Performance Of An Isolated Two Dimensional Variable Geometry Wedge Nozzle With Translating Shroud And Collapsing Wedge At Speeds Up To Mach 2 01
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Performance of an Isolated Two-dimensional Variable-geometry Wedge Nozzle with Translating Shroud and Collapsing Wedge at Speeds Up to Mach 2.01
A wind-tunnel investigation was conducted to determine the aeropropulsion performance (thrust-minus-drag) of a single-engine, variable-geometry, two-dimensional (2-D) wedge nozzle with simulated translating-shroud and collapsing-wedge mechanisms. The investigation was conducted statically and at Mach numbers from 0.60 to 2.01 at an angle of attack of 0 deg and at varied jet total-pressure ratios up to 21, depending on the Mach number. The results indicate that the isolated aeropropulsion performance of a variable-geometry two-dimensional wedge nozzle is competitive with axisymmetric nozzles at transonic and supersonic speeds, but the isolated performance is slightly inferior for static take-off and low subsonic speeds. With the use of a simple tertiary-air ejector, the static take-off performance was increased.