The boundary effects on an 18-inch span, 60° triangular wing model tested in the 26-inch Langley transonic blowdown tunnel are shown to cause only small decreases in the lift-curve slopes from those obtained with the same model in the Langley 8-foot transonic tunnel;the decreases amount to less than 0.001 per degree and 0.003 per degree at Mach numbers of 0.80 and 0.975, respectively. The theory of a previously published paper (NACA RM L53A26), although not exactly applicable to the present case, gave corrections to the lift-curve slopes obtained in the smaller tunnel which appeared to be of the correct sign and of the proper order of magnitude.
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