The input thinair.data:

51	=ix mesh system <102
1.8	=omega relaxation factor
0.086	=dm camber ratio                                              
0.12	=em thickness ratio                                           
3	=ithick (1/2/3/4/5) ellip/semi-cubic/q-j/naca00xx/selig 
0.	=alphd angle of incidence (deg.)
+ other data not useful for this project.                              


ix is the number of discretization points along the camber line. 
You can see that the plots (e.g. circulation distribution) will be less accurate, if you decrease the value for ix. 
You can play with it, but it's not required for the project.

The omega relaxation factor is a numerical parameter you learned about in Eng 180 or the equivalent numerics class, and can
range from 1 to less than 2. For this lab, do not change it from 1.8.

ithick should be set to '3' for cases (a)-(d). 
This is important in order to compare your obtained results with those of the Q-J airfoils in Project 1.

dm, em and alphd you know the meaning from Project 1.



Running the code ...


itx is the number of iterations, keep running until the number to the right 'dgx'stops decreasing.  
you may want to record the number of iterations it took.
To stop iterating enter '0' it then outputs Cl and Cm,o. 

Enter 0 for the Reynolds number as we are not making any boundary layer corrections. 



The output:

thinair.xcp  This is the upper and lower surface Cp distribution, small disturbance and "regularized". You should now be able to tell which is which.

thinair.xgp , thinair.xg these are the vorticity distribution and partial circulation. 

thinair.xz this is the profile shape and it is easy to see which is upper and lower surface if you plot them. 

thinair.xu , has thin airfoil theory and "regularized" u velocities for the upper and lower surface.
thinair.xo , has 		' '                    w velocities ....