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Inviscid-Viscous Interactions of Compressible Convex Corner Flows

  • K. M. Chung
  • P. H. Chang
Conference paper

Introduction

Variable camber concept, such as deflection of flaps or ailerons in cruise, could play a role in performance optimization for current- and future-generation aircrafts. Within the operational flight envelopes, it would change the flowfield and consequently modify aerodynamic characteristics[1]. A study by Szodruch and Hilibig[2] also indicated that variable camber can be employed to improve the transonic maneuvering characteristics of a fighter aircraft. Furthermore, Parndtl-Meyer expansion is well known in supersonic flows. However, the subsonic expansion or transonic expansion flows around a sharp convex corner are less studied. At lower Mach number, the flow is expanded and recompressed around a sharp corner. With increasing Mach number or convex-corner angle, the boundary layer is subject to a rapid acceleration and the flow switches to transonic expansion flow. Noted that Chung[3] proposed a similarity parameter to characterize the flowfield, in which the transition of subsonic and transonic expansion flows is observed at M 2 η=6.14. Shock-induced boundary layer separation is also another concern for application of variable camber concept.

Keywords

Mach Number Sharp Corner Stagnation Pressure Lower Mach Number Freestream Mach Number 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • K. M. Chung
    • 1
    • 2
  • P. H. Chang
    • 1
    • 2
  1. 1.Aerospace Science and Technology Research Center (ASTRC)National Cheng Kung UniversityTaiwan, ROC
  2. 2.Institute of Aerospace and AstronauticsNational Cheng Kung UniversityTaiwan, ROC

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