Four Prop Tilt Wing with Cyclic Pitch Propellers: Results of Full Span Wind Tunnel Test/Phase 2

Abstract

The report presents the results of wind tunnel test BVWT 067, the Phase II test of a two phase test program, performed in the Boeing-Vertol V/ STOL wind tunnel on a powered four prop tilt wing full span model equipped with cyclic pitch propellers for longitudinal control. Items evaluated through transitional flight, include cyclic pitch effectiveness, descent performance with cyclic pitch inputs, the effect of cyclic on longitudinal and lateral/ directional stability plus the influence of cyclic action on the effectiveness of the aircraft surface controls (stabilizer for longitudinal trim and differentially deflected flaps/spoiler for roll/yaw control). An in-ground effect investigation with a moving ground plane was also conducted to establish the influence of the ground on cyclic pitch effectiveness and on stability characteristics with cyclic pitch inputs.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1971
Accession Number
AD0734236

Entities

People

  • Charles E. Kolesar

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircrafts
  • Animal Structures
  • Control Surfaces
  • Data Acquisition
  • Dynamic Pressure
  • Geometry
  • Horizontal Stabilizers
  • Measurement
  • Propeller Blades
  • Propeller Hubs
  • Stabilization Systems
  • Test Facilities
  • Tilt Wing Aircraft
  • Tilt Wings
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering