Flow Investigations in a Stalling Nacelle Inlet Under Disturbed Inflow

  • Simon ÜbelackerEmail author
  • Rainer Hain
  • Christian J. Kähler
Conference paper
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design book series (NNFM, volume 131)


A generic, cold flow-through nacelle under atmospheric disturbed inflow was experimentally investigated. The boundary layer development of the nacelle resembles that of a powered engine at take-off conditions and high mass flow rates. A vortex generator was positioned \({{l}/{c_\text {n}}=3.3}\) in front of the nacelle’s leading edge in order to generate an inhomogeneous inflow. This vortex generator is a motor driven airfoil, which pitches from angles of attack \({\alpha _{\text {vg}}=-11^{\circ }}\) to \({\alpha _{\text {vg}}=11^{\circ }}\) within approximately \({58\,\text {ms}}\). This way, vortices are generated in the wind tunnel. These vortices induce an upward velocity component which is comparable to a realistic gust. The investigations are performed for attached, as well as separated, flow in the nacelle. It is shown that for the attached flow the low speed near-wall area and the turbulent fluctuation velocities are increased. For the higher angle of attack of the nacelle, the interaction with the generic gust increases the size of the turbulent separation bubble as well as the amplitude of the fluctuation velocities. In both cases the changes might lead to problems on the compressor of a powered jet engine. The results indicate crucial distortions due to the interaction of the relatively small generic gust with the flow through the nacelle.


Wind Tunnel Test Section Light Sheet Separation Bubble Vortex Generator 
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  1. 1.
    Klein, S., Hoppmann, D., Scholz, P., Radespiel, R.: High-Lift Airfoil Interacting with a Vortical Disturbance: Wind-Tunnel Measurements. AIAA Journal, 1–12 (2014), doi: 10.2514/1.J053441 Google Scholar
  2. 2.
    Schulze, S.: Experimental Investigations on the Vortex Dynamics of a Stalling Jet Engine Inlet. PhD thesis, Universität der Bundeswehr München, Aeronautics and Astronautics Dept. (2013), ISBN: 978-3-8440-1644-4Google Scholar
  3. 3.
    Vollmers, H.: Detection of vortices and quantitative evaluation of their main parameters from experimental velocity data. Measurement Science & Technology 12, 1199–1207 (2001)CrossRefGoogle Scholar
  4. 4.
    Wartzek, F., Holzinger, F., Brandstetter, C., Schiffer, H.P.: Realistic inlet distortion patterns interacting with a transonic compressor stage. In: 4th International Symposium ‘Simulation fo Wing and Nacelle Stall’, Braunschweig, Germany, pp. 1–2. Springer, December 2014Google Scholar

Copyright information

© Springer International Publishing Switzerland 2016

Authors and Affiliations

  • Simon Übelacker
    • 1
    Email author
  • Rainer Hain
    • 1
  • Christian J. Kähler
    • 1
  1. 1.Institute of Fluid Mechanics and AerodynamicsUniversität der Bundeswehr MünchenNeubibergGermany

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