J.M. Nies, H. Olivier

The dependence of upstream moving pressure waves on the free stream and the local Mach number is investigated on the supercritical BAC 3-11 airfoil in transonic flow. The high-instationary behavior of the waves is analyzed in detail from the very weak pressure waves at a subsonic Mach number of M[free stream] = 0.63 to a stationary shock at a transonic Mach number M[free stream] = 0.79. Due to the increasing free stream Mach number the pressure waves gain strength which is accompanied by their steepening and fusion, leading to the formation of instationary shock waves. A further increase of the free stream Mach number finally results in the formation of a recompression shock at an approximate Mach number of M[free stream] = 0.78. In a second step a serrated splitter plate is applied to the trailing edge in order to disturb the vortex/trailing edge interaction which is one of the development mechanism of the pressure waves. The influence of the serrated splitter plate is examined with the focus on the change in wave amplitude and wave behavior.

Deutscher Luft- und Raumfahrtkongress 2013, Stuttgart

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2013

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

urn:nbn:de:101:1-20131223778

pressure wave, transonic airfoil flow

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20.12.2013