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Analysis of Wind Tunnel Wall Interference Effects on Subsonic Unsteady Airfoil Flows
 

Summary: Analysis of Wind Tunnel Wall Interference Effects
on Subsonic Unsteady Airfoil Flows
Karthikeyan Duraisamy
University of Maryland, College Park, Maryland 20742
William J. McCroskey
U.S. Army Aeroflightdynamics Directorate, NASA Ames Research Center,
Moffett Field, California 94035
and
James D. Baeder
University of Maryland, College Park, Maryland 20742
DOI: 10.2514/1.28143
In this work, the effect of wall interference on steady and oscillating airfoils in a subsonic wind tunnel is studied. A
variety of approaches including linear theory, compressible inviscid and viscous computations, and experimental
data are considered. Integral transform solutions of the linearized potential equations show an augmentation of the
lift magnitude for steady flows when the wall is close to the airfoil surface. For oscillating airfoils, lift augmentation is
accompanied by a significant change in the phase of the lift response. Idealized compressible Euler calculations are
seen to corroborate the linear theory under conditions that are sufficiently away from acoustic resonance. Further,
the theory compares well with compressible Reynolds-averaged Navier­Stokes calculations and experimental
measurements over a wide range of attached flows at subsonic Mach numbers. The present methodology can thus be
used to predict wall interference effects and also to help extrapolate linear and nonlinear (dynamic stall) wind tunnel

  

Source: Alonso, Juan J. - Department of Aeronautics and Astronautics, Stanford University

 

Collections: Engineering