The development of an asymmetric type of adjustable supersonic nozzle suitable for application to wind tunnels is described. This new type of nozzle permits continuous adjustment of the test-section Mach number without the requirement of flexible walls. Uniformity of flow within the test section as well as the compression ratio required for the attainment of the supersonic flow are considered.nThe advantages and disadvantages of this nozzle relative to the conventional interchangeable-fixed-block and flexible-wall nozzles are discussed.
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