Evaluation of a Wind Tunnel Technique to Determine Aircraft Departure Characteristics

Abstract

A wind tunnel pilot test was conducted to develop a captive aircraft testing technique. By utilizing wind tunnel research to determine the static aerodynamic forces and moments in conjunction with an on-line digital computer programmed with the equations of motion, a series of aircraft stall/departure type maneuvers was generated. A 1/72-scale A-7D aircraft model was utilized. All maneuvers were initiated at Mach number 0.50 at a simulated altitude of 20, 000 ft.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1974
Accession Number
AD0776317

Entities

People

  • R. W. Butler

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Acquisition
  • Aerodynamic Forces
  • Air Force
  • Aircraft Models
  • Asymmetry
  • Computers
  • Control Surfaces
  • Control Systems
  • Data Acquisition
  • Digital Computers
  • Equations
  • Equations Of Motion
  • Horizontal Stabilizers
  • Mach Number
  • Models
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Control Systems Engineering.
  • Fluid Mechanics and Fluid Dynamics.