Propulsion System Integration and Test Program (Steady State). Part 3. Nozzle Interaction Drag Tests

Abstract

Near wake and far wake nozzle jet effects on forces on the aft end of a .09 scale simulated fighter airplane were tested at Mach numbers of .6, .85, 1.27, 1.7 and 2.0. Cold air was used for producing the simulated engine exhaust jets. Model configuration changes included various boattail angles, inlet bluntness, wing sweep, and horizontal tail on and off. Data obtained include chord force, normal force, and pitching moment from an internal balance, external static pressure distributions and chord force determined from integrated pressures, and schlieren and shadowgraph photographs of exhaust plumes.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0858526

Entities

People

  • Robert C. Westphal
  • Robert H. Johnson

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airplanes
  • Base Lines
  • Boundary Layer
  • Fighter Aircraft
  • Geometry
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Propulsion System Components
  • Propulsion Systems
  • Static Pressure
  • Steady State
  • Swept Wings
  • Test And Evaluation
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Rocket Propulsion.