Accession Number:

AD0609058

Title:

LIFT/CRUISE FAN EXHAUST SYSTEM RESEARCH PROGRAM

Descriptive Note:

Rept. for 6 Jun 1963-3 Apr 1964

Corporate Author:

GENERAL ELECTRIC CO CINCINNATI OH

Personal Author(s):

Report Date:

1964-09-01

Pagination or Media Count:

226.0

Abstract:

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.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE