LIFT/CRUISE FAN EXHAUST SYSTEM RESEARCH PROGRAM

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 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.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1964
Accession Number
AD0609058

Entities

People

  • John Kutney
  • W. A. Fasching

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Base Pressure
  • Boundary Layer
  • Conical Nozzles
  • Drag
  • Exhaust Systems
  • Geometry
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Simulators
  • Static Pressure
  • Test And Evaluation
  • Test Equipment
  • Test Facilities
  • War Colleges

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Fluid Dynamics.