Sonic Boom Minimization of Airfoils through Computational Fluid Dynamics and Computational Acoustics

This project analyzes 2-D, inviscid, steady supersonic flow over different airfoil designs at Mach 2.2 while at 60,000ft. The airfoils tested have sharp leading and trailing edges. The shapes range from diamond to convex to a combination of the two. A hybridization of Computational Fluid Dynamics (CFD) and Computational Acoustic simulations are used to obtain values for the lift coefficient, drag coefficient, and maximum overpressure. The trends obtained from this very specialized case show that flat bottomed airfoils generate the smallest overpressures, and the highest lift to drag ratios. The reason for this is that the thinner shapes create smaller disturbances in the flow and thus generate smaller shock waves, which in turn reduce the drag, and the overpressure. This study does not take into consideration structural issues, viscosity, differing angles of attack, or 3-D effects. * Undergraduate Student, Aerospace and Ocean Engineering, 125 Lee Hall, [email protected] † Associate Professor, Aerospace and Ocean Engineering, 330 Randolph Hall, [email protected] Nomenclature L = chord length x = axial coordinate yu = maximum distance from the centerline to the upper surface of the airfoil with respect to L yl = maximum distance from the centerline to the lower surface of the airfoil xu = location of yu from the leading edge xl = location of yl from the leading edge δ = shape function of the airfoil P = free stream pressure δP = over pressure M = Mach number T = temperature