An analytical method for including a variable isentropic exponent in the method of characteristics as applied to the design of rocket nozzles has been obtained, which is independent of the manner in which the initial boundary conditions are specified for the problem. The method incorporates existing thermodynamic data for either frozen or equilibrium composition in the characteristic flow equations of supersonic flow.nThe design of several nozzles was attempted by specification of the initial boundary conditions along the nozzle centerline. It was extremely difficult, however, to specify the flow distribution along the nozzle axis and to obtain solutions to the characteris¬tic equations yielding short-length nozzles.
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