Numerical Investigation of Winglet Aerodynamics and Dimple Effect of NACA 0017 Airfoil for a Freight Aircraft
Abstract: Drag reduction is an ever-present challenge within the aeronautical engineering industry. This paper presents two substantial wing modifications: the addition of a winglet of a freighter aircraft and a dimpled wing on the NACA 0017 aerofoils. Studies on nine (9) different geometries of dimpled aerofoils were performed against a control model of an aerofoil without any dimple. Computational fluid dynamics (CFD) analysis was performed using two (2) commercial CFD platforms. This paper also explored two novel solutions of aircraft optimisation to mitigate the effects of drag and leading-edge pressure, while increasing the effect of lift. The optimised performance model of a freighter aircraft increased its aerodynamic efficiency. The study found that at take-off velocity of 82 m/s, winglets decreased pressure on the wing by 16.31%, through flow redirection and better flow integration into aerofoils wake. The study also analysed the separation layer and its effect through the appropriate use of the dimple effect. Increased lift effects were observed on a NACA 0017 aerofoil. Despite the low increase in drag of 6% from the modifications, the resultant L/D ratio was highly increased. This study also faced some challenges with validating the model. Hence some validation approaches were taken, and some other approaches suggested for future studies.
Author(s): Matthew Thomas Lewthwaite, Chiemela Victor Amaechi
Date Published: March 7, 2022
Depositing User: Jawad Ali
DOI: https://doi.org/10.3390/inventions7010031
Keywords: Dimple effect; NACA 0017 aerofoil; winglet aerodynamics; drag and lift coefficients; vortex induced vibration (VIV); computational fluid dynamics (CFD); freight aircraft; aerofoil
Pages: 1-30
Place of publication: Switzerland
Publication title: Inventions
Published URL: https://www.mdpi.com/2411-5134/7/1/31
Publisher: MDPI
Subject(s): Engineering
Type of publication: Journal