HEAVY-LIFT TIP TURBOJET ROTOR SYSTEM. VOLUME 8. WIND-TUNNEL STUDIES

Abstract

Wind-tunnel tests were conducted to provide nacelle design information which would assist in the design of the tip turbojet installation. The model was constructed to provide for single, over-under, and side-by-side engine arrangements. The nacelle loads were measured with a six-component strain-gage balance. Tests were conducted at nacelle Reynolds Numbers from 450, 000 to 1,830,000 with most of the data taken at the higher value. The model pitch angle was varied from -3 degrees to +12 degrees and the yaw angle was varied from -20 degrees to +20 degrees. Nacelle inlet to freestream velocity ratios were varied from 0 to .7625, the maximum obtainable with freestream total pressure supplying the energy necessary to overcome internal losses.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0624814

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Air Flow
  • Aircrafts
  • Blade Tips
  • Blades
  • Dynamic Pressure
  • Flow
  • Geometry
  • Jet Aircraft
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Static Pressure
  • Strain Gages
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Energy Conservation and Renewable Energy Engineering.