Assessment of aerodynamic behaviour of the NACA 64A212 airfoil on the context of computational fluid dynamics

Abstract

A comprehensive understanding of an aircraft�s fluid and flight dynamics cannot be understated from both an engineering and aircraft handling perspective. In this context, availability of such descriptive information, especially in the case of trainer aircraft, will deliver profitable results for both students and teachers. This research examines the behaviour of an aircraft having a wing tip designed with the NACA 64A212 airfoil. Detailed information regarding the aerodynamic behaviour of the wing has not been disclosed by the aircraft manufacturer to relevant stakeholders. Due to the complexity of flow physics involved during different regimes of the flight envelope, analytical fluid dynamic modelling does not render completely accurate results for the appraisal of the vehicle aerodynamic behaviour. The present work is involved with the assessment of aerodynamic behaviour of the NACA 64A212 airfoil through Computational Fluid Dynamics (CFD) methodology. The geometry of the airfoil is created using a solid modelling software and a commercial CFD tool models the flow physics involved. A generic lift curve and drag polar is developed to represent flows of reasonable Reynolds number that the vehicle would experience in actual flight. The results provide new insights into the behaviour of the airfoil, thus enabling means of enhancing handling qualities of the aircraft.