# Airfoil and Lift Coefficient Variation

**Topics:**Airfoil, Aerodynamics, MATLAB

**Pages:**2 (320 words)

**Published:**November 6, 2012

MAE466

2/8/12

HW#2

1) I think about 1000 radial stations are required for a converged calculation. 2) The first plot is of a rotor with linear twist showing the lift coefficient variation with rbar in hover. The second plot is the lift coefficient max along the radius which looks to be about 1.2.

The maximum thrust of the rotor in hover in terms of thrust coefficient is 0.0183.

Cpo = 2.5668e-004

Cpi = 0.0020

Cpt = 0.0022

Cpideal = 0.0017

Fig Mer = 0.7832

MATLAB CODE:

First Code:

This function integrates using the composite trapezoidal method of a function f(x) that is given in a set of n discrete points.

function I = IntPointsTrap(x,y)

n = length(x)-1

a = x(1)

b = x(n+1)

h = (b-a)/n

s = 0

for i = 2:n

s = y(i)+s;

end

I = h/2*(y(1)+y(n+1))+h*s

Second Code: s=sigma t=theta l=lambda a=alpha

B = 4;

rbar = .001:0.001:1;

s = .1; a = (2.*pi)./(sqrt(1 - .4.*(rbar.^2))); t0 = 0.3; t1 = -.17;

t = t0 + t1.*rbar;

li = -(1/2).*((s.*a)./(8))+(sqrt((((s.*a)./(16)).^2)+((s.*a.*rbar.*t)./(8))));

f = (B./2).*((1-rbar)./li)

F = (2./pi).*acos(exp(-f));

l = -(1/2).*((s.*a)./(8.*F))+(sqrt((((s.*a)./(16.*F)).^2)+((s.*a.*rbar.*t)./(8.*F))));

phi = l./rbar;

ab = theta - phi;

Cl = a.*ab;

plot(rbar, Cl)

dCt = (s./2).*Cl.*(rbar.^2)

y = dCt(1:999);

x = rbar(1:999);

I = IntPointsTrap(x,y);

Ct =I

Cd = .0091 - .078.*ab + 1.02.*(ab.^2);

dCp0 = Cd.*(rbar.^3);

y = dCp0(1:999);

I = IntPointsTrap(x,y);

Cpo = I.*s./2

Cpi = 1.13.*(Ct^1.5)./(sqrt(2))

Cpt = Cp_o+Cp_i

Cpideal = (Ct^1.5)./(sqrt(2))

FigMer = Cp_ideal/(Cp_total)

Please join StudyMode to read the full document