C4 airfoil data
Does someone know the C4 airfoil data or the eqautions to calculate its coordinates? thanks !
dragon 
Re: C4 airfoil data
I've found RC(4) airfoil on this page: http://www.nasg.com/afdb/showairfoile.phtml?id=996 Click on contour link and y'll find cordinates.

Re: C4 airfoil data
thanks,dear Bounecer.
But I guess RC(4) is not the one I want. I read in the paper that the airfoil's name is C4. I dont know if it is NACA,but I guess not. This is the paper I read: "NonNewtonian Flow over the trailing edge of an airfoil" Journal name:Experimental thermal and fluid science 1996;12:244249 there is a picture of C4, but it does not look like RC(4). thanks again. dragon 
Re: C4 airfoil data
I'm studing a 2D, incompressible, laminar, viscous flow about airfoil. I've used "structured C grid generation", with finite volumes method and second order upwind numerical scheem and SIMPLER algorithm. After great time and efforts, my code program diverge after i reach a precision of 10e3.
In my work i'am using only NACA airfoil, but if i found what you look for, i'll contact you. Good chance friend 
HN273airfoil data
please send all information about airfoil HN273. thank you.

Please click one of the Quick Reply icons in the posts above to activate Quick Reply.

matlab code
Here is the code to generate C4 thickness distribution and cambered airfoil
clc clear all t = 0.1;%thickness, t and x are in % of chord length theta = 18.5*pi/180; %camber angle/2 mu = pi/6;%it is actually dy_c/dx, for simplicity i used it equal to 30 degrees. x = 0:0.02:1; y = (t/0.2)*(0.3048*x.^0.50.0914*x0.8614*x.^2+2.1236*x.^32.9163*x.^4+1.9744*x.^50.5231*x.^6);%equation for symmetric airfoil C4 y_c = sqrt(((0.5/sin(theta/2)).^2(x0.5).^2))0.5/tan(theta/2);%equation of camber line %for upper s/f wrapped coordinates around camber line y_c x_u = transpose(115*(xy*sin(mu))); y_u = transpose(115*(y_c+y*cos(mu))); %for lower s/f wrapped coordinates around camber line y_c x_L = transpose(115*(xy*cos(mu))); y_L = transpose(115*(y_cy*sin(mu))); plot(x_u,y_u,x_L,y_L); ylim([20 50]); regards, Ammofreak 
All times are GMT 4. The time now is 18:08. 