Zobrazeno 1 - 4
of 4
pro vyhledávání: '"shock-induced boundary layer separation"'
Publikováno v:
Aerospace, Vol 8, Iss 9, p 268 (2021)
A convex corner models the upper surface of a deflected flap and shock-induced boundary layer separation occurs at transonic speeds. This study uses micro-vortex generators (MVGs) for flow control. An array of MVGs (counter-rotating vane type, ramp t
Externí odkaz:
https://doaj.org/article/039220834c4844a380904c17e576d1d1
Publikováno v:
Aerospace, Vol 8, Iss 268, p 268 (2021)
Aerospace
Volume 8
Issue 9
Aerospace
Volume 8
Issue 9
A convex corner models the upper surface of a deflected flap and shock-induced boundary layer separation occurs at transonic speeds. This study uses micro-vortex generators (MVGs) for flow control. An array of MVGs (counter-rotating vane type, ramp t
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::4a1d6cb55e73c20db2a3f5225733a08e
https://www.mdpi.com/2226-4310/8/9/268
https://www.mdpi.com/2226-4310/8/9/268
Akademický článek
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Autor:
Johnston, Thomas A.
Steady and unsteady two-dimensional flowfield analysis was conducted for a Sikorsky SSC-AO9 airfoil in compressible, high Reynolds number flows. Limited verification with experimental measurement was achieved. Computational methods included a steady,
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______2778::d4628592eb37ebf17ecbf2c398184f7d
https://hdl.handle.net/10945/39957
https://hdl.handle.net/10945/39957
