An experimental investigation of the transonic-flow-generation and shock-wave-reflection characteristics of a two-dimensional wind tunnel with 17-percent-open perforated walls

Thomas B. Sellers, George M. Stakes, Don D. Davis
naca-rm-l54b15a
Apr 1954


The transonic-flow-generation and shock-wave-reflection characteristics of a test section with 17-percent-open perforated top and bottom walls have been investigated in a 3- by 3-inch transonic flow apparatus. A test section of acceptable flow uniformity was obtained through the Mach number range (0.80 to 1.3). Wall divergence was used to eliminate a velocity gradient near a Mach number of 1.3.

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