XFOIL Version 6.96 Calculated polar for: AG10 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.6702 0.12557 0.12391 0.0428 1.0000 0.0044 -10.000 -0.6662 0.12192 0.12027 0.0413 1.0000 0.0045 -7.500 -0.6695 0.01896 0.01535 -0.0307 1.0000 0.0055 -7.250 -0.6441 0.01687 0.01292 -0.0310 1.0000 0.0057 -7.000 -0.6179 0.01541 0.01119 -0.0311 1.0000 0.0059 -6.750 -0.5912 0.01435 0.00992 -0.0311 1.0000 0.0061 -6.500 -0.5641 0.01348 0.00887 -0.0311 1.0000 0.0063 -6.250 -0.5368 0.01276 0.00801 -0.0310 1.0000 0.0063 -6.000 -0.5096 0.01175 0.00683 -0.0310 1.0000 0.0067 -5.750 -0.4821 0.01116 0.00615 -0.0310 1.0000 0.0069 -5.500 -0.4544 0.01069 0.00561 -0.0310 1.0000 0.0072 -5.250 -0.4266 0.01024 0.00510 -0.0309 1.0000 0.0074 -5.000 -0.3988 0.00982 0.00461 -0.0308 1.0000 0.0078 -4.750 -0.3709 0.00946 0.00419 -0.0308 1.0000 0.0082 -4.500 -0.3429 0.00916 0.00385 -0.0307 1.0000 0.0087 -4.250 -0.3150 0.00872 0.00337 -0.0306 1.0000 0.0094 -4.000 -0.2870 0.00842 0.00306 -0.0306 1.0000 0.0101 -3.750 -0.2589 0.00816 0.00277 -0.0305 1.0000 0.0109 -3.500 -0.2308 0.00792 0.00251 -0.0304 1.0000 0.0116 -3.250 -0.2028 0.00765 0.00223 -0.0303 1.0000 0.0130 -3.000 -0.1747 0.00745 0.00203 -0.0303 1.0000 0.0144 -2.750 -0.1466 0.00724 0.00183 -0.0302 1.0000 0.0162 -2.500 -0.1128 0.00709 0.00168 -0.0314 0.9698 0.0188 -2.250 -0.0850 0.00700 0.00154 -0.0311 0.9267 0.0220 -2.000 -0.0610 0.00702 0.00142 -0.0298 0.8746 0.0256 -1.750 -0.0354 0.00707 0.00130 -0.0291 0.8191 0.0306 -1.500 -0.0085 0.00714 0.00119 -0.0286 0.7610 0.0376 -1.250 0.0189 0.00723 0.00109 -0.0284 0.7000 0.0471 -1.000 0.0466 0.00732 0.00102 -0.0283 0.6384 0.0585 -0.750 0.0745 0.00742 0.00096 -0.0283 0.5789 0.0728 -0.500 0.1025 0.00752 0.00092 -0.0283 0.5239 0.0894 -0.250 0.1306 0.00758 0.00090 -0.0284 0.4773 0.1107 0.000 0.1587 0.00763 0.00088 -0.0284 0.4371 0.1386 0.250 0.1868 0.00763 0.00088 -0.0285 0.4040 0.1778 0.500 0.2150 0.00759 0.00090 -0.0286 0.3745 0.2357 0.750 0.2432 0.00749 0.00093 -0.0287 0.3480 0.3173 1.000 0.2715 0.00725 0.00097 -0.0290 0.3245 0.4536 1.250 0.2927 0.00586 0.00098 -0.0275 0.3047 1.0000 1.500 0.3209 0.00600 0.00102 -0.0275 0.2834 1.0000 1.750 0.3490 0.00615 0.00107 -0.0274 0.2622 1.0000 2.000 0.3771 0.00631 0.00113 -0.0274 0.2423 1.0000 2.250 0.4052 0.00646 0.00120 -0.0274 0.2223 1.0000 2.500 0.4332 0.00664 0.00129 -0.0273 0.2018 1.0000 2.750 0.4612 0.00682 0.00138 -0.0273 0.1829 1.0000 3.000 0.4892 0.00701 0.00149 -0.0273 0.1639 1.0000 3.250 0.5171 0.00721 0.00162 -0.0272 0.1453 1.0000 3.500 0.5449 0.00743 0.00175 -0.0272 0.1272 1.0000 3.750 0.5727 0.00765 0.00190 -0.0272 0.1104 1.0000 4.000 0.6004 0.00789 0.00206 -0.0271 0.0932 1.0000 4.250 0.6280 0.00817 0.00226 -0.0271 0.0760 1.0000 4.500 0.6556 0.00844 0.00247 -0.0270 0.0609 1.0000 4.750 0.6831 0.00874 0.00269 -0.0269 0.0471 1.0000 5.000 0.7105 0.00903 0.00293 -0.0269 0.0368 1.0000 5.250 0.7378 0.00935 0.00321 -0.0268 0.0277 1.0000 5.500 0.7651 0.00968 0.00350 -0.0267 0.0207 1.0000 5.750 0.7923 0.00999 0.00380 -0.0266 0.0164 1.0000 6.000 0.8195 0.01030 0.00412 -0.0265 0.0134 1.0000 6.250 0.8466 0.01064 0.00447 -0.0263 0.0113 1.0000 6.500 0.8735 0.01099 0.00483 -0.0262 0.0097 1.0000 6.750 0.9004 0.01138 0.00526 -0.0260 0.0087 1.0000 7.000 0.9272 0.01174 0.00566 -0.0259 0.0079 1.0000 7.250 0.9537 0.01215 0.00610 -0.0257 0.0071 1.0000 7.500 0.9800 0.01266 0.00666 -0.0255 0.0064 1.0000 7.750 1.0063 0.01309 0.00716 -0.0253 0.0062 1.0000 8.000 1.0324 0.01357 0.00771 -0.0251 0.0059 1.0000 8.250 1.0583 0.01409 0.00829 -0.0248 0.0056 1.0000 8.500 1.0839 0.01463 0.00890 -0.0246 0.0053 1.0000 8.750 1.1093 0.01521 0.00956 -0.0243 0.0051 1.0000 9.000 1.1343 0.01586 0.01028 -0.0240 0.0049 1.0000 9.250 1.1586 0.01664 0.01117 -0.0237 0.0047 1.0000 9.500 1.1817 0.01774 0.01239 -0.0233 0.0045 1.0000 9.750 1.2056 0.01849 0.01326 -0.0229 0.0044 1.0000 10.000 1.2291 0.01931 0.01421 -0.0225 0.0043 1.0000 10.250 1.2520 0.02021 0.01523 -0.0220 0.0042 1.0000 10.500 1.2742 0.02121 0.01637 -0.0216 0.0041 1.0000 10.750 1.2956 0.02231 0.01762 -0.0210 0.0040 1.0000 11.000 1.3161 0.02352 0.01900 -0.0204 0.0039 1.0000 11.250 1.3356 0.02484 0.02048 -0.0198 0.0038 1.0000 11.500 1.3539 0.02629 0.02210 -0.0191 0.0038 1.0000 11.750 1.3707 0.02788 0.02388 -0.0184 0.0037 1.0000 12.000 1.3856 0.02965 0.02584 -0.0176 0.0036 1.0000 12.250 1.3984 0.03160 0.02799 -0.0167 0.0036 1.0000 12.500 1.4082 0.03381 0.03041 -0.0158 0.0035 1.0000 12.750 1.4143 0.03628 0.03309 -0.0148 0.0035 1.0000 13.000 1.4146 0.03921 0.03623 -0.0139 0.0034 1.0000 13.250 1.4038 0.04252 0.03973 -0.0126 0.0034 1.0000 13.500 1.3830 0.04864 0.04609 -0.0163 0.0034 1.0000 13.750 1.3471 0.06517 0.06293 -0.0328 0.0035 1.0000 14.000 1.2942 0.08151 0.07943 -0.0432 0.0036 1.0000 14.250 1.2435 0.09603 0.09406 -0.0510 0.0036 1.0000