LIFT/CRUISE FAN EXHAUST SYSTEM RESEARCH PROGRAM
Rept. for 6 Jun 1963-3 Apr 1964
GENERAL ELECTRIC CO CINCINNATI OH
Pagination or Media Count:
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 liftcruise fan nacelle installations, are reported. Thrust-, drag-, and discharge-coefficients as well as model surface pressure distributions are presented for the representative liftcruise 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.
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