Normal shock wave-turbulent boundary layer interactions in transonic intakes at incidence

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Change log
Coschignano, Andrea  ORCID logo
Sheaf, C 
Platt, E 

© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The flow field around a transonic engine inlet lip at high incidence is investigated for a variety of flow conditions around the design point. Generally, the flow on the upper surface of the lip is characterised by a supersonic region, terminated by a near-normal shock wave. At the nominal design point, the shock is not strong enough to cause significant flow separation, resulting only in marginal losses in pressure recovery. Off-design conditions were explored by altering the angle of attack as well as changing the mass flow rate over the upper lip, intended to mimic the effect of an increase in engine flow. The results suggest that angle of attack has the greatest effect on the flow field. In particular, even a relatively small increase of 2 ◦ can lead to large and highly unsteady flow separation with an associated shock oscillation. Both qualitative and quantitative measurements suggest a noticeably reduced aerodynamic performance resulting from higher incidence operation. In contrast, an increase of up to 5.2% in mass flow over the upper part of the intake lip did not result in large separated regions or flow-field unsteadiness.

Journal Title
AIAA Aerospace Sciences Meeting, 2018
Conference Name
2018 AIAA Aerospace Sciences Meeting
Journal ISSN
Volume Title
American Institute of Aeronautics and Astronautics
EPSRC (1621817)