Some Conical and Quasi-Conical Flows in Linearized Supersonic-Wing Theory

Abstract

A number of conical and quasi-conical linearized supersonic flows have been derived These flows may be applied in. lift- cancellation techniques in the determination of wing-lift disturbances that arise at subsonic trailing edges Some of the results are applied to damping in roll and pitch in another paper. Two methods of analysis have been employed, both involving integral equations. One is a development of the membrane method of Evvard; the other is an analog of the superposition method of Schlichting. In both cases, source distributions are used. The mathematical equivalence of the first method and a new doublet- distribution method of Goodman and Mirels is shown.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1950
Accession Number
ADA380461

Entities

People

  • Herbert S. Ribner

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Cyber
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Agreements
  • Boundaries
  • Cancellation
  • Cartesian Coordinates
  • Delta Wings
  • Equations
  • Flow
  • Free Stream
  • Integral Equations
  • Integrals
  • Load Distribution
  • Mach Number
  • Specifications
  • Supersonic Flow
  • Sweptback Wings
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics