CIRCULATION CONTROL BY MEANS OF TRAILING EDGE SUCTION AND THE CUSP EFFECT

Abstract

A mathematical method is presented for predicting under limited conditions the performance of systems employing powered or automatically controlled flow singularities to produce a high lift without a corresponding change in attack angle. Wind-tunnel tests or systems utilizing suction at the trailing edge indicated that: (1) the lift increases with increasing suction quantities up to a limiting value without an increase in attack angle; (2) the limiting value is determined by the suction quantity required to remove the stagnation point from the upper surface to the trailing edge; and (3) the lift obtained with an unflapped profile utilizing edge suction is strongly affected by slot width and trailing edge overhang, but not by upper surface slot shape. A means was devised to create and stabilize a vortex at a desired location. An important feature of the flow is the powerful manner in which the vortex affects the downwash pattern to produce a large circulation about a profile.

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Document Details

Document Type
Technical Report
Publication Date
Jun 15, 1953
Accession Number
AD0016075

Entities

People

  • D. C. Hazen
  • F. O. Ringleb
  • R. F. Lehnert
  • T. E. Sweeney

Organizations

  • Princeton University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Boundary Layer Control
  • Complex Variables
  • Control Systems
  • Flow Fields
  • Free Stream
  • Geometry
  • High Lift
  • Measurement
  • Pressure Distribution
  • Stagnation Point
  • Suction Slots
  • Trailing Edges
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Control Systems Engineering.
  • Electrical Engineering