Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing

The competitiveness of high-performance wing with improved stalling characteristics gains more popularity in recent decades. The primary factor dominating the lack in aerodynamic performance is drag formation. Rough surface aerodynamics is one of the promising alternative method which involves pa...

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Main Author:	Gracia, Samuel Merryisha Sweety
Format:	Thesis
Language:	English
Published:	2020
Subjects:	T Technology
Online Access:	http://eprints.usm.my/47765/1/Drag%20Reduction%20On%20Naca%202412%20Using%20Dimpled%20Airfoil%20And%20Grooved%20Wing.pdf
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spelling	my-usm-ep.477652021-11-17T03:42:09Z Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing 2020-06-01 Gracia, Samuel Merryisha Sweety T Technology The competitiveness of high-performance wing with improved stalling characteristics gains more popularity in recent decades. The primary factor dominating the lack in aerodynamic performance is drag formation. Rough surface aerodynamics is one of the promising alternative method which involves passive control technique to degrade drag and improve lift to drag ratio. In current study, the interaction of dimple and groove parameters influencing the aerodynamic performance of airfoil and wing at a different angle of attack operating at 30 m/s and Reynolds number of 4.4x105 are considered. The present study divides into two, Study (1) explores the aerodynamic performance and behaviour of five different indented and protruded dimples located at 1) 0.3C, 2) 0.5C, 3) 0.7C, 4) multiple dimples on suction side alone and 5) multiple dimples indenting throughout airfoil (i.e. both pressure and suction side) over 2D airfoil. Study (2) deals with grooves indented over the wingspan at different x/c location 1) near leading edge (0.2C), 2) near trailing edge (0.8C), 3) mid-span (0.5C), 4) triplet location (0.2C, 0.5C, 0.8C). Altering the surface of airfoil/wing boosts its efficiency, thereby thickens the reattached flow; hence the flow is kept attached even at higher AOA. The models are designed using CATIA V5R20 and ANSYS Fluent helps to simulate the flow behaviour, and aerodynamic performance difference between models. The results of study (1) show introducing dimples over airfoil keep flow attached beyond 0.25C even at 16o AOA with (l/d)max of 39.5% enhancement. The results of the study (2) show that the presence of grooves enhances the stalling characteristics by keeping the flow attached up to 18o AOA. In all the grooved wing model, the L/D shows at least 0.05% improvement compared to baseline wing. However, the aerodynamic characteristics show the pronounced result on SRD(I) 0.5, SOD(P) 0.3, SSRD(I), SSSD(I) and SSSD(P) models in the case of dimple airfoil study and triplet groove wing in the case of groove wing study. The analyses of the dimpled airfoil and groove wing with different configurations showcased the sensitivity of flow over rough airfoil on pressure and suction side. 2020-06 Thesis http://eprints.usm.my/47765/ http://eprints.usm.my/47765/1/Drag%20Reduction%20On%20Naca%202412%20Using%20Dimpled%20Airfoil%20And%20Grooved%20Wing.pdf application/pdf en public masters Universiti Sains Malaysia Pusat Pengajian Kejuruteraan Aeroangkasa
institution	Universiti Sains Malaysia
collection	USM Institutional Repository
language	English
topic	T Technology
spellingShingle	T Technology Gracia, Samuel Merryisha Sweety Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing
description	The competitiveness of high-performance wing with improved stalling characteristics gains more popularity in recent decades. The primary factor dominating the lack in aerodynamic performance is drag formation. Rough surface aerodynamics is one of the promising alternative method which involves passive control technique to degrade drag and improve lift to drag ratio. In current study, the interaction of dimple and groove parameters influencing the aerodynamic performance of airfoil and wing at a different angle of attack operating at 30 m/s and Reynolds number of 4.4x105 are considered. The present study divides into two, Study (1) explores the aerodynamic performance and behaviour of five different indented and protruded dimples located at 1) 0.3C, 2) 0.5C, 3) 0.7C, 4) multiple dimples on suction side alone and 5) multiple dimples indenting throughout airfoil (i.e. both pressure and suction side) over 2D airfoil. Study (2) deals with grooves indented over the wingspan at different x/c location 1) near leading edge (0.2C), 2) near trailing edge (0.8C), 3) mid-span (0.5C), 4) triplet location (0.2C, 0.5C, 0.8C). Altering the surface of airfoil/wing boosts its efficiency, thereby thickens the reattached flow; hence the flow is kept attached even at higher AOA. The models are designed using CATIA V5R20 and ANSYS Fluent helps to simulate the flow behaviour, and aerodynamic performance difference between models. The results of study (1) show introducing dimples over airfoil keep flow attached beyond 0.25C even at 16o AOA with (l/d)max of 39.5% enhancement. The results of the study (2) show that the presence of grooves enhances the stalling characteristics by keeping the flow attached up to 18o AOA. In all the grooved wing model, the L/D shows at least 0.05% improvement compared to baseline wing. However, the aerodynamic characteristics show the pronounced result on SRD(I) 0.5, SOD(P) 0.3, SSRD(I), SSSD(I) and SSSD(P) models in the case of dimple airfoil study and triplet groove wing in the case of groove wing study. The analyses of the dimpled airfoil and groove wing with different configurations showcased the sensitivity of flow over rough airfoil on pressure and suction side.
format	Thesis
qualification_level	Master's degree
author	Gracia, Samuel Merryisha Sweety
author_facet	Gracia, Samuel Merryisha Sweety
author_sort	Gracia, Samuel Merryisha Sweety
title	Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing
title_short	Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing
title_full	Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing
title_fullStr	Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing
title_full_unstemmed	Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing
title_sort	drag reduction on naca 2412 using dimpled airfoil and grooved wing
granting_institution	Universiti Sains Malaysia
granting_department	Pusat Pengajian Kejuruteraan Aeroangkasa
publishDate	2020
url	http://eprints.usm.my/47765/1/Drag%20Reduction%20On%20Naca%202412%20Using%20Dimpled%20Airfoil%20And%20Grooved%20Wing.pdf
_version_	1747821827298689024

Drag Reduction On Naca 2412 Using Dimpled Airfoil And Grooved Wing

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