Experimental Investigation of Vortex Generators for Flow Separation Control on the Hinge Line of Leading-Edge Flap

2016 ◽  
Vol 64 (1) ◽  
pp. 35-40
Author(s):  
Zhong LEI ◽  
Keisuke TAKIZAWA ◽  
Dongyoun KWAK ◽  
Masayoshi NOGUCHI
Keyword(s):  
Experimental Investigation ◽  
Flow Separation ◽  
Leading Edge ◽  
Vortex Generators ◽  
Separation Control ◽  
Hinge Line ◽  
Flow Separation Control

scholarly journals Plasma Streamwise Vortex Generators for Flow Separation Control on Trucks

2018 ◽  
Vol 100 (4) ◽  
pp. 1101-1109 ◽  
Author(s):  
Julie A. Vernet ◽  
Ramis Örlü ◽  
David Söderblom ◽  
Per Elofsson ◽  
P. Henrik Alfredsson
Keyword(s):  
Flow Separation ◽  
Streamwise Vortex ◽  
Vortex Generators ◽  
Separation Control ◽  
Flow Separation Control

Design and Scaling of Plasma Streamwise Vortex Generators for Flow Separation Control

AIAA Journal ◽  
2016 ◽  
Vol 54 (11) ◽  
pp. 3397-3408 ◽  
Author(s):  
Christopher L. Kelley ◽  
Thomas C. Corke ◽  
Flint O. Thomas ◽  
Mehul Patel ◽  
Alan B. Cain
Keyword(s):  
Flow Separation ◽  
Streamwise Vortex ◽  
Vortex Generators ◽  
Separation Control ◽  
Flow Separation Control

Flow separation control of NACA-2412 airfoil with bio-inspired nose

2019 ◽  
Vol 91 (7) ◽  
pp. 1058-1066 ◽  
Author(s):  
Mohamed Arif Raj Mohamed ◽  
Ugur Guven ◽  
Rajesh Yadav
Keyword(s):  
Flow Control ◽  
Flow Separation ◽  
Control Method ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Separation Control ◽  
Cetacean Species ◽  
Aerodynamic Efficiency ◽  
Content Type ◽  
Flow Separation Control

Purpose The purpose of this paper is to achieve an optimum flow separation control over the airfoil using passive flow control method by introducing bio-inspired nose near the leading edge of the NACA 2412 airfoil. Design/methodology/approach Two distinguished methods have been implemented on the leading edge of the airfoil: forward facing step, which induces multiple accelerations at low angle of attack, and cavity/backward facing step, which creates recirculating region (axial vortices) at high angle of attack. Findings The porpoise airfoil (optimum bio-inspired nose airfoil) delays the flow separation and improves the aerodynamic efficiency by increasing the lift and decreasing the parasitic drag. The maximum increase in aerodynamic efficiency is 22.4 per cent, with an average increase of 8.6 per cent at all angles of attack. Research limitations/implications The computational analysis has been done for NACA 2412 airfoil at low subsonic speed. Practical implications This design improves the aerodynamic performance and increases structural strength of the aircraft wing compared to other conventional high-lift devices and flow-control devices. Originality/value Different bio-inspired nose designs which are inspired by the cetacean species have been analysed for NACA 2412 airfoil, and optimum nose design (porpoise airfoil) has been found.

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

2021 ◽  
Vol 93 (2) ◽  
pp. 251-266
Author(s):  
Mohamed Arif Raj Mohamed ◽  
Rajesh Yadav ◽  
Ugur Guven
Keyword(s):  
Flow Control ◽  
Flow Separation ◽  
Control Method ◽  
Leading Edge ◽  
Aircraft Design ◽  
Separation Control ◽  
Cetacean Species ◽  
Aerodynamic Efficiency ◽  
Content Type ◽  
Flow Separation Control

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.

Plasma-Actuator Burst-Mode Frequency Effects on Leading-Edge Flow-Separation Control at Reynolds Number 2.6×105

AIAA Journal ◽  
2017 ◽  
Vol 55 (11) ◽  
pp. 3789-3806 ◽  
Author(s):  
Hikaru Aono ◽  
Soshi Kawai ◽  
Taku Nonomura ◽  
Makoto Sato ◽  
Kozo Fujii ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Flow Separation ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Mode Frequency ◽  
Separation Control ◽  
Flow Separation Control ◽  
Frequency Effects ◽  
Burst Mode ◽  
Edge Flow
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