Transonic Wind Tunnel Tests on a Series of Two-Dimensional Aerofoils in a Solid Wall Test Section,

Abstract

Transonic wind tunnel tests are reported on a series of two-dimensional models in a test section equipped with four solid walls. The tests were conducted on two geometrically similar models of each of two aerofoil sections -- NACA-0012 and BGK-1 -- and covered a range of Mach numbers between 0.5 and 0.82. The main purpose of the tests was to provide a body of data suitable for testing the validity of linear interference theory without the complication of the unknown boundary conditions associated with non-solid wind tunnel walls. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1979
Accession Number
ADA076131

Entities

People

  • B. D. Fairlie
  • N. Pollock

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Airfoils
  • Boundary Layer
  • Corporations
  • Fluid Dynamics
  • Fluid Mechanics
  • Mach Number
  • Mechanics
  • Military Aircraft
  • Physics Laboratories
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Silicon Carbide
  • Two Dimensional
  • United States
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Test and Evaluation
  • Computational Fluid Dynamics (CFD)