NUMERICAL STUDY OF ACTIVE SHOCK WAVE-TURBULENT BOUNDARY LAYER INTERACTION CONTROL FOR TRANSONIC AERODYNAMICS

摘要

Transonic and high subsonic speeds are fromthe most critical aircrafts flight conditions dueto the fact that flying in these speeds causeslocal supersonic pockets on their lifting surfaceswhich end up with a shock wave. Shock waveappearance results in drag increment and hasthe potential to cause flow unsteadiness andbuffet. Shock wave control for large flightvehicles can reduce the fuel consumption and/oralternatively increases the flight range.Therefore, shock waves creation, theirinteraction with boundary layer and theircontrol have been the subject of the wide rangeof studies. Surface mass transfer using fluidsuction or injection is one of the active devicesfor the control of shock wave-boundary layerinteraction as a means of airfoil drag reductionor aerodynamic performance improvement. Aparametric study is carried out in order to gaininsight into the effects of mass transferparameters, i.e. the location, flow rate and theinclination angle on the aerodynamiccoefficients. The parametric study is done foroff-design transonic flow conditions containingstrong shock-boundary layer interaction aroundthe NACA64A010 airfoil and also to determinethe required information to commence anoptimization process. The flow is simulated bysolving the compressible Navier-Stokesequations in Reynolds averaged form togetherwith a two-equation turbulence model. A cellcenteredfinite-volume scheme is developed witha dual-time implicit time discretization. Resultsare presented for different mass transferparameters.