Matlab项目包含用于使用cst参数化方法生成翼型的源代码和Matlab示例

function [coord] = CST_airfoil(wl,wu,dz,N); % Description : Create a set of airfoil coordinates using CST parametrization method % Input : wl = CST weight of lower surface % wu = CST weight of upper surface % dz = trailing edge thickness % Output : coord = set of x-y coordinates of airfoil generated by CST % Create x coordinate x=ones(N+1,1);y=zeros(N+1,1);zeta=zeros(N+1,1); for i=1:N+1 zeta(i)=2*pi/N*(i-1); x(i)=0.5*(cos(zeta(i))+1); end % N1 and N2 parameters (N1 = 0.5 and N2 = 1 for airfoil shape) N1 = 0.5; N2 = 1; zerind = find(x(:,1) == 0); % Used to separate upper and lower surfaces xl= x(1:zerind-1); % Lower surface x-coordinates xu = x(zerind:end); % Upper surface x-coordinates [yl] = ClassShape(wl,xl,N1,N2,-dz); % Call ClassShape function to determine lower surface y-coordinates [yu] = ClassShape(wu,xu,N1,N2,dz); % Call ClassShape function to determine upper surface y-coordinates y = [yl;yu]; % Combine upper and lower y coordinates coord = [x y]; % Combine x and y into single output %% Function to calculate class and shape function function [y] = ClassShape(w,x,N1,N2,dz); % Class function; taking input of N1 and N2 for i = 1:size(x,1) C(i,1) = x(i)^N1*((1-x(i))^N2); end % Shape function; using Bernstein Polynomials n = size(w,2)-1; % Order of Bernstein polynomials for i = 1:n+1 K(i) = factorial(n)/(factorial(i-1)*(factorial((n)-(i-1)))); end for i = 1:size(x,1) S(i,1) = 0; for j = 1:n+1 S(i,1) = S(i,1) + w(j)*K(j)*x(i)^(j-1)*((1-x(i))^(n-(j-1))); end end % Calculate y output for i = 1:size(x,1) y(i,1) = C(i,1)*S(i,1) + x(i)*dz; end