XFOIL Version 6.96 Calculated polar for: Eiffel 371 (Monge) 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 ------ -------- --------- --------- -------- -------- -------- -12.500 -0.6398 0.05535 0.05334 -0.0718 1.0000 0.0098 -12.250 -0.6878 0.04675 0.04453 -0.0769 1.0000 0.0097 -12.000 -0.7324 0.04195 0.03955 -0.0746 1.0000 0.0095 -11.750 -0.7615 0.03964 0.03711 -0.0700 1.0000 0.0096 -11.500 -0.7658 0.03616 0.03335 -0.0703 0.9974 0.0097 -11.250 -0.7722 0.03195 0.02875 -0.0697 0.9922 0.0097 -11.000 -0.7632 0.02908 0.02555 -0.0691 0.9873 0.0098 -10.750 -0.7430 0.02716 0.02342 -0.0693 0.9848 0.0099 -10.500 -0.7198 0.02551 0.02155 -0.0697 0.9831 0.0100 -10.250 -0.7133 0.02251 0.01818 -0.0675 0.9772 0.0101 -10.000 -0.6931 0.02039 0.01586 -0.0671 0.9742 0.0104 -9.750 -0.6644 0.01952 0.01494 -0.0676 0.9724 0.0107 -9.500 -0.6335 0.01892 0.01428 -0.0684 0.9709 0.0110 -9.250 -0.6046 0.01803 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0.00970 0.00340 -0.0549 0.7099 0.0248 -4.250 -0.1119 0.00956 0.00315 -0.0530 0.6835 0.0278 -4.000 -0.0896 0.00951 0.00300 -0.0517 0.6622 0.0306 -3.750 -0.0678 0.00936 0.00280 -0.0503 0.6434 0.0366 -3.500 -0.0460 0.00918 0.00264 -0.0489 0.6279 0.0519 -3.250 -0.0240 0.00900 0.00253 -0.0476 0.6155 0.0806 -3.000 -0.0011 0.00884 0.00243 -0.0465 0.6042 0.1063 -2.750 0.0212 0.00865 0.00234 -0.0453 0.5943 0.1436 -2.500 0.0417 0.00839 0.00223 -0.0438 0.5852 0.1989 -2.250 0.0532 0.00769 0.00210 -0.0407 0.5779 0.3622 -2.000 0.0724 0.00745 0.00203 -0.0389 0.5700 0.4227 -1.750 0.0932 0.00727 0.00207 -0.0374 0.5631 0.4980 -1.500 0.1206 0.00735 0.00214 -0.0371 0.5559 0.5279 -1.250 0.1478 0.00745 0.00219 -0.0369 0.5493 0.5417 -1.000 0.1751 0.00751 0.00222 -0.0367 0.5427 0.5519 -0.750 0.2021 0.00762 0.00225 -0.0364 0.5364 0.5589 -0.500 0.2284 0.00762 0.00223 -0.0360 0.5298 0.5628 -0.250 0.2546 0.00767 0.00223 -0.0356 0.5220 0.5677 0.000 0.2812 0.00773 0.00224 -0.0353 0.5155 0.5721 0.250 0.3073 0.00774 0.00222 -0.0350 0.5077 0.5766 0.500 0.3327 0.00776 0.00221 -0.0345 0.5010 0.5825 0.750 0.3597 0.00780 0.00222 -0.0343 0.4944 0.5879 1.000 0.3847 0.00779 0.00218 -0.0338 0.4875 0.5911 1.250 0.4109 0.00779 0.00218 -0.0335 0.4804 0.5929 1.500 0.4364 0.00783 0.00218 -0.0331 0.4718 0.5946 1.750 0.4626 0.00786 0.00219 -0.0329 0.4639 0.5961 2.000 0.4879 0.00792 0.00220 -0.0325 0.4544 0.5977 2.250 0.5139 0.00796 0.00222 -0.0322 0.4437 0.5992 2.500 0.5391 0.00805 0.00225 -0.0318 0.4306 0.6009 2.750 0.5639 0.00814 0.00229 -0.0314 0.4164 0.6025 3.000 0.5876 0.00823 0.00232 -0.0307 0.3995 0.6048 3.250 0.6109 0.00836 0.00238 -0.0300 0.3812 0.6069 3.500 0.6342 0.00851 0.00246 -0.0294 0.3643 0.6089 3.750 0.6574 0.00867 0.00255 -0.0287 0.3486 0.6108 4.000 0.6808 0.00882 0.00265 -0.0281 0.3352 0.6130 4.250 0.7042 0.00898 0.00276 -0.0275 0.3229 0.6151 4.750 0.7513 0.00923 0.00296 -0.0263 0.3045 0.6209 5.000 0.7738 0.00935 0.00308 -0.0256 0.2960 0.6256 5.500 0.8163 0.00954 0.00351 -0.0236 0.2817 0.7353 5.750 0.8404 0.00970 0.00368 -0.0231 0.2753 0.7402 6.000 0.8633 0.00990 0.00385 -0.0225 0.2676 0.7432 6.250 0.8867 0.01007 0.00401 -0.0220 0.2611 0.7454 6.500 0.9086 0.01026 0.00417 -0.0212 0.2536 0.7473 6.750 0.9299 0.01044 0.00433 -0.0203 0.2464 0.7490 7.000 0.9507 0.01062 0.00450 -0.0194 0.2389 0.7503 7.250 0.9705 0.01084 0.00469 -0.0182 0.2290 0.7515 7.500 0.9887 0.01113 0.00493 -0.0168 0.2167 0.7528 7.750 1.0063 0.01145 0.00521 -0.0153 0.2041 0.7541 8.000 1.0232 0.01181 0.00551 -0.0137 0.1892 0.7552 8.250 1.0389 0.01221 0.00584 -0.0119 0.1731 0.7566 8.500 1.0528 0.01267 0.00622 -0.0098 0.1562 0.7577 8.750 1.0672 0.01312 0.00662 -0.0079 0.1445 0.7589 9.000 1.0818 0.01355 0.00701 -0.0061 0.1365 0.7601 9.250 1.0982 0.01393 0.00737 -0.0046 0.1307 0.7613 9.500 1.1138 0.01432 0.00776 -0.0030 0.1263 0.7624 9.750 1.1278 0.01478 0.00821 -0.0012 0.1206 0.7634 10.000 1.1452 0.01511 0.00856 -0.0001 0.1177 0.7642 10.250 1.1616 0.01548 0.00895 0.0012 0.1153 0.7648 10.500 1.1750 0.01596 0.00942 0.0029 0.1107 0.7655 10.750 1.1884 0.01642 0.00990 0.0046 0.1065 0.7665 11.000 1.2055 0.01675 0.01027 0.0056 0.1031 0.7674 11.250 1.2155 0.01739 0.01087 0.0076 0.0950 0.7682 11.500 1.2251 0.01807 0.01149 0.0096 0.0827 0.7689 11.750 1.2133 0.01976 0.01296 0.0144 0.0525 0.7695 12.000 1.1905 0.02218 0.01521 0.0200 0.0213 0.7700 12.250 1.1901 0.02359 0.01664 0.0225 0.0158 0.7707 12.500 1.1950 0.02479 0.01790 0.0242 0.0144 0.7713 12.750 1.1978 0.02619 0.01938 0.0260 0.0131 0.7719 13.000 1.2035 0.02748 0.02073 0.0272 0.0125 0.7725 13.250 1.2081 0.02893 0.02225 0.0284 0.0119 0.7731 13.500 1.2136 0.03038 0.02377 0.0293 0.0118 0.7736 13.750 1.2156 0.03216 0.02564 0.0302 0.0112 0.7742 14.000 1.2168 0.03412 0.02766 0.0310 0.0109 0.7745 14.250 1.2163 0.03630 0.02991 0.0316 0.0104 0.7751 14.500 1.2075 0.03937 0.03311 0.0324 0.0099 0.7754 14.750 1.2070 0.04179 0.03562 0.0326 0.0098 0.7757 15.000 1.2115 0.04379 0.03767 0.0326 0.0095 0.7761 15.250 1.2083 0.04663 0.04060 0.0325 0.0094 0.7764 15.500 1.2096 0.04906 0.04311 0.0323 0.0093 0.7768 15.750 1.2049 0.05226 0.04639 0.0320 0.0090 0.7770 16.000 1.2036 0.05513 0.04934 0.0315 0.0088 0.7773 16.250 1.1980 0.05859 0.05288 0.0308 0.0085 0.7775 16.500 1.1917 0.06225 0.05663 0.0300 0.0083 0.7777 16.750 1.1841 0.06622 0.06069 0.0290 0.0084 0.7778 17.000 1.1744 0.07058 0.06515 0.0278 0.0083 0.7780 17.250 1.1633 0.07530 0.06997 0.0264 0.0081 0.7781 17.500 1.1576 0.07938 0.07414 0.0249 0.0080 0.7783 17.750 1.1417 0.08508 0.07995 0.0230 0.0079 0.7784 18.000 1.1208 0.09174 0.08673 0.0206 0.0078 0.7784 18.250 1.1131 0.09647 0.09156 0.0187 0.0078 0.7786 18.500 1.0996 0.10221 0.09740 0.0164 0.0078 0.7788 18.750 1.0870 0.10790 0.10319 0.0140 0.0078 0.7789