Study on Trailing Edge Ramp of Supercritical Airfoil

Abstract

Trailing edge flow control method could improve the performance of supercritical airfoil with a small modification on the original airfoil. In this paper, a ramp of 2%~7% chord length is sliced near the trailing edge to improve airfoil performance. The trailing edge ramp is adopted to create a sharp pressure recovery without flow separation. Reynolds averaged Navier-Stokes method is used to numerically study the effects of the ramp, and to investigate the influence of the ramp length and height. Results show that the ramp could increase the circulation of the airfoil and improve lift/drag ratio, and gain better buffet characteristic and some other benefits also.

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Document Details

Document Type
Technical Report
Publication Date
Mar 30, 2016
Accession Number
AD1040848

Entities

People

  • Haixin Chen
  • Runze Li
  • Yufei Zhang

Organizations

  • RMIT University

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aircrafts
  • Airfoils
  • Applied Mathematics
  • Coefficients
  • Computational Fluid Dynamics
  • Flow
  • Flow Separation
  • Fluid Dynamics
  • Fluid Flow
  • Hypervelocity Flow
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Shock Waves
  • Supercritical Airfoils
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design