The Effect of Compressibility on Two-Dimensional Tunnel-Wall Interference for a Symmetrical Airfoil

Abstract

The effective change of flow past a wing section, due to presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. For a symmetrical section at a zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M(2) to take account of compressibility effects.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1943
Accession Number
ADB815629

Entities

People

  • G. E. Nitzberg

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Buildings And Structures
  • Compressible Flow
  • Compressive Properties
  • Differential Equations
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Incompressible Flow
  • Mach Number
  • Potential Flow
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.