Date of Award

Spring 5-17-2019

Author's Department

Mechanical Engineering & Materials Science

Degree Name

Master of Science (MS)

Degree Type




Numerical Simulation of flow Past NACA 0012 Airfoil Using a Co-Flow Jet at Different Injection Angles to Control Lift and Drag


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.


English (en)


Ramesh K. Agarwal

Committee Members

David Peters Swami Karunamoorthy


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