Compressible Gas Flow in Nozzle taking Boundary Layer into Consideration : Part 3 Calculations of Convergent and Divergent Nozzles, and Schrielen-photo Experiments

Abstract

The theoretical calculations of compressible gas flow of nozzle accompanied by laminer or turbulent boundary layer at its wall, are extended to the case of convergent and divergent nozzles in this paper, using assumptions, equations and methods similar to those of the foregoing papers, which discussed the parallel walled straight simple nozzle only. And Schrielen photographic experiments of miscellaneous nozzles of conv. div. and parallel walls are done. By the results from above calculations and experiments, there exists supersonic main flow inside the nozzle end of parallel nozzle, and though, of convergent nozzle. And in divergent nozzle, there are some cases where the acoustic line is put away from throat into the divergent part.