Further Studies on the 21% Thick, Supercritical NLF Airfoil NAE (National Aeronautical Establishment) 68-060-21:1.

Abstract

Further wind tunnel tests have been carried out on the NAE 10 in. chord supercritical NLF airfoil NAE 68-060-21:1. In previous tests, this airfoil showed very low drag levels when free transition was allowed on the model. In the main part of about 7,9 and 13 million, transition was fixed at 7% and 15% on upper and lower surfaces respectively. It is observed that there is a substantial loss of lift under these conditions which appears to be associated with boundary layer thickening on the lower surface causing decambering near the trailing edge. Additional tests were also carried out under free transition at other Reynolds numbers than those previously used. The same drag bucket behaviour near the design flow conditions was observed. Keywords: Supersonic airfoils; Aerodynamic drag.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1986
Accession Number
ADA175923

Entities

People

  • D. J. Jones
  • Muhammad Khalid

Organizations

  • National Research Council Canada

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Drag
  • Flow
  • Free Stream
  • Laminar Flow
  • Layers
  • Low Drag
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Trailing Edges
  • Transitions
  • Turbulent Boundary Layer
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Materials Science and Engineering.
  • Small Business Innovation Research Program (SBIR) EDI Research and Innovation.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow