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) : LI,Runze ; ZHANG,Yufei ; CHEN,Haixin


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/1040848.pdf


Report Date : 30 Mar 2016


Pagination or Media Count : 9


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.


Descriptors :   trailing edges , computational fluid dynamics , SUPERCRITICAL AIRFOILS , ramps , Flow separation


Subject Categories : Aircraft
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE