ABSTRACT OF THE THESIS
Numerical Simulation of flow Past NACA 0012 Airfoil Using a Co-Flow Jet at Different Injection Angles to Control Lift and Drag
by
Da Xiao
Master of Science in Mechanical Engineering
Washington University in St. Louis, 2019
Research Advisor: Professor Ramesh K. Agarwal
The focus of this thesis is to numerically study the aerodynamic performance of an airfoil by employing the active flow control from a co-flow jet (CFJ) near the leading edge. The study is conducted by changing the injection angle of CFJ on a location close to the leading edge on the upper surface of a most widely used NACA 0012 airfoil. The compressible Reynolds-Averaged Navier-Stokes (RANS) equations with Spalart-Allmaras (SA) turbulence model are solved using the commercial CFD solver ANSYS FLUENT. Steady state solver is employed in the simulations with pseudo-transient numerical method. The study is performed at free stream angles of attack from 0° and 10° for momentum coefficients = 0.1, 0.2 and 0.3 with injection slot located at 5%, 15% and 25% chord length from the leading edge of the airfoil. It is shown that for given free stream conditions, the lift coefficient can be substantially increased and drag coefficient can be decreased with suitable choice of , injection angle and location of co-flow jet on the airfoil surface and different injection angles can have different aerodynamic coefficients performance. Thus, Changeable Injection Angle CFJ technology can be used for AFC to achieve the desired outcome of increasing the lift of an airfoil, decreasing drag of an airfoil and at the same time, to have a control of aerodynamic coefficients
