Abstract
An application of the inviscid (Euler) version of the NPARC code to a finite thickness airfoil inside a test section with impermeable walls is described. Three different, physically meaningful, choking patterns are generated. It is shown that, in contrast to predictions from singular perturbation analyses, the computed wind-tunnel results are not correctable to equivalent freestream conditions when flow is choked. Nomenclature A = cross-sectional area Cp = pressure coefficient CltL = upper-surface lift coefficient c = chord length of airfoil h = height of test section M = local Mach number Mch = choking Mach number Mch = choking Mach number, subsonic MS' = choking Mach number, supersonic MT = wind-tunnel Mach number M^ = Mach number imposed on outer boundary t = maximum thickness of airfoil jc = chordwise coordinate y - ratio of specific heats I. Introduction
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