Create an airfoil in MATLAB

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James Hall-Prior
James Hall-Prior il 4 Nov 2022
%%%%% part 1
t = .18;
tau = .349;
e = .0721;
a = .574;
k = 1.889;
c = 2;
theta = [0:1:360];
r1 = sqrt(((a*cos(theta)-a).^2)+(a.^2)*sin(theta).^2)
r2 = sqrt(((a*cos(theta)-e*a).^2)+(a.^2)*sin(theta).^2)
theta1 = atand((a*sind(theta))./(a*cosd(theta)-a)) + pi
for theta2 = atand((a*sind(theta))./(a*cosd(theta)-e*a)) + n*pi
if theta2 <= 90
n = 0
elseif 90<theta2<=270
n = 1
elseif 270<theta2<360
n = 2
end
end
theta2 = atand((a*sind(theta))./(a*cosd(theta)-e*a)) + n*pi
x = ((r1.^k)/r2.^k-1).*(cos(k*theta1)*cos(k-1).*theta2+sin(k*theta1).*sin(k-1).*theta2)
z = ((r1.^k)/r2.^k-1).*(sin(k*theta1)*cos(k-1).*theta2-cos(k*theta1).*sin(k-1).*theta2)
plot(x,z)
(It should look like this but does not any help would be appreciated)
  3 Commenti
Sam Chak
Sam Chak il 4 Nov 2022
Do you have the 4-digit NACA code?
James Hall-Prior
James Hall-Prior il 4 Nov 2022
I don't and I'm not sure if I'm allowed to use it

Accedi per commentare.

Risposte (1)

Davide Masiello
Davide Masiello il 4 Nov 2022
From the wikipedia page
t = 0.25; % maximum thickness as a fraction of the chord
x0 = 0:0.001:1;
y0 = 5*t*(0.2969*sqrt(x0)-0.1260*x0-0.3516*x0.^2+0.2843*x0.^3-0.1015*x0.^4);
x = [x0,flip(x0)];
y = [y0,flip(-y0)];
plot(x,y)
axis equal

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