A note on adaptive-wall wind tunnels

In principle, the adaptive-wall wind tunnel is an attractive alternative to traditional methods of accounting for wind-tunnel wall interference. The concept has been successfully demonstrated for two-dimensional flows at moderately supercritical Mach numbers, but more work needs to be done before the method can be used in production testing. In this paper experimental techniques for rapid assessment and correction of wall interference are described. The procedure is based on laser velocimetry measurements on two control surfaces and on the use of a dedicated computer for rapid data processing. The experimental arrangement and instrumentation are described and typical results from an experiment on a nonlifting NACA 0012 airfoil at M = 0.78 are discussed. Nomenclature c = airfoil chord C p = pressure coefficient: (p -p^) / [ (Yi)p FjJ M = Mach number, subscript p = static pressure u = axial perturbation velocity component v = normal perturbation velocity component x = axial distance y = distance normal to x axis a = angle of attack p = densitySubscripts cl = calculated value at level 1 c2 = calculated value at level 2 ml = measured value at level 1 m2 = measured value at level 2 oo = freestream 1,2 = at levels 1 and 2

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Numerical Simulations of a Segmented-Plenum, Perforated, Adaptive-Wall Wind Tunnel

Erickson¹,

Homicz²

1982

AIAA Journal

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A note on adaptive-wall wind tunnels

Cited by 8 publications

References 1 publication

Advances in the Understanding and Computation of Unsteady Transonic Flow

Advances in the Understanding and Computation of Unsteady Transonic Flow

Adaptive-wall wind-tunnel development for transonic testing

Numerical Simulations of a Segmented-Plenum, Perforated, Adaptive-Wall Wind Tunnel

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