Passer d'un code matlab à un code VBA

[regatier25]

Bonjour à tous,

Dans le cadre d'un projet de calcul aéronautique, j'ai réussi à obtenir un code matlab. Cependant, mon but est de réussir à le transposer sous excel afin que les différents utilisateurs puissent saisir certaines informations, et qu'à la fin j'obtienne les résultats que je souhaite. Voici le code matlab et merci d'avance pour votre aide


croot=input('Please input root chord ');
ctip=input('Please input tip chord ');
span=input('Please input span ');
thetaroot=input('Please input Root twist angle in degrees ');
thetatip=input('Please input tip twist angle in degrees ');
a0root=input('Please input root lift curve slope in units/ radian ');
a0tip=input('Please input lift curve slope at the tip, in units/radian ');
alpha=input('Please input angle of attack, in degrees ');
alpha0root=input('Please input zero-lift angle at the root ');
alpha0tip=input('Please input zero lift angle at the tip ');
thetaroot=thetaroot * atan(1.)/45.;
thetatip=thetatip * atan(1.)/45.;
alpha = alpha * atan(1.)/45.;
alpha0root=alpha0root * atan(1.)/45.;
alpha0tip=alpha0tip * atan(1.)/45.;
n = 10;
theta=zeros(1,n);
y=zeros(1,n);
c=zeros(1,n);
cl=zeros(1,n);
alp=zeros(1,n);
a=zeros(1,n);
rhs=zeros(n,1);
b=zeros(n,n);
a=zeros(n,1);
%
% Define properties at n span stations
%
pi = 4. * atan(1.);
for i=1:n
theta(i) = (i) * pi/(2. * n);
y(i) = span * 0.5 * cos(theta(i));
c(i) = croot+(ctip-croot)*y(i)*2./span;
alp(i) = alpha+thetaroot-(alpha0root+(alpha0tip-alpha0root+thetaroot-thetatip)*y(i)*2./span);
a(i) = a0root+(a0tip-a0root)*y(i)*2./span;
end
pi = 4. * atan(1.);
% Set up 2n x 2n system of equations for A1, A3 , ... A2n-1
for j=1:n
mu = c(j)* a(j) / (4. * span)
rhs(j,1)=alp(j)*sin(theta(j))*c(j)*a(j)/(4*span);
for i=1:n
l = 2 * i-1;
b(j,i)=sin(l*theta(j))*(mu*l+sin(theta(j)));
end
end
%
% Solve for the Fourier Coefficients
%
a=b\rhs
% Compute wing area and aspect ratio
S=(croot+ctip)/2.*span;
AR=span*span/S;
% Compute CL
CL=a(1)*pi*AR
% Compute CD
CD0=1.;
for i=2:n
CD0=CD0+(2.*i-1)*a(i)*a(i)/(a(1)*a(1));
end
CD = pi * AR * a(1) * a(1) * CD0
% Compute spanwise load distribution, normalized by Freestream velocity times Span
gamma=zeros(1,n);
for i=1:n
gamma(i)=0.0;
y(i)=y(i)*2./span;
for j=1:n
gamma(i)=gamma(i)+2.*a(j)*sin((2*j-1)*theta(i));
end
gamma(i) = gamma(i) * span;
cl(i) = gamma(i)/(0.5*c(i));
end
cl
%
% Plot the circulation distribution from root to tip with labels
%
plot(y,cl);
xlabel('y/Semi-Span');
ylabel('Cl');
title('Sectional Lift Coefficient distribution');