THE DESIGN OF VARIABLE MACH NUMBER ASYMMETRIC SUPERSONICnNOZZLES BY TWO PROCEDURES EMPLOYING INCLINEDnAND CURVED SONIC LINES

摘要

Two theoretical procedures are developed for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One procedure is applicable at Mach num¬bers less than approximately 3. This approach yields without itera¬tion, a nozzle for which the calculated exit flow is uniform at two Mach numbers and, with proper design, is nearly uniform at Mach numbers between, slightly above, and slightly below these two. The use of an inclined and curved sonic line is an essential feature of this approach. The second procedure requires iteration and is used for designs at Mach numbers exceeding 3. Although it is not a necessary feature, an inclined and curved sonic line is also used in this procedure. In both approaches the flow field downstream of the sonic line is determined using the method of characteristics.