Pitching airfoil performance enhancement using co-flow jet flow control at high mach number

Alexis Lefebvre, GeCheng Zha

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Scopus citations

Abstract

Pitching airfoils with Co-Flow Jet (CFJ) flow control are simulated using Unsteady Reynolds Average Navier-Stokes (URANS) at Mach number 0.4 with reduced frequency of 0.1. The flow is transonic with shock wave boundary layer interaction. A 5th order WENO scheme for the inviscid flux, a 4th order central differencing model for the viscous terms and the one equation Spalart- Allmaras model for the turbulence are used to resolve the flow. The airfoil oscillate around its mean AoA of 10° with amplitude of 5°, 7.5° and 10°. The study demonstrates that the CFJ pitching airfoil is very effective to remove dynamic stall at high Mach number of 0.4. The performance is significantly enhanced with radically increased lift, reduced drag, and decreased moment variation.

Original languageEnglish (US)
Title of host publication52nd Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624102561
StatePublished - 2014
Event52nd Aerospace Sciences Meeting 2014 - National Harbor, United States
Duration: Jan 13 2014Jan 17 2014

Other

Other52nd Aerospace Sciences Meeting 2014
CountryUnited States
CityNational Harbor
Period1/13/141/17/14

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ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Lefebvre, A., & Zha, G. (2014). Pitching airfoil performance enhancement using co-flow jet flow control at high mach number. In 52nd Aerospace Sciences Meeting American Institute of Aeronautics and Astronautics Inc..