Parametric Airfoil Design and Sensitivity Analysis for Turbulent Boundary-Layer Trailing-Edge Noise Reduction
Chen Liu, Seongkyu Lee
Abstract
This paper presents the investigation of airfoil turbulent boundary-layer trailing-edge noise reduction using a parametric airfoil design. The airfoil design tool performs a parametric design starting from a baseline airfoil and then morphing it with a number of design parameters, which include camber, camber crest position, thickness, thickness crest position, leading-edge radius, trailing-edge camber, and boat-tail angle. A predictive method that combines an empirical wall-pressure spectrum model and an acoustic diffraction model is used to predict airfoil turbulent boundary-layer trailing-edge noise. In this study, a NACA 0012 airfoil and a NACA 64-618 airfoil are used to analyze the effects of the design parameters on airfoil aerodynamic performance and trailing-edge noise. The sensitivity of different parameters is performed with Morris’s method in order to further assess their relative influences. Overall, it is found that thickness, trailing-edge camber, and boat-tail angle have a significant influence on noise levels.