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Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils

Mohamed Arif Raj Mohamed (Department of Aerospace Engineering, SRM Institute of Science and Technology, Kattankulathur, India)
Rajesh Yadav (Department of Aerospace Engineering, University of Petroleum and Energy Studies, Dehradun, India)
Ugur Guven (Department of Aerospace Engineering, University of Petroleum and Energy Studies, Dehradun, India)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 25 January 2021

Issue publication date: 5 April 2021

386

Abstract

Purpose

This paper aims to achieve an optimum flow separation control over the airfoil using a passive flow control method by introducing a bio-inspired nose near the leading edge of the National Advisory Committee for Aeronautics (NACA) 4 and 6 series airfoil. In addition, to find the optimised leading edge nose design for NACA 4 and 6 series airfoils for flow separation control.

Design/methodology/approach

Different bio-inspired noses that are inspired by the cetacean species have been analysed for different NACA 4 and 6 series airfoils. Bio-inspired nose with different nose length, nose depth and nose circle diameter have been analysed on airfoils with different thicknesses, camber and camber locations to understand the aerodynamic flow properties such as vortex formation, flow separation, aerodynamic efficiency and moment.

Findings

The porpoise nose design that has a leading edge with depth = 2.25% of chord, length = 0.75% of chord and nose diameter = 2% of chord, delays the flow separation and improves the aerodynamic efficiency. Average increments of 5.5% to 6° in the lift values and decrements in parasitic drag (without affecting the pitching moment) for all the NACA 4 and 6 series airfoils were observed irrespective of airfoil geometry such as different thicknesses, camber and camber location.

Research limitations/implications

The two-dimensional computational analysis is done for different NACA 4 and 6 series airfoils at low subsonic speed.

Practical implications

This design improves aerodynamic performance and increases the structural strength of the aircraft wing compared to other conventional high lift devices and flow control devices. This universal leading edge flow control device can be adapted to aircraft wings incorporated with any NACA 4 and 6 series airfoil.

Social implications

The results would be of significant interest in the fields of aircraft design and wind turbine design, lowering the cost of energy and air travel for social benefits.

Originality/value

Different bio-inspired nose designs that are inspired by the cetacean species have been analysed for NACA 4 and 6 series airfoils and universal optimum nose design (porpoise airfoil) is found for NACA 4 and 6 series airfoils.

Keywords

Citation

Raj Mohamed, M.A., Yadav, R. and Guven, U. (2021), "Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils", Aircraft Engineering and Aerospace Technology, Vol. 93 No. 2, pp. 251-266. https://doi.org/10.1108/AEAT-08-2019-0170

Publisher

:

Emerald Publishing Limited

Copyright © 2020, Emerald Publishing Limited

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