions of streamwise separated flow, which were clearly indicated in the vapor-screen and oil-flow photographs. |
| doi_str_mv | 10.2514/3.45450 |
| format | Article |
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These data were used as flow diagnostic tools along with surface-pressure and force data and full-potential theory calculations. A large separation bubble was found on the lower wing surface at low angle of attack. The high-angle-of-attack flowfield was characterized by a large attached-flow leading-edge expansion followed by a crossflow shock. 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At alpha = 14 deg the crossflow shock apparently induced discrete regions of streamwise separated flow, which were clearly indicated in the vapor-screen and oil-flow photographs.</description><subject>Aerodynamics</subject><subject>aircraft</subject><subject>Applied fluid mechanics</subject><subject>Exact sciences and technology</subject><subject>flow visualization</subject><subject>Fluid dynamics</subject><subject>Fluid Mechanics And Heat Transfer</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Physics</subject><subject>supersonic flow</subject><subject>wings</subject><issn>0021-8669</issn><issn>1533-3868</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>1987</creationdate><recordtype>article</recordtype><sourceid>CYI</sourceid><recordid>eNp9kE1v1DAQQC1EJZaC-AMcfEBUHLJ4bMcfR1S1BamoFzhbs47ddeUmIXZo6a9v2q6ohFac5jBPb0aPkHfA1rwF-VmsZStb9oKsoBWiEUaZl2TFGIfGKGVfkdelXDHGDNN6RU5PbscwpevQV8w05uEmppA7-juVGXO6w5qGng6RIt2myy3FPG6R3qT-kmKl39FvKawVf0MOIuYS3u7mIfl5evLj-GtzfnH27fjLeYPC2tpw4AqWj3iwHICHzsSorAhCbTYtehCwkUx3yrbeoPQqCgVGC-5RWy1VJw7J0ZN3nIZfcyjVXafiQ87Yh2EuTktpDWMSFvLjf0kutXno9az001DKFKIblx44_XHA3APhhHssupAfdkosHnOcsPep_MW1ZGC1WbDmH6FP9bFjnTDlPdr3T3yPBd0CFQfWaMZarjg8X8WE6K6GeeqXwnssn_Zhu7Ubu-jinHMNt1XcA-rOoxk</recordid><startdate>19870501</startdate><enddate>19870501</enddate><creator>Pittman, James L</creator><general>American Institute of Aeronautics and Astronautics</general><scope>CYE</scope><scope>CYI</scope><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>8FD</scope><scope>H8D</scope><scope>L7M</scope><scope>7TC</scope></search><sort><creationdate>19870501</creationdate><title>Experimental flowfield visualization of a high alpha wing at Mach 1.62</title><author>Pittman, James L</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a399t-212613862e92112ed8ff693e36bb5ac131b407d695c8a4c6f3618732ca79746d3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>1987</creationdate><topic>Aerodynamics</topic><topic>aircraft</topic><topic>Applied fluid mechanics</topic><topic>Exact sciences and technology</topic><topic>flow visualization</topic><topic>Fluid dynamics</topic><topic>Fluid Mechanics And Heat Transfer</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Physics</topic><topic>supersonic flow</topic><topic>wings</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Pittman, James L</creatorcontrib><collection>NASA Scientific and Technical Information</collection><collection>NASA Technical Reports Server</collection><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Technology Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Mechanical Engineering Abstracts</collection><jtitle>Journal of aircraft</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Pittman, James L</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Experimental flowfield visualization of a high alpha wing at Mach 1.62</atitle><jtitle>Journal of aircraft</jtitle><date>1987-05-01</date><risdate>1987</risdate><volume>24</volume><issue>5</issue><spage>335</spage><epage>341</epage><pages>335-341</pages><artnum>335</artnum><issn>0021-8669</issn><eissn>1533-3868</eissn><coden>JAIRAM</coden><abstract>Experimental oil-flow and tuft patterns and vapor-screen flow-visualization data were obtained on a cambered wing model at Mach = 1.62 for an angle-of attack range of 0-14 deg. 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| fulltext | fulltext |
| identifier | ISSN: 0021-8669 |
| ispartof | Journal of aircraft, 1987-05, Vol.24 (5), p.335-341, Article 335 |
| issn | 0021-8669 1533-3868 |
| language | eng |
| recordid | cdi_aiaa_journals_10_2514_3_45450 |
| source | NASA Technical Reports Server; Alma/SFX Local Collection |
| subjects | Aerodynamics aircraft Applied fluid mechanics Exact sciences and technology flow visualization Fluid dynamics Fluid Mechanics And Heat Transfer Fundamental areas of phenomenology (including applications) Physics supersonic flow wings |
| title | Experimental flowfield visualization of a high alpha wing at Mach 1.62 |
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