program_3.m

用MATLAB编写关于飞机设计的matlab程序

%符号说明
%V：巡航速度（m/s）；n_max：正向最大过载系数；i：展向点数 Cs：安全系数；n_des：设计过载系数
%x：压心距前缘距离(向后为正)(m)；y：压心距根弦距离(向右为正)(m)； ca_w：机翼平均气动弦长(m)
%S：升力格面积（m^2）；CL：升力格处的升力系数； L：升力(N)
%Q：升力格分界线处的剪力(N)； M：升力格分界线处的弯矩(N*m)

%此程序计算升力沿右半机翼展向的分布
V=15;n_max=3.8;Cs=1.5;ca_w=0.268;
n_des=n_max*Cs;
x=[0.1226,0.1227,0.1227,0.1229,0.1230,0.1233,0.1236,0.1240,0.1244,0.1249,0.1254,...
    0.1262,0.1271,0.1283,0.1298,0.1317,0.1342,0.1376,0.1421,0.1484];
y=[0.02402,0.07491,0.12865,0.18239,0.23613,0.30089,0.36565,0.41939,0.47313,0.51867,...
    0.56418,0.61784,0.67151,0.72517,0.77884,0.83250,0.88617,0.93984,0.99350,1.04717];
S=ca_w*2*[0.02402,0.02687,0.02687,0.02687,0.02687,0.03789,0.02687,0.02687,0.02687,...
    0.01870,0.02687,0.02687,0.02687,0.02687,0.02687,0.02687,0.02687,0.02687,0.02687,0.02687];
CL=[0.3453,0.3451,0.3445,0.3437,0.3425,0.3408,0.3383,0.3357,0.3326,0.3287,...
    0.3248,0.3195,0.3131,0.3050,0.2950,0.2822,0.2654,0.2422,0.2081,0.1505];
L=n_des*0.5*1.225*V^2*S.*CL;
Q(20)=L(20);
M(20)=L(20)*S(20)/0.5;
for i=19:-1:1;
    Q(i)=L(i)+Q(i+1);
    M(i)=M(i+1)+Q(i+1).*S(i)/0.25+L(i).*S(i)/0.5;
end
disp('                 ***** 右半机翼载荷沿展向的分布 *****');
disp('******************** 各载荷均为考虑过载后的最大值 ********************');
disp('** x：压心距前缘距离(向后为正)；y：压心距根弦距离(向右为正)；L：升力 **');
disp('       ** Q：升力格分界线处的剪力N)； M：升力格分界线处的弯矩 **');
disp('       number    x(m)       y(m)      L(N)      Q(N)      M(N*m)');
for i=1:1:20;
    fprintf('        %2d     %7.4f    %7.4f   %7.4f   %7.4f    %7.4f\n',i,x(i),y(i),L(i),Q(i),M(i));
end