Effect of Various Parameters Including Mach Number on the Single-Degree-of-Freedom Flutter of a Control Surface in Potential Flow

Abstract

Various investigations of single-degree-of-freedom pitching oscillations of a wing in potential flow have been inade. However, corresponding studies of single-degree-of- freedom flutter of a control surface have not been made. The present paper demonstrates by theoretical calculations that single-degree-of-freedom control surface flutter is possible. The effects of structural damping, aerodynamic balance, axis of rotation, and compressibility are included. The mechanism of instability presented here is based on potential flow theory and the results of such a study are not directly applicable to separated flow; in addition, certain practical limitations are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1951
Accession Number
ADA380507

Entities

People

  • Harry L. Runyan

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Altitude
  • Aspect Ratio
  • Coefficients
  • Compressible Flow
  • Computational Fluid Dynamics
  • Control Surfaces
  • Equations
  • Flight Speeds
  • Flow
  • Frequency
  • Incompressible Flow
  • Leading Edges
  • Mach Number
  • Potential Flow
  • Supersonic Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Robotics and Automation.