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
2013-10-01
808328 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch