FLIGHT TEST EVALUATION OF A DISTRIBUTED SUCTION HIGH-LIFT BOUNDARY LAYER CONTROL SYSTEM ON A MODIFIED L-19 LIAISON AIRCRAFT

Abstract

A distributed suction high-lift boundary layer control system fitted to a standard liaison L-19 aircraft increased the aircraft CL max to 5.74 and decreased the take-off and landing distance over a 50-foot obstacle by 38 percent and 29 percent, respectively, with no increase in available power. The modified aircraft demonstrated acceptable stability, control, and handling characteristics in all flight phases, and the stalling characteristics were good, with no rolling tendency. Considerable structural modifications were necessary to obtain the above results. The small holes in the boundary layer control system operated quite successfully for a period of 5 years without clogging due to dust or rain.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0635953

Entities

People

  • David G. Clark
  • Michael R. Smith
  • Sean C. Roberts

Organizations

  • Mississippi State University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircraft Equipment
  • Aircraft Wings
  • Aircrafts
  • Airfoils
  • Airframes
  • Army Aviation
  • Boundary Layer
  • Boundary Layer Control
  • Control Systems
  • Fixed Wing Aircraft
  • Fluid Dynamics
  • High Angles
  • Horizontal Stabilizers
  • Measurement
  • Pressure Distribution
  • Short Takeoff Aircraft

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.
  • Robotics and Automation.