Abstract
A two-dimensional nozzle with boundary-layer correction to both the shaped and unshaped walls was designed with an adjustable throat to operate at the nominal Mach Number = 3.106 and a static jet pressure of 85 microns of Hg (0.0236 lb. per sq.ft.). The nozzle was evaluated in a low-density free-jet wind tunnel (No. 2) located at the Low Pressures Project, University of California, and met substantially all of the design conditions with the exception of the desired free-stream cross section. Experimental results verified that it would operate over a limited Mach Number range without producing observable disturbances to the uniform exit flow.
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