A relaxation method for the solution of rotational transonic nozzle flow.
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This work was successful in demonstrating the feasibility, accuracy, and importance of including the effects of total pressure gradients in evaluating propulsion nozzle performance. In fact, in the cases considered here inlet flow nonuniformities produced effects greater than those which resulted from a consideration of just the two-dimensionality of the flow. For the hyperbolic nozzle and the turbofan bypass nozzle, two-dimensional effects were found to produce a reduction in discharge coefficient of only 0.1 to 0.6%. Whereas, nonuniform inlet flow effects produced an additional decrease in the discharge coefficient of about 1%. Agreement with the solutions of Oswatitsch and Rothstein (18) and Wehofer and Moger (6) is good. However, available experimental data does not provide conclusive proof of the program's accuracy. It is expected that more test data will soon be available from tests conducted by Wehofer and Matz at the Arnold Engineering Development Center. Also, more experimental data is available for nozzles with subsonic exhausts and for convergent nozzles (2). When, as recommended in the next section, the capability of handling subsonic exit flow and convergent nozzles is incorporated into the program, further comparison to experimental data will be possible.
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