RESULTS OF WIND TUNNEL TESTS OF A FULL SCALE, FUSELAGE MOUNTED, TIP TURBINE DRIVEN LIFT FAN. VOLUME 3

Abstract

Results are reported of wind-tunnel model tests of a tip-turbine- driven lift fan (X353-5) mounted in the fuselage of a full-scale model. Longitudinal stability margin with fan operating was increased. STOL performance was essentially unchanged. Lift loss due to throttling the fan was very sensitive to height above ground. Pitching moments (longitudinal trim requirements) in ground effect decreased at low velocity ratios, but increased at high velocity ratios because of tail downwash increase. The fan flow decrease was accompanied by hub stall by a high static pressure ratio across the rotor. Modifications to test equipment and new instrumentation are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1962
Accession Number
AD0275711

Entities

People

  • Z. J. Przedpelski

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Air Temperature
  • Aircrafts
  • Aspect Ratio
  • Contracts
  • Measurement
  • Metal Matrix Composites
  • Military Research
  • Model Tests
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Three Dimensional
  • United States
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics.
  • Aerospace Engineering