Accession Number:

AD1040848

Title:

Study on Trailing Edge Ramp of Supercritical Airfoil

Descriptive Note:

Conference Paper

Corporate Author:

RMIT University Melbourne Australia

Personal Author(s):

Report Date:

2016-03-30

Pagination or Media Count:

9.0

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 27 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 liftdrag ratio, and gain better buffet characteristic and some other benefits also.

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE