XFOIL Version 6.96 Calculated polar for: DORNIER A-5 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.000 -0.9165 0.08478 0.08214 -0.0769 1.0000 0.0206 -17.750 -0.9510 0.07621 0.07337 -0.0810 1.0000 0.0206 -17.500 -0.9706 0.07062 0.06764 -0.0830 1.0000 0.0207 -17.250 -0.9898 0.06547 0.06236 -0.0845 1.0000 0.0208 -17.000 -0.9969 0.06222 0.05903 -0.0850 1.0000 0.0210 -16.750 -1.0077 0.05877 0.05547 -0.0852 1.0000 0.0212 -16.500 -1.0219 0.05517 0.05174 -0.0850 1.0000 0.0212 -16.250 -1.0272 0.05189 0.04833 -0.0858 0.9997 0.0213 -16.000 -1.0231 0.04894 0.04524 -0.0878 0.9989 0.0216 -15.750 -1.0162 0.04643 0.04261 -0.0896 0.9978 0.0218 -15.500 -1.0094 0.04398 0.04003 -0.0912 0.9967 0.0219 -15.250 -0.9981 0.04212 0.03806 -0.0928 0.9955 0.0221 -15.000 -0.9969 0.03900 0.03474 -0.0939 0.9945 0.0224 -14.750 -0.9878 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0.9648 0.0284 -10.000 -0.5806 0.01822 0.01294 -0.1084 0.9637 0.0288 -9.750 -0.5507 0.01761 0.01230 -0.1099 0.9626 0.0294 -9.500 -0.5197 0.01702 0.01168 -0.1116 0.9617 0.0298 -9.250 -0.4871 0.01647 0.01110 -0.1135 0.9607 0.0302 -9.000 -0.4734 0.01599 0.01059 -0.1116 0.9542 0.0304 -8.750 -0.4480 0.01508 0.00965 -0.1126 0.9509 0.0311 -8.500 -0.4159 0.01429 0.00885 -0.1149 0.9488 0.0318 -8.250 -0.3811 0.01367 0.00823 -0.1175 0.9470 0.0325 -8.000 -0.3759 0.01322 0.00775 -0.1139 0.9371 0.0328 -7.750 -0.3433 0.01271 0.00721 -0.1158 0.9341 0.0337 -7.500 -0.3220 0.01233 0.00681 -0.1152 0.9277 0.0344 -7.250 -0.2941 0.01193 0.00637 -0.1159 0.9226 0.0350 -7.000 -0.2606 0.01148 0.00588 -0.1178 0.9190 0.0359 -6.750 -0.2437 0.01108 0.00545 -0.1162 0.9116 0.0370 -6.500 -0.2163 0.01075 0.00511 -0.1167 0.9066 0.0384 -6.250 -0.1843 0.01047 0.00479 -0.1181 0.9023 0.0399 -6.000 -0.1688 0.01028 0.00458 -0.1158 0.8943 0.0409 -5.750 -0.1425 0.00995 0.00422 -0.1159 0.8878 0.0436 -5.500 -0.1247 0.00973 0.00401 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0.7734 0.6316 -0.500 0.3713 0.00588 0.00169 -0.1052 0.7677 0.6377 -0.250 0.3962 0.00587 0.00168 -0.1045 0.7598 0.6423 0.000 0.4210 0.00588 0.00168 -0.1038 0.7520 0.6472 0.250 0.4455 0.00588 0.00169 -0.1031 0.7425 0.6518 0.500 0.4688 0.00592 0.00168 -0.1020 0.7307 0.6571 0.750 0.4901 0.00598 0.00171 -0.1005 0.7162 0.6625 1.000 0.5115 0.00606 0.00175 -0.0991 0.7008 0.6676 1.250 0.5323 0.00616 0.00178 -0.0975 0.6822 0.6733 1.500 0.5493 0.00627 0.00182 -0.0951 0.6613 0.6774 1.750 0.5643 0.00644 0.00191 -0.0922 0.6365 0.6817 2.000 0.5802 0.00665 0.00201 -0.0896 0.6058 0.6858 2.250 0.5941 0.00692 0.00212 -0.0867 0.5720 0.6898 2.500 0.6073 0.00724 0.00229 -0.0836 0.5349 0.6938 2.750 0.6135 0.00779 0.00256 -0.0792 0.4659 0.6975 3.000 0.6226 0.00836 0.00286 -0.0756 0.4053 0.7008 3.250 0.6403 0.00869 0.00307 -0.0736 0.3797 0.7042 3.500 0.6588 0.00899 0.00326 -0.0718 0.3567 0.7073 3.750 0.6784 0.00923 0.00343 -0.0702 0.3398 0.7103 4.000 0.6998 0.00942 0.00361 -0.0690 0.3285 0.7130 4.250 0.7204 0.00966 0.00380 -0.0676 0.3164 0.7157 4.500 0.7419 0.00986 0.00397 -0.0664 0.3049 0.7186 4.750 0.7627 0.01008 0.00416 -0.0651 0.2920 0.7216 5.000 0.7827 0.01035 0.00434 -0.0637 0.2750 0.7243 5.250 0.7995 0.01071 0.00457 -0.0618 0.2441 0.7268 5.500 0.8106 0.01130 0.00494 -0.0588 0.2003 0.7291 5.750 0.8273 0.01169 0.00527 -0.0568 0.1819 0.7314 6.000 0.8459 0.01203 0.00555 -0.0553 0.1705 0.7338 6.250 0.8658 0.01232 0.00582 -0.0539 0.1637 0.7362 6.500 0.8848 0.01263 0.00610 -0.0524 0.1575 0.7386 6.750 0.9045 0.01293 0.00638 -0.0511 0.1520 0.7408 7.000 0.9253 0.01315 0.00662 -0.0499 0.1488 0.7432 7.250 0.9447 0.01344 0.00692 -0.0486 0.1440 0.7453 7.500 0.9626 0.01380 0.00728 -0.0470 0.1381 0.7474 7.750 0.9836 0.01403 0.00754 -0.0459 0.1347 0.7497 8.000 1.0031 0.01433 0.00783 -0.0446 0.1271 0.7519 8.250 1.0222 0.01466 0.00814 -0.0433 0.1203 0.7540 8.500 1.0404 0.01504 0.00846 -0.0419 0.1109 0.7559 8.750 1.0583 0.01544 0.00882 -0.0404 0.1052 0.7574 9.000 1.0752 0.01583 0.00918 -0.0388 0.1000 0.7593 9.250 1.0921 0.01622 0.00960 -0.0373 0.0960 0.7611 9.500 1.1098 0.01660 0.01001 -0.0358 0.0935 0.7629 9.750 1.1264 0.01705 0.01046 -0.0343 0.0903 0.7647 10.000 1.1407 0.01762 0.01103 -0.0324 0.0860 0.7668 10.250 1.1585 0.01802 0.01147 -0.0311 0.0841 0.7687 10.500 1.1768 0.01840 0.01188 -0.0299 0.0818 0.7706 10.750 1.1940 0.01886 0.01235 -0.0286 0.0792 0.7722 11.000 1.2087 0.01943 0.01292 -0.0269 0.0758 0.7736 11.250 1.2245 0.01990 0.01342 -0.0255 0.0735 0.7755 11.500 1.2419 0.02033 0.01388 -0.0243 0.0713 0.7770 11.750 1.2574 0.02086 0.01443 -0.0229 0.0689 0.7786 12.000 1.2709 0.02152 0.01508 -0.0212 0.0656 0.7804 12.250 1.2862 0.02209 0.01570 -0.0199 0.0639 0.7822 12.500 1.3012 0.02269 0.01633 -0.0185 0.0622 0.7840 12.750 1.3149 0.02339 0.01703 -0.0171 0.0599 0.7856 13.000 1.3261 0.02425 0.01789 -0.0154 0.0572 0.7869 13.250 1.3404 0.02494 0.01863 -0.0141 0.0557 0.7880 13.500 1.3548 0.02562 0.01936 -0.0129 0.0540 0.7891 13.750 1.3676 0.02640 0.02016 -0.0116 0.0519 0.7908 14.000 1.3774 0.02740 0.02118 -0.0100 0.0496 0.7923 14.250 1.3904 0.02821 0.02205 -0.0088 0.0481 0.7938 14.500 1.4034 0.02904 0.02293 -0.0077 0.0462 0.7954 14.750 1.4138 0.03006 0.02397 -0.0064 0.0442 0.7969 15.000 1.4231 0.03120 0.02514 -0.0050 0.0422 0.7982 15.250 1.4346 0.03220 0.02619 -0.0039 0.0406 0.7995 15.500 1.4447 0.03333 0.02735 -0.0028 0.0389 0.8007 15.750 1.4512 0.03477 0.02879 -0.0015 0.0369 0.8019 16.000 1.4602 0.03604 0.03012 -0.0005 0.0357 0.8030 16.250 1.4680 0.03744 0.03157 0.0006 0.0344 0.8040 16.500 1.4741 0.03903 0.03320 0.0016 0.0331 0.8057 16.750 1.4771 0.04093 0.03515 0.0026 0.0316 0.8073 17.000 1.4843 0.04251 0.03681 0.0033 0.0308 0.8087 17.250 1.4901 0.04426 0.03863 0.0040 0.0297 0.8100 17.500 1.4936 0.04629 0.04073 0.0046 0.0288 0.8112 17.750 1.4942 0.04866 0.04315 0.0052 0.0276 0.8126 18.000 1.4948 0.05113 0.04569 0.0056 0.0267 0.8140 18.250 1.4990 0.05329 0.04794 0.0058 0.0260 0.8152 18.500 1.5005 0.05580 0.05053 0.0059 0.0253 0.8166 18.750 1.4994 0.05868 0.05348 0.0058 0.0246 0.8178 19.000 1.4951 0.06205 0.05692 0.0055 0.0238 0.8187 19.250 1.4887 0.06580 0.06076 0.0049 0.0232 0.8195