XFOIL Version 6.94 Calculated polar for: Eiffel 371 (Monge) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2871 0.00922 0.00351 -0.0356 0.5720 0.6656 0.500 0.3405 0.00948 0.00356 -0.0352 0.5572 0.7578 1.000 0.3924 0.00976 0.00367 -0.0344 0.5410 0.7646 1.500 0.4446 0.01003 0.00384 -0.0337 0.5263 0.7697 2.000 0.4958 0.01025 0.00399 -0.0329 0.5095 0.7742 2.500 0.5465 0.01048 0.00417 -0.0320 0.4917 0.7783 3.000 0.5956 0.01074 0.00434 -0.0309 0.4717 0.7829 3.500 0.6434 0.01096 0.00451 -0.0296 0.4475 0.7864 4.000 0.6905 0.01123 0.00472 -0.0283 0.4200 0.7894 4.500 0.7348 0.01164 0.00498 -0.0265 0.3876 0.7931 5.000 0.7774 0.01205 0.00529 -0.0245 0.3599 0.7957 5.500 0.8209 0.01249 0.00566 -0.0228 0.3384 0.7976 6.500 0.9028 0.01340 0.00649 -0.0186 0.3052 0.8007 7.000 0.9426 0.01385 0.00695 -0.0164 0.2901 0.8021 7.500 0.9816 0.01438 0.00748 -0.0142 0.2748 0.8036 8.000 1.0189 0.01489 0.00802 -0.0118 0.2587 0.8049 8.500 1.0540 0.01552 0.00866 -0.0091 0.2396 0.8064 9.000 1.0851 0.01633 0.00943 -0.0060 0.2136 0.8077 9.500 1.1112 0.01740 0.01042 -0.0024 0.1850 0.8088 10.000 1.1344 0.01864 0.01158 0.0014 0.1628 0.8098 11.000 1.1772 0.02149 0.01443 0.0082 0.1371 0.8115 11.500 1.1980 0.02310 0.01611 0.0112 0.1269 0.8120 12.000 1.2175 0.02493 0.01800 0.0137 0.1158 0.8129 12.500 1.2316 0.02726 0.02030 0.0163 0.0954 0.8135 13.500 1.1780 0.03951 0.03220 0.0236 0.0177 0.8142 14.000 1.1786 0.04430 0.03722 0.0241 0.0165 0.8145 14.500 1.1645 0.05105 0.04422 0.0240 0.0146 0.8146 15.000 1.1542 0.05786 0.05129 0.0231 0.0139 0.8148 15.500 1.1389 0.06577 0.05945 0.0214 0.0133 0.8149 16.000 1.1174 0.07511 0.06902 0.0188 0.0125 0.8150 16.500 1.0954 0.08518 0.07933 0.0155 0.0124 0.8150 17.000 1.0751 0.09550 0.08987 0.0116 0.0122 0.8152 17.500 1.0515 0.10673 0.10130 0.0071 0.0120 0.8151 18.000 1.0241 0.11880 0.11353 0.0021 0.0116 0.8151 18.500 1.0143 0.12789 0.12274 -0.0020 0.0113 0.8152 19.000 1.0131 0.13569 0.13069 -0.0059 0.0108 0.8154 19.500 1.0176 0.14216 0.13722 -0.0093 0.0104 0.8155 20.000 1.0218 0.14878 0.14392 -0.0131 0.0096 0.8157 20.500 1.0383 0.15242 0.14757 -0.0154 0.0093 0.8160 21.000 1.0569 0.15542 0.15060 -0.0174 0.0088 0.8167 21.500 1.0699 0.16002 0.15533 -0.0203 0.0087 0.8171 22.000 1.0735 0.16681 0.16231 -0.0247 0.0083 0.8175 22.500 1.0805 0.17271 0.16837 -0.0286 0.0079 0.8179 23.000 1.0866 0.17868 0.17452 -0.0326 0.0079 0.8181 23.500 1.0869 0.18608 0.18212 -0.0374 0.0078 0.8183 24.000 1.0829 0.19455 0.19079 -0.0429 0.0078 0.8184 24.500 1.0655 0.20658 0.20312 -0.0499 0.0080 0.8184 25.000 1.0483 0.21913 0.21590 -0.0573 0.0081 0.8183 25.500 1.0191 0.23578 0.23279 -0.0657 0.0086 0.8180