Missile datcom与matlab匹配计算程序

clc clear %由用户输入马赫数mach及马赫数编号mach_index，运行计算程序misdat.exe,读取for006.dat文件 mach=input('Please insert the Mach Number: '); mach_index=input('Please insert the Mach index: '); open('Data Create/misdat.exe');% aero=datcomimport('Data Create/for006.dat');% duopian=0; %结果调用 cn=aero{1, 1}.cn; cm=aero{1, 1}.cm; ca=aero{1, 1}.ca; cy=aero{1, 1}.cy; cln=aero{1, 1}.cln; cll=aero{1, 1}.cll; cna=aero{1, 1}.cna; cma=aero{1, 1}.cma; cyb=aero{1, 1}.cyb; % clnb=aero{1, 1}.clnb; % cllb=aero{1, 1}.cllb; xcp=aero{1, 1}.xcp; cd=aero{1, 1}.cd; cl=aero{1, 1}.cl; al=[0;2;4;6;8;10;12;16;20]; results=[al,cd,cl,xcp,ca,cn,cy,cll,cln,cm]; alpha=al.*pi/180; %打印结果到Excel文件 filename='data.xlsx'; xls_sheet_index=1; if mach_index==1 txt={'马赫数','攻角','阻力系数','升力系数','压心系数','轴向力系数','法向力系数','侧向力系数','滚转力矩系数',... '偏航力矩系数','俯仰力矩系数'}; xlswrite(filename,txt,xls_sheet_index,'A1'); xlswrite(filename,[mach.*ones(9,1),alpha,cd,cl,xcp,ca,cn,cy,cll,cln,cm],xls_sheet_index,'A2'); else data_index=(mach_index-1)*9+2; XLrange=['A' num2str(data_index)]; xlswrite(filename,[mach.*ones(9,1),alpha,cd,cl,xcp,ca,cn,cy,cll,cln,cm],xls_sheet_index,XLrange); end %存储结果文件到mat文件，方便日后查看 dp=num2str(duopian,'%d'); mc=num2str(mach,'%4.2f'); save(['DELTA' dp 'MACH' mc '.mat'],'results'); % open results