A Two Dimensional Test of a Single Bay Cold Thrust Augmentation Ejector Wing

A two dimensional model of a single bay cold thrust augmentation ejector wing designed and built by Bell Aerospace Company and utilizing hypermixing nozzles developed by the Aerodynamic Research Laboratory of Wright Patterson Air Force Base was tested both statically and at speed in the Lockheed-Georgia low speed wind tunnel facility. The wing was tested at flap angles of 20 and 30 degrees at airspeeds from 0 to 165 fps and through an angle of attack range of -10 to +32 degrees. The ejector primary pressure ratio was varied from 1.0 to 2.25 and the diffuser area ratio was varied from 1.3 to 2.0. The report presents a detailed description of the model including its air supply and instrumentation systems, the test facility and data reduction equations and methodology. Also, presented is the detailed run schedule, the data limitations and the resulting plotted data.