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Basically, this is a study to see if the 1933 wind tunnel
measurements of airfoils for coefficient of lift CL and
coefficient of drag CD can be reproduced by computer
simulation.
Airfoil 0015
Testing formulas for 0015 airfoil
rotate_prime.java
Create data file for airfoil at a specific angle and grid:
w0015grid.java
Build a PDE analysis grid around the airfoil:
w0015vert.java
w0015grid_java.out
w0015a22.grid
w0015vert_java.out
w0015b22_grid_java.out
w0015b22.grid
w0015b22_vert_java.out
w0015c22_grid_java.out
w0015c22.grid
w0015c22_vert_java.out
w0015b00.grid
w0015b00_vert_java.out
References:
NACA-460 1933 78 airfoils
NACA-824 1945 Airfoil Summary
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