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|Title:||Numerical calculations for flows past an unconventional airfoil|
|Doctoral Committee Chair(s):||Addy, A.L.|
|Department / Program:||Mechanical Science and Engineering|
|Discipline:||Mechanical Science and Engineering|
|Degree Granting Institution:||University of Illinois at Urbana-Champaign|
|Abstract:||A computer program has been developed for both two-dimensional compressible and incompressible turbulent flows around airfoils. Numerical solutions have been obtained by solving the steady-state Reynolds-averaged Navier-Stokes equations in primitive variable form. The standard k-$\varepsilon$ turbulence model was employed and a compression turbulence model was also discussed. Based on a non-staggered arrangement on a body-fitted grid system, the discretized transport equations were solved either by a hybrid or a second-order upwind differencing scheme. A multiple pressure correction procedure with implicit density treatment has been used. The solutions were obtained through an under-relaxed iterative process.
Various cases of flow past NACA 0012 and 4412 airfoils were examined first. The experimental data available included cases with freestream Mach numbers varying from 0 to 0.799, the chord Reynolds number up to 9 $\times$ 10$\sp6$, and the angle of attack ranging from 0$\sp\circ$ to 13.87$\sp\circ$. The results were good when compared with experimental data. Many cases of incompressible and compressible flows past an unconventional airfoil were then computed. The freestream Mach number varied from 0 to 0.9 with the chord Reynolds number of 3.9 $\times$ 10$\sp6$. The general behavior of the unconventional airfoil is presented.
|Rights Information:||Copyright 1990 Tsai, Ping-Ho|
|Date Available in IDEALS:||2011-05-07|
|Identifier in Online Catalog:||AAI9021770|
This item appears in the following Collection(s)
Graduate Dissertations and Theses at Illinois
Graduate Theses and Dissertations at Illinois
Dissertations and Theses - Mechanical Science and Engineering