Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20 Chord Flap

Abstract

Wind-tunnel tests were made through angle of attack range of -2 to +12 degrees at flap deflections from 0 to -12 degrees. Mach range was 0.28 to 0.74. Additional pressure-distribution measurements were made for positive (down) deflections of the flap at angles of attack of 2 and 4 degrees. Results show that effectiveness of the trailing edge type control surface rapidly decreases and approaches zero as the Mach number increases above critical value.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1946
Accession Number
ADA800619

Entities

People

  • W. F. Lindsey

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Air Flow
  • Boundary Layer
  • Coefficients
  • Compressive Properties
  • Control Surfaces
  • Dynamic Pressure
  • Flow
  • Mach Number
  • Measurement
  • Photographs
  • Pressure Distribution
  • Pressure Gradients
  • Static Pressure
  • Trailing Edges
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.