Flow Investigations in a Stalling Nacelle Inlet
A flow-through nacelle was investigated at the Institute of Fluid Mechanics and Aerodynamics of the Universität der Bundeswehr in Munich. The boundary layer loading of the nacelle resembles that of a powered engine at take-off conditions and high mass flow rates, see Schulze (2013). The aim of the project is to generate an experimental validation database in order to develop a physically based numerical code to calculate the flow at the edge of the flight envelope. The investigations concentrated on the flow under an inhomogeneous onstream. Therefore, a vortex generator was positioned 1.74 m in front of the nacelle’s leading edge. This vortex generator is a motor driven airfoil, which pitches from angles of attack of αvg = -11° to αvg = 11° within approximately 60 ms.
Simon Übelacker, Rainer Hain, Christian J. Kähler
Institute of Fluid Mechanics and Aerodynamics, Universität der Bundeswehr München, 85577 Neubiberg, Germany 2016