Lift/Cruise Fan Exhaust System Research Program

摘要

Results of static and wind tunnel cold-flow scale-model tests of convergent-conical nozzles and convergent-plug nozzles with a fore body and various afterbodies, simulating lift/cruise fan nacelle installations, are reported. Thrust-, drag-, and discharge-coefficients as well as model surface pressure distributions are presented for the representative lift/cruise fan nozzle pressure ratio range of 1.2 to 2.4 and flight Mach numbers of .0, .4, .6, .8, and .9. The test results are analyzed and compared to other test data and analytical calculations. (Author)