Ejector Blown Lift/Cruise Flap Wind Tunnel Investigation.
Final rept. Dec 71-May 73,
AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
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The report presents the results of a wind tunnel investigation of a two dimensional powered wing section model employing a trailing edge ejector flap as a combination high lift and cruise propulsion device. The concept investigated was proposed for application to STOL aircraft. Thrust augmentation data is presented for the static zero velocity, Mach .12 and Mach .3 conditions. The compact ejector employed had a nominal inlet area ratio of 5 and produced a peak thrust augmentation ratio of 1.3 under static conditions. The thrust augmentation capability of the ejector decreased rapidly between 0 and Mach .12 to a value of approximately 1.0. Between Mach .12 and .3, the thrust produced by the ejector reduced at a much slower rate. Good high lift performance was obtained with the model in the low speed flight regime. Author