FULL SCALE WIND TUNNEL TEST REPORT

Abstract

The test program included aerodynamic, thermodynamic and mechanical evaluation of the complete flight type aircraft system at flight speeds equivalent to hover up through 100 knots in both the conventional and fan power modes of flight. The report summarizes the more important aerodynamic performance obtained during the test program. The data are presented graphically in coefficient form to provide a consistent basis of comparison. The aerodynamic results obtained during these tests may be summarized by saying that the aircraft, as designed and tested, has adequate control power, lift, horizontal thrust and static stability to permit safe transitional flight between a hover lift-off and conversion to the jet mode of flight. The results of this wind tunnel test program have proven to be a valuable asset during conduct of the flight test program. Using these data, predictions of aircraft performance have been verified by actual measured flight data.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0654043

Entities

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Actuators
  • Aerodynamic Forces
  • Aircrafts
  • Birds
  • Control Sticks
  • Control Surfaces
  • Control Systems
  • Data Processing
  • Horizontal Stabilizers
  • Load Cells
  • Measurement
  • Propulsion Systems
  • Recording Systems
  • Rigging
  • Spars
  • Test Equipment
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Test and Evaluation
  • Aviation Science / Aeronautics.