Aerodynamic Analysis on Winglets

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  • Topic: Aerodynamics, Wingtip vortices, Wingtip device
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  • Published : May 1, 2013
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BMEDME613 Aerodymamics
Assignment

Aerodynamic Analysis on Winglet

By: V.Devanandh, 114009037, B.Tech-Mechanical Engineering(III year), SASTRA University. Prof.Dhananjay, SASTRA University. Submitted to:

April 12, 2013

Contents
1 Introduction 2 Scope of the Assignment 3 Review of Basic concepts 3.1 3.2 Wingtip vortices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Induced drag . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3 3 3 4 5 6 7 8

4 Modeling and Analysis of NACA 2412 airfoil 4.1 4.2 Scenario 1: Airfoil without Winglet. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Scenario 2: Airfoil with winglet. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 Conclusion

1

List of Figures
1 2 3 4 5 6 7 Regions of upwash and downwash created by trailing vortices . . . . . . . . . . . . . . . . AOA Effect on induced drag . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NACA 2412 Airfoil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Airfoil without Winglet Flow Analysis - Top View . . . . . . . . . . . . . . . . . . . . . . Airfoil without Winglet Flow Analysis - Rear View . . . . . . . . . . . . . . . . . . . . . . Airfoil with Winglet Flow Analysis - Top View . . . . . . . . . . . . . . . . . . . . . . . . Airfoil with Winglet Flow Analysis - Rear View . . . . . . . . . . . . . . . . . . . . . . . . 4 5 5 6 7 7 8

2

1

Introduction

In commercial aircraft industry, fuel efficiency plays a major role in the current scenario wherein fuel resources are depleting rapidly. Induced drag is an important phenomenon in determining the fuel efficiency of an aircraft. The less induced drag is, the more fuel efficient the aircraft is. Winglet-an extension at the wing tip, also called as wingtip devices is one of the proven methods of reducing induced drag at wingtips. Winglets effectively reduce the wingtip vortices thereby reducing the drag. The initial theoretical concept goes back to times before even the Wright Brothers first took to the skies in 1905, but it was picked up and developed by Richard T. Whitcomb of NASA after the 1973 oil crisis-in order to reduce fuel consumption. The first tests were carried out in 1979/80 in cooperation with the U.S. Air Force. At almost the same time, but independent of any U.S. military organization, a private jet producer, LearJet exhibited a prototype in 1977: the LearJet 28 that featured the first winglets on a jet and a production aircraft. Flight tests made with and without winglets showed that the winglets increased range by about 6.5 percent and also improved directional stability for the LearJet- these two factors are the major reasons behind using this facility at any fixed wing aircraft ever since.

2

Scope of the Assignment

This assignment focuses on the turbulent dissipation study at the wing tip which is a direct interpretation of wingtip vortices and the associated induced drag. Introduction to wingtip vortex and induced drag has been discussed briefly. Later, a CFD Analysis Solidworks 2012TM has been performed on a NACA 2412 airfoil wing with and without winglet and the result has been critically analysed.

3
3.1

Review of Basic concepts
Wingtip vortices

A vortex is the rotational motion of a fluid medium, in this case air, generated as the high-pressure air from the bottom of the wing flows around the tip-side edge to the lower pressure region on top.While vortices known as bound vortices are created along the entire length of the wingspan, it is the trailing vortices behind the wingtips that are much stronger due to the three-dimensional effect of a finite wingspan. Such a phenomenon can create significant stability and efficiency issues for the entire aircraft. For high-lift, low-speed conditions as seen on runways, or for high subsonic cruising speeds, the drag induced from these vortices...
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