XFOIL Version 6.96 Calculated polar for: DAE-11 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.0770 0.08860 0.08544 -0.0736 0.6568 0.0077 -9.000 -0.0712 0.08560 0.08244 -0.0750 0.6553 0.0080 -8.500 -0.2731 0.02894 0.02548 -0.1159 0.6532 0.0092 -8.250 -0.2677 0.02020 0.01583 -0.1202 0.6517 0.0094 -8.000 -0.2437 0.01865 0.01405 -0.1208 0.6502 0.0096 -7.750 -0.2181 0.01755 0.01278 -0.1212 0.6487 0.0097 -7.500 -0.1917 0.01674 0.01183 -0.1214 0.6470 0.0098 -7.250 -0.1650 0.01600 0.01095 -0.1216 0.6453 0.0099 -7.000 -0.1380 0.01530 0.01011 -0.1219 0.6438 0.0101 -6.750 -0.1106 0.01462 0.00932 -0.1221 0.6426 0.0102 -6.500 -0.0831 0.01398 0.00857 -0.1223 0.6412 0.0104 -6.250 -0.0553 0.01339 0.00787 -0.1224 0.6397 0.0106 -6.000 -0.0275 0.01285 0.00722 -0.1226 0.6379 0.0107 -5.750 0.0005 0.01234 0.00660 -0.1228 0.6363 0.0109 -5.500 0.0287 0.01188 0.00605 -0.1229 0.6347 0.0111 -5.250 0.0569 0.01148 0.00556 -0.1230 0.6329 0.0114 -5.000 0.0854 0.01118 0.00518 -0.1232 0.6312 0.0116 -4.750 0.1138 0.01092 0.00484 -0.1233 0.6294 0.0118 -4.500 0.1421 0.01045 0.00431 -0.1235 0.6280 0.0122 -4.250 0.1708 0.01017 0.00400 -0.1237 0.6265 0.0125 -4.000 0.1996 0.00994 0.00375 -0.1239 0.6248 0.0129 -3.750 0.2284 0.00972 0.00350 -0.1240 0.6230 0.0133 -3.500 0.2573 0.00951 0.00326 -0.1242 0.6212 0.0137 -3.250 0.2861 0.00933 0.00304 -0.1244 0.6193 0.0142 -3.000 0.3149 0.00916 0.00283 -0.1246 0.6174 0.0146 -2.750 0.3437 0.00897 0.00261 -0.1247 0.6155 0.0152 -2.500 0.3725 0.00884 0.00245 -0.1249 0.6136 0.0160 -2.250 0.4016 0.00870 0.00232 -0.1251 0.6120 0.0169 -2.000 0.4306 0.00859 0.00220 -0.1254 0.6100 0.0179 -1.750 0.4596 0.00846 0.00208 -0.1256 0.6078 0.0195 -1.500 0.4886 0.00837 0.00198 -0.1258 0.6056 0.0213 -1.250 0.5175 0.00828 0.00188 -0.1260 0.6033 0.0235 -1.000 0.5463 0.00821 0.00180 -0.1262 0.6009 0.0263 -0.750 0.5751 0.00814 0.00174 -0.1264 0.5985 0.0315 -0.500 0.6042 0.00805 0.00169 -0.1266 0.5962 0.0409 -0.250 0.6331 0.00796 0.00165 -0.1269 0.5934 0.0541 0.000 0.6619 0.00787 0.00162 -0.1271 0.5904 0.0771 0.250 0.6906 0.00776 0.00160 -0.1274 0.5875 0.1138 0.500 0.7190 0.00764 0.00160 -0.1276 0.5846 0.1690 0.750 0.7476 0.00746 0.00162 -0.1279 0.5820 0.2459 1.000 0.7761 0.00729 0.00166 -0.1283 0.5789 0.3323 1.250 0.8044 0.00714 0.00171 -0.1285 0.5755 0.4178 1.500 0.8324 0.00701 0.00177 -0.1287 0.5719 0.5053 1.750 0.8599 0.00684 0.00184 -0.1288 0.5684 0.6144 2.000 0.8850 0.00646 0.00195 -0.1284 0.5646 0.7965 2.500 0.9458 0.00626 0.00202 -0.1294 0.5556 1.0000 2.750 0.9742 0.00633 0.00207 -0.1296 0.5514 1.0000 3.000 1.0025 0.00642 0.00213 -0.1298 0.5464 1.0000 3.250 1.0304 0.00653 0.00219 -0.1300 0.5410 1.0000 3.500 1.0586 0.00662 0.00227 -0.1301 0.5360 1.0000 3.750 1.0864 0.00672 0.00235 -0.1303 0.5298 1.0000 4.000 1.1140 0.00685 0.00245 -0.1304 0.5239 1.0000 4.250 1.1418 0.00696 0.00255 -0.1305 0.5175 1.0000 4.750 1.1964 0.00725 0.00278 -0.1307 0.5038 1.0000 5.250 1.2500 0.00758 0.00307 -0.1308 0.4874 1.0000 5.500 1.2761 0.00779 0.00324 -0.1307 0.4784 1.0000 5.750 1.3021 0.00800 0.00342 -0.1306 0.4679 1.0000 6.000 1.3279 0.00822 0.00361 -0.1305 0.4576 1.0000 6.250 1.3529 0.00848 0.00383 -0.1303 0.4465 1.0000 6.500 1.3773 0.00878 0.00408 -0.1300 0.4340 1.0000 6.750 1.4009 0.00910 0.00436 -0.1296 0.4203 1.0000 7.000 1.4238 0.00946 0.00467 -0.1291 0.4058 1.0000 7.250 1.4456 0.00986 0.00501 -0.1284 0.3901 1.0000 7.500 1.4664 0.01030 0.00538 -0.1276 0.3743 1.0000 7.750 1.4859 0.01077 0.00580 -0.1266 0.3577 1.0000 8.000 1.5035 0.01130 0.00625 -0.1253 0.3403 1.0000 8.250 1.5189 0.01188 0.00676 -0.1237 0.3229 1.0000 8.500 1.5301 0.01255 0.00736 -0.1214 0.3051 1.0000 8.750 1.5333 0.01329 0.00805 -0.1177 0.2897 1.0000 9.000 1.5339 0.01433 0.00903 -0.1142 0.2744 1.0000 9.250 1.5358 0.01558 0.01023 -0.1114 0.2587 1.0000 9.500 1.5384 0.01698 0.01157 -0.1089 0.2428 1.0000 10.000 1.5437 0.02004 0.01450 -0.1045 0.2104 1.0000 10.250 1.5489 0.02148 0.01591 -0.1027 0.1983 1.0000 10.500 1.5514 0.02313 0.01750 -0.1007 0.1833 1.0000 10.750 1.5554 0.02472 0.01904 -0.0989 0.1708 1.0000 11.250 1.5611 0.02814 0.02238 -0.0954 0.1450 1.0000 11.500 1.5628 0.02999 0.02417 -0.0937 0.1316 1.0000 11.750 1.5668 0.03170 0.02585 -0.0922 0.1210 1.0000 12.000 1.5706 0.03348 0.02760 -0.0907 0.1113 1.0000 12.250 1.5737 0.03539 0.02947 -0.0894 0.1003 1.0000 12.500 1.5759 0.03745 0.03150 -0.0881 0.0899 1.0000 12.750 1.5805 0.03932 0.03335 -0.0869 0.0819 1.0000 13.000 1.5839 0.04139 0.03540 -0.0859 0.0733 1.0000 13.250 1.5887 0.04335 0.03735 -0.0849 0.0657 1.0000 13.500 1.5911 0.04560 0.03957 -0.0839 0.0582 1.0000 13.750 1.5951 0.04773 0.04170 -0.0831 0.0519 1.0000 14.000 1.6006 0.04977 0.04377 -0.0824 0.0477 1.0000 14.250 1.6045 0.05200 0.04599 -0.0817 0.0429 1.0000 14.500 1.6088 0.05424 0.04825 -0.0811 0.0386 1.0000 14.750 1.6127 0.05654 0.05057 -0.0805 0.0348 1.0000 15.000 1.6166 0.05892 0.05297 -0.0800 0.0316 1.0000 15.250 1.6206 0.06131 0.05538 -0.0796 0.0288 1.0000 15.500 1.6241 0.06380 0.05792 -0.0793 0.0261 1.0000 15.750 1.6274 0.06635 0.06049 -0.0790 0.0238 1.0000 16.000 1.6309 0.06894 0.06313 -0.0788 0.0219 1.0000 16.250 1.6334 0.07167 0.06589 -0.0787 0.0200 1.0000 16.500 1.6367 0.07436 0.06864 -0.0786 0.0187 1.0000 16.750 1.6393 0.07713 0.07146 -0.0786 0.0172 1.0000 17.000 1.6402 0.08023 0.07461 -0.0787 0.0159 1.0000 17.250 1.6434 0.08302 0.07746 -0.0789 0.0148 1.0000 17.500 1.6443 0.08619 0.08070 -0.0791 0.0138 1.0000 17.750 1.6447 0.08945 0.08400 -0.0795 0.0128 1.0000 18.000 1.6463 0.09258 0.08721 -0.0799 0.0121 1.0000 18.250 1.6472 0.09585 0.09055 -0.0804 0.0114 1.0000 18.500 1.6469 0.09933 0.09408 -0.0810 0.0107 1.0000 18.750 1.6455 0.10304 0.09786 -0.0818 0.0100 1.0000 19.000 1.6465 0.10636 0.10126 -0.0825 0.0096 1.0000