Ejector Shroud Aerodynamics,
ROCKWELL INTERNATIONAL COLUMBUS OH NORTH AMERICAN AIRCRAFT DIV
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An experimental and analytical study has been conducted to determine the effect of shroud parameters on ejector thrust augmentation. The ejector shroud is analogous to a wing operating in a non-linear stream and potential flow methods were utilized to predict ideal pressure distributions on the shroud. Scale model tests were conducted to determine actual forces and pressure distributions on shroud components. Experimental data were obtained for symmetrically increased flap lengths LW and asymmetric flap lengths. It is shown that flap length increases produce higher thrust augmentation ratios by delaying stall to higher diffuser area ratios.