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.

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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 
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