Wind Tunnel Test to Investigate Aerodynamic Hysteresis Phenomena of the F-4 and F-111 Aircraft Models,

Abstract

Wind tunnel tests were conducted to investigate aerodynamic hysteresis phenomena found in other investigations of the F-4 and F-111 aircraft models. A 1/20-scale model of the F-4C aircraft was used to obtain static force, moment and wing pressure data in pitch and sideslip over a Mach number range from 0.7 to 0.95. A 1/24-scale model of the F-111 aircraft was used to obtain static force and moment data for a Mach number range of 0.7 to 1.3. Data on the F-111 were obtained for wing sweep angles of 26 and 54 deg. In addition, tuft and oil flow visualization data were obtained for selected configurations. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 15, 1979
Accession Number
ADA077196

Entities

People

  • Joseph F. Herman

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Base Pressure
  • Boundary Layer
  • Data Acquisition
  • Data Reduction
  • Dynamic Pressure
  • Flow
  • Flow Visualization
  • Free Stream
  • Mach Number
  • Models
  • Plastic Explosives
  • Static Pressure
  • Test Facilities
  • Tubes
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.