Hi,
JCran, this helps and makes sense.
I don't try to resolve the Navier thing. as yous said, i just need a common, united database from whitch i could get the data to include in my routines. a kind of CLift (airfoil, AoA).
not much, as you said, i believe i must not go into a comlex simulation but re-use existing data but Whitch data.
XFoil and JAVAFoil are great but i can't get them interfaced with my code yet.
Dave, thanks for the code, interesting, but very particular to the naca0012, if i understand it correctly. i asked the same on rotary and got an approx solution for a 3D wing , i think it is for a very approx aprox :
---------------------------------- from Gabriel Hugh Elkaim
- rotary
Cl = 2*pi*AR/(AR+2)*alpha
where alpha is the angle of attack from the zero lift line in RADIANS
AR is the aspect ratio (span/chord for a rectangular wing)
____________________________________
using the AR to calculatet hat is a kind of simple , how "un-acurate" can it be ?
for your understanding : i try to code a simulator that will compute the lift along a blade, with a transition between different airfoils and different twist values. Then i will compute the lift on the disk at different angles and airfoil combinations.
Since I'm not a math man, i slice the blade in N small elements to plot the lift/drag values.
QUESTIONS :
I was wondering if i can interlopate an average CLift betwen 2 airfoils CLifts at the same AoA.
How to consider the airflow on the 0 degree azimut (blade at the front), the blade being submitted to an angular speed + a frontal speed, the air flow passes through a distorted airfoil. could i introduce a kind of coefficient of distortion ? or can i consider the lift is the same.
Thanks for your quality help.
---------------------------------- from Geneweber - rotary
The Department of Aerospace Engineering at the University of Illinois has a large airfoil coordinate database.
http://www.aae.uiuc.edu/m-selig/ads.html I ran some of these through both JavaFoil
http://www.mh-aerotools.de/airfoils/javafoil.htm and Xfoil
http://raphael.mit.edu/xfoil/ and was able to generate lift and drag plots. It was interesting. Hope this helps.