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
Mechanical Engineering (MS)
Department, Program, or Center
Mechanical Engineering (KGCOE)
Kailasapathy, Sivaraj, "Investigation of steady incompressible flows in the vicinity of an airfoil" (1987). Thesis. Rochester Institute of Technology. Accessed from
RIT – Main Campus