Four Prop Tilt Wing with Leading Edge BLC: Results of Semi-Span Wind Tunnel Test

Abstract

The report presents the results of wind tunnel test BVWT 055 performed in the Boeing Vertol V/STOL wind tunnel on a powered four prop tilt wing semi-span model. The purpose of the test was to establish the effect of leading edge boundary layer control (BLC) coupled with cyclic pitch on the descent capability of the aircraft. Configuration changes including 'both-down- between-nacelles' and 'both-down-inboard' propeller rotations, double slotted flaps and single slotted flaps, full span leading edge slats on and off, and all but the inboard wing fence removed were investigated during this test.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1970
Accession Number
AD0734233

Entities

People

  • Charles E. Kolesar
  • George Kassianides
  • Joyce Andrews

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Sensors

DTIC Thesaurus Topics

  • Acquisition
  • Aerodynamic Configurations
  • Aircrafts
  • Boundaries
  • Boundary Layer
  • Boundary Layer Control
  • Dynamic Pressure
  • Geometry
  • Instrumentation
  • Layers
  • Leading Edges
  • Test Equipment
  • Test Facilities
  • Tilt Wing Aircraft
  • Tilt Wings
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering