An auxiliary inlet ejector nozzle applicable to a supersonic-cruise aircraft was evaluated over a range of free-stream Mach numbers from 0 to 1.20 at appropriate nozzle pressure ratios. Two primary throat areas were used:one to simulate nonreheat operation, and the other for reheat operation. The fixed-geometry shroud was only used in the closed position. The projected boattail area was 47 percent of the simulated nacelle area. Variation in auxiliary inlets included door type (single and double hinge) and values of tertiary flow area (controlled with fixed-position doors) from 0 to 71. 5 per cent of the shroud exit area. A slightly higher nozzle efficiency was obtained with the double-hinge doors at subsonic-cruise power setting, while the single-hinge doors were a little better at dry-acceleration power setting. At the reheat power setting, the maxi mum nozzle efficiency was obtained with the doors closed at Mach 0.60 and higher.
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