THE EFFECT OF THICKNESS ON PITCHING AIRFOILS AT SUPERSONIC SPEEDS

Abstract

A second-order theory was developed for 2 dimensional pitching airfoils at supersonic speeds. The development is based on considering airfoils with arbitrary symmetrical cross sections, but the analysis can be extended to airfoils with unsymmetrical cross sections. An expression for the lifting pressure caused by steady pitching is obtained which permits the stability derivatives to be calculated. The equation considered is similar to the equation of steady supersonic flow. The assumptions were that the second-order solution could be obtained by iteration and that the characteristics of the first- and second-order solutions are the same. The partial differential equation for airfoils with a steady pitching velocity was expressed in a time-independent form by conversion to a set of axes fixed to the airfoil. The first-order solution of this form of the equation was taken as the first approximation to the second-order equation. The second approximation was obtained by substituting this first-order solution into the second-order equation and solving the resulting non-homogeneous equation.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1953
Accession Number
AD0014217

Entities

People

  • John C. Martin
  • Nathan Gerber

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Boundaries
  • Cartesian Coordinates
  • Differential Equations
  • Discontinuities
  • Equations
  • Flow
  • Iterations
  • Leading Edges
  • Mach Number
  • Partial Differential Equations
  • Pressure Distribution
  • Supersonic Flow
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Calculus or Mathematical Analysis

Technology Areas

  • Hypersonics