Unsteady Airloads on a Sinusoidally Oscillating Supercritical Airfoil.

Abstract

The aim of the proposed investigation was to generate a set of theoretical and experimental unsteady aerodynamic data for an advanced type airfoil. This set of data should serve as a standard for the comparison and the evaluation of computational methods for two-dimensional unsteady transonic flow. For this purpose it was intended to complement the results of the wind tunnel tests conducted at NLR on the supercritical NLR 7301 airfoil with theoretical results. The statement of work of the intended investigation was: NLR provides the contour data of the 'shock free' NLR 7301 airfoil section, together with the hodograph solution for the design condition; and NLR provides the measured steady and unsteady pressure distributions in three characteristic flow conditions; subsonic flow, transonic flow with a well developed supercritical region terminated by a shock wave and the 'shock free' design condition. (sdw)

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1979
Accession Number
ADA214740

Entities

People

  • H. Tijdeman

Organizations

  • National Aerospace Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Autonomy
  • Space

DTIC Thesaurus Topics

  • Airfoils
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Fluid Dynamics
  • Fluid Flow
  • Frequency
  • Pressure Distribution
  • Shock Waves
  • Steady Flow
  • Subsonic Flow
  • Supercritical Airfoils
  • Test And Evaluation
  • Trailing Edges
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Instructional Design and Training Evaluation.