calculate.m

本程序的开发环境为MATLAB6.5版本

%   Calculate 

%   LiuXiangChun
%   The college of astronautics NWPU
%   Date:2007-06-07

disp('Calculating ...')

[m,n] = size(alpha);            %取迎角数组alpha的大小
N_alpha = max(m,n);             %确定循环次数N_alpha
[m,n] = size(MachNumber);       %取马赫数数组alpha的大小
N_MachNumber = max(m,n);        %确定循环次数N_MackNumber

for i=1:N_alpha;
    a=alpha(1,i);
    for j=1:N_MachNumber
        
        M=MachNumber(1,j);
        if M>1
            Xd_T=1/2*br_T;
        else
            Xd_T=1/4*br_T;
        end
        
        Re      = M*Sonic_0*b_A/v_0;             %雷诺数   Re_b=V*b_A/v； v为运动粘性系数 page259 
        Re_T    = M*Sonic_0*b_A_T/v_0;           %雷诺数   Re_b=V*b_A/v； v为运动粘性系数 page259 
        Re_b    = M*Sonic_0*Lb/v_0;              %以弹体长度来计算，Re_b=V*L_b/v；           

        sim('Aerodynamic.mdl');                  %运行Simulink程序Aerodnamic
                                                 %保存运算结果
        Result_Cy(i,j)=Cy(1,1);
        Result_Cx(i,j)=Cx(1,1);
        Result_Xd(i,j)=Xd(1,1);
        
        Result_Cy_body(i,j)=Cy_body(1,1);
        Result_Cy_wing(i,j)=Cy_wing(1,1);
        
        Result_Cx0_body(i,j)=Cx0_body(1,1);
        Result_Cx0_wing(i,j)=Cx0_wing(1,1);
        Result_Cx0_tail(i,j)=Cx0_tail(1,1);
        Result_Cx0(i,j)=Cx0(1,1);
        Result_Cxi(i,j)=Cxi(1,1);
        
        Result_Cxm(i,j)=Cxm(1,1);
        Result_Cxn(i,j)=Cxn(1,1);
        Result_Cxt(i,j)=Cxt(1,1);
        Result_Cxb(i,j)=Cxb(1,1);
        
        Result_Xd_B(i,j)=Xd_B(1,1);
        Result_Xd_W(i,j)=Xd_W(1,1);
        Result_Xd_WB(i,j)=Xd_WB(1,1);
        Result_Xd_TB(i,j)=Xd_TB(1,1);
        Result_Xd_BT(i,j)=Xd_BT(1,1);

    end                                  
end