Eskandarian, Azim2020-12-152020-12-151983http://hdl.handle.net/10919/101430An inverse method for the design of exhaust nozzles with a specified transonic pressure distribution is presented. A problem of mixed Neumann and Dirichlet boundary condition is solved. A successive line relaxation process is used to solve the array of velocity potentials in the entire flow field. The streamlines are then displaced to produce boundaries which match a desired pressure distribution. Various cases are tested to verify the reliability of the method. The design calculation proves to be efficient and accurate.x, 58 leavesapplication/pdfenIn CopyrightLD5655.V855 1983.E842Aerodynamics, TransonicJet nozzlesThesis