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Theory of viscous transonic flow over airfoils at high Reynolds numberThis paper considers viscous flows with unseparated turbulent boundary layers over two-dimensional airfoils at transonic speeds. Conventional theoretical methods are based on boundary layer formulations which do not account for the effect of the curved wake and static pressure variations across the boundary layer in the trailing edge region. In this investigation an extended viscous theory is developed that accounts for both effects. The theory is based on a rational analysis of the strong turbulent interaction at airfoil trailing edges. The method of matched asymptotic expansions is employed to develop formal series solutions of the full Reynolds equations in the limit of Reynolds numbers tending to infinity. Procedures are developed for combining the local trailing edge solution with numerical methods for solving the full potential flow and boundary layer equations. Theoretical results indicate that conventional boundary layer methods account for only about 50% of the viscous effect on lift, the remaining contribution arising from wake curvature and normal pressure gradient effects.
Document ID
19770056031
Document Type
Conference Paper
Authors
Melnik, R. E. (Grumman Aerospace Corp. Bethpage, NY, United States)
Chow, R. (Grumman Aerospace Corp. Bethpage, NY, United States)
Mead, H. R. (Grumman Aerospace Corp. Bethpage, N.Y., United States)
Date Acquired
August 9, 2013
Publication Date
June 1, 1977
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 77-680
Meeting Information
Conference on Fluid and Plasmadynamics(Albuquerque, NM)
Funding Number(s)
CONTRACT_GRANT: NAS1-12426
Distribution Limits
Public
Copyright
Other