A PRELIMINARY INVESTIGATION TO STUDY THE EFFECT OF FLAT SPOILERS ON THE AERODYNAMIC CHARACTERISTICS OF WINGS AT ANGLES OF ATTACK FROM 0 DEGREES TO 90 DEGREES.

Abstract

Flat spoilers were tested on a semispan wing as a possible leading-edge, upper-surface device for controlling flow separation on wings rotated through 90 degrees for application to tilt-wing V/STOL aircraft. Model tests indicated that a spoiler height of 0.10 wing chord at the 0.15 wing chord location was capable of partially controlling flow separation. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1966
Accession Number
AD0636750

Entities

People

  • Gary W. Brasseur

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airframes
  • Flow
  • Flow Separation
  • Leading Edges
  • Model Tests
  • Short Takeoff Aircraft
  • Tilt Wing Aircraft
  • Tilt Wings
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.