Two-dimensional computational fluid dynamics analysis of wings in ground effect and assessment on lift, drag and momentum coefficients resulting in a three-dimensional turbulence model of efficiency and instability

Ford, Elizabeth (2001) Two-dimensional computational fluid dynamics analysis of wings in ground effect and assessment on lift, drag and momentum coefficients resulting in a three-dimensional turbulence model of efficiency and instability. MSc(R) thesis, University of Glasgow.

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Abstract

The analysis of the following topic has been carried out using the following subdivisions, namely; History of Wings involving the Database, The CFD analysis-involving the Gambit and Fluent 5 program, and The Experimental tests. Database: A database of WIG craft was comprised, this allowed statistical analysis of WIG characteristics to be carried out. With the use of specific attributes of previous WIG designs a new design could then be comprised. CFD: Although difficult, it is vital to compare lift, drag and moment coefficients with both the angle of attack as well as h/c (the height to chord ratio). For this reason, as well as the increase in WISE craft over the years it is believed of great importance to analyze these characteristics using numerical simulation techniques based on CFD programs. It is hoped to describe all forces exerted on wing profiles while analyzing all stages of take-off. The aim of this section was to analyze two different types of airtfoil profiles using CFD. The NACA 0012 due to there being adequate information available on it, (it seemed logical to commence my CFD analysis on this profile) and the S-shaped profile, (which incorporates the Munk M6R2 over the upper portion and the CJ-5 over its tower portion). This was due to all new designs being based on this fairly new concept which has an increased effectiveness and has been proven to be of more use in surface effect vehicles. Details of the strategy behind the numerous input requirements of the Gambit program, such as the mesh generation process, the boundary conditions involved have been studied as well as the Fluent 5 program creation of solver input files and information on the running of solutions given prior to the solver outputs attained. Due to the involvement of five different angles of attack, namely 0, 2, 5, 7.5 and 10 degrees varying with five different h/c values, namely 1.5, 1, 0.75, 0.5 and 0.25, a positive or negative contribution to the aerodynamics involved around the airfoil could then be produced. Statistical analysis on the outcomes would then take place, resulting in effective results. Examples of the types of programs run are shown below, the LHS is NACA0012 over still water and the RHS for S-shaped over curved ground simulating waves. These are two cases from 150. This thesis is intended to enlighten and persuade the readers requiring various types of information enticed to the W.I.S.E. field, to subsequently interrogate such enigmas in more detail and hence, aid in the development and construction of future W.I.S.E. designs.

Item Type: Thesis (MSc(R))
Qualification Level: Masters
Additional Information: Adviser: R C McGregor
Keywords: Aerospace engineering, Fluid mechanics
Date of Award: 2001
Depositing User: Enlighten Team
Unique ID: glathesis:2001-73429
Copyright: Copyright of this thesis is held by the author.
Date Deposited: 14 Jun 2019 08:56
Last Modified: 14 Jun 2019 08:56
URI: http://theses.gla.ac.uk/id/eprint/73429

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