Date of Award
Master of Science (MS)
Aerospace Engineering Sciences
Kenneth E. Jansen
Airflow over a stabilizer-rudder assembly is simulated on an unstructured grid using a streamline upwind Petrov-Galerkin (SUPG) weighted residual finite element formulation of the incompressible Navier-Stokes equations. These studies seek to determine the effectiveness of synthetic jet flow control in increasing side force over the vertical tail. The two models under investigation are the Beta model, with 12 jets aligned along the span of the stabilizer, and a Beta model scaled up by a factor of 1.969, with 24 jets aligned along the span of the stabilizer. These two models have Reynolds numbers of 3.6*10^5 and 7.1*10^5, respectively, where both are based on the mean aerodynamic chord. The flow solver, Phasta, is used to run these simulations. URANS simulations on the Beta model with a 5 degree sideslip angle and 20 degree rudder deflection angle show that unsteady blowing with a blowing ratio of 1.0 increases the total side force coefficient by 14% with respect to the baseline. The Cp data obtained as a function of percent chord showed improvement in Cp from unsteady blowing in the outboard region, but negligible change in the inboard region. This data is in agreement with experimental values. Speed isosurface data was obtained for the Beta model with a 0 degree sideslip angle and 30 degree rudder deflection angle, with steady blowing. It was found that these isosurfaces create ridges and valleys along the span, suggesting interference between the jets. The same result was found for the scaled-up Beta model with a 0 degree sideslip angle and 30 degree rudder deflection angle, with steady blowing.
Martin, Jeffrey Louis, "Numerical Analysis of Synthetic Jet Flow Control on a Vertical Tail" (2013). Aerospace Engineering Sciences Graduate Theses & Dissertations. 63.