Evolution of Vortex Structures on the Leeward Side of a Delta Wing |
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Authors: | M D Brodetsky E Krause S B Nikiforov A A Pavlov A M Kharitonov A M Shevchenko |
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Institution: | (1) Institute of Theoretical and Applied Mechanics, Siberian Division, Russian Academy of Sciences, Novosibirsk, 630090;(2) Aachen Institute of Aerodynamics, Aachen, 52062, Germany |
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Abstract: | Results of an experimental study of a supersonic flow around the leeward side of a delta wing are presented. The experiments are performed on three delta wings with leading–edge sweep angles = 68°, 73°, and 78° for Mach numbers M =2—4 and angles of attack = 0—22°. Data on the structure and position of internal shock waves are obtained; the size and location of primary and secondary vortices are found. New regimes of the flow around a delta wing are identified. The chart of flow regimes around delta wings is refined and extended. |
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