Abstract

O-type body-fitted coordinate systems are numerically generated about NACA0012 and NACA4412 airfoils. These coordinate systems are used to effect a coordinate transformation from the physical plane to a rectangular transformed plane. The software developed also has a coordinate contraction capability. Plots of uncontracted and contracted coordinate systems are presented.

The nonconservative, velocity-pressure formulation of the two-dimensional, steady-state Euler equations are transformed to the rectangular plane. The boundary conditions at the airfoil are determined by the source-panel method, following which, the explicit finite difference form of the transformed Euler equations are solved using a space-marching scheme. Non-lifting potential flow solutions are obtained for the aforementioned airfoils at 0 and ±16 angles of attack. Pressure and velocity distribution plots are presented for all cases.

Library of Congress Subject Headings

Aerofoils--Aerodynamics; Aerofoils--Aerodynamics--Data processing; Aerodynamics--Data processing

Publication Date

1-1987

Document Type

Thesis

Student Type

Graduate

Degree Name

Mechanical Engineering (MS)

Department, Program, or Center

Mechanical Engineering (KGCOE)

Advisor

Amitabha Ghosh

Advisor/Committee Member

Hany Ghoneim

Advisor/Committee Member

P. Venkataraman

Comments

"I, Sivaraj Kailasapathy, require that I be contacted each time a request for reproduction is made."

Physical copy available from RIT's Wallace Library at TL574.A4 K343 1987

Campus

RIT – Main Campus

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