Effect of airfoil leading edge waviness on flow structures and noise

• Published in: International Journal of Numerical Methods for Heat & Fluid Flow
• Main Authors: Zhang, Man, Frendi, Abdelkader
• Format: Article in Journal/Newspaper
• Language: English
• Published: Emerald 2016
• Subjects: Humpback Whale
• Online Access: http://dx.doi.org/10.1108/hff-04-2015-0143; http://www.emeraldinsight.com/doi/full-xml/10.1108/HFF-04-2015-0143; https://www.emerald.com/insight/content/doi/10.1108/HFF-04-2015-0143/full/xml; https://www.emerald.com/insight/content/doi/10.1108/HFF-04-2015-0143/full/html

Purpose – The tubercles at the leading edge of Humpback Whale flippers have been shown to increase aerodynamic efficiency. The purpose of this paper is to compute the flow structures and noise signature of a NACA0012 airfoil with and without leading edge waviness, and located in the wake of a cylinder using the hybrid RANS-LES method. Design/methodology/approach – The mean flow Mach number is 0.2 and the angle of attack used is 2°. After benchmarking the method using existing experimental results, unsteady computations were then carried-out on both airfoil geometries and for a 2° angle of attack. Findings – Results from these computations confirmed the aerodynamic benefits of the leading edge waviness. Moreover, the wavy leading edge airfoil was found to be at least 4 dB quieter than its non-wavy counterpart. In-depth analysis of the computational results revealed that the wavy leading edge airfoil breaks up the large coherent structures which are then convected at higher speeds down the trough region of the waviness in agreement with previous experimental observations. This result is supported by both the two-point and space-time correlations of the wall pressure. Research limitations/implications – The limitations of the current findings reside in the fact that both the Reynolds number and the flow Mach number are low, therefore not applicable to aircrafts. In order to extend the study to practical aircrafts one needs huge grids and large computational resources. Practical implications – The results obtained here could have a huge implications on the design of future aircrafts and spacecrafts. More specifically, the biggest benefit from such redesign is the reduction of acoustic signature as well as increased efficiency in fuel consumption. Social implications – Reducing acoustic signature from aircrafts has been a major research thrust for NASA and Federal Aviation Administration. The social impact of such reduction would be improved quality of life in airport communities. For military aircrafts, this could ...