Numerical Study of the Influence of Leading and Trailing Edge Flaps on the Performance of Airfoils

Abstract

The purpose of this study is to develop a code based on the Approximate Navier Stokes (ANS) equations (in the Vorticity Stream Function delta form). The Wortman FX 63-137 airfoil fitted with leading and trailing edge devices has been analyzed at low Reynolds Number (100,000) at various angles of attack and various deflection angles. Results are compared to the experimental data. The agreement is very good at small angles of attack. However, at large angles of attack the disparity is larger, and improvements have been recommended which will resolve this disparity. Overall the present scheme produces very reasonable results, with good repeatability and fast convergence, and has the potential of being developed into an effective design tool. Theses.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1989
Accession Number
ADA206138

Entities

People

  • Faran Hafeez

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Engineering
  • Equations
  • Experimental Data
  • Flow Visualization
  • Fluid Dynamics
  • Geometry
  • Mathematical Models
  • Pressure Distribution
  • Remotely Piloted Vehicles
  • Reynolds Number
  • Steady State
  • Turbulent Mixing
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Systems Analysis and Design