Notes on the Theoretical Characteristics of Two-Dimensional Supersonic Airfoils

Abstract

The shock-expansion method of NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical supersonic airfoil was found to be ahead of the 0.50 chord.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1947
Accession Number
ADA801407

Entities

People

  • H. R. Ivey

Organizations

  • National Advisory Committee for Aeronautics

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Aircrafts
  • Airfoils
  • Camber
  • Deflection
  • Drag
  • Flow
  • Fluid Dynamics
  • Free Stream
  • Geometry
  • Mach Number
  • Pressure Distribution
  • Skin Friction
  • Supersonic Airfoils
  • Trailing Edges
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow