The dynamics of unsteady vortex flow around the wing in the hydrodynamic tunnel was investigated. The hypothesis of cross-sensitivity detachable small vortex excitation flow velocity in the region of leading edge with nasal influx was confirmed.
Unsteady flow around airfoil at large angles of attack
01.10.2013
808328 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch