XFOIL Version 6.96 Calculated polar for: Smoothed ATR airfoil coordinates obtained using 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.7334 0.06448 0.06148 -0.0578 1.0000 0.0244 -13.500 -0.7931 0.05151 0.04815 -0.0682 1.0000 0.0241 -13.250 -0.8229 0.04553 0.04193 -0.0711 1.0000 0.0240 -13.000 -0.8474 0.04116 0.03733 -0.0713 1.0000 0.0240 -12.750 -0.8628 0.03825 0.03421 -0.0699 1.0000 0.0242 -12.500 -0.8747 0.03589 0.03167 -0.0674 1.0000 0.0243 -12.250 -0.8852 0.03387 0.02946 -0.0639 1.0000 0.0243 -12.000 -0.8929 0.03236 0.02779 -0.0598 1.0000 0.0245 -11.750 -0.8991 0.03120 0.02649 -0.0552 1.0000 0.0248 -11.500 -0.9003 0.02994 0.02507 -0.0514 1.0000 0.0249 -11.250 -0.9021 0.02900 0.02398 -0.0470 1.0000 0.0252 -11.000 -0.9063 0.02826 0.02312 -0.0420 1.0000 0.0253 -10.750 -0.9091 0.02742 0.02215 -0.0373 1.0000 0.0254 -10.500 -0.8995 0.02550 0.02006 -0.0353 0.9987 0.0257 -10.250 -0.8709 0.02395 0.01842 -0.0365 0.9958 0.0262 -10.000 -0.8398 0.02296 0.01738 -0.0379 0.9932 0.0267 -9.750 -0.8111 0.02208 0.01644 -0.0386 0.9897 0.0271 -9.500 -0.7801 0.02117 0.01544 -0.0397 0.9865 0.0277 -9.250 -0.7454 0.02029 0.01447 -0.0415 0.9838 0.0283 -9.000 -0.7081 0.01940 0.01348 -0.0436 0.9806 0.0292 -8.750 -0.6742 0.01865 0.01261 -0.0449 0.9757 0.0298 -8.500 -0.6396 0.01743 0.01137 -0.0467 0.9726 0.0308 -8.250 -0.6019 0.01677 0.01071 -0.0489 0.9699 0.0319 -8.000 -0.5703 0.01629 0.01021 -0.0496 0.9635 0.0332 -7.750 -0.5369 0.01574 0.00958 -0.0506 0.9576 0.0345 -7.500 -0.5099 0.01500 0.00882 -0.0505 0.9500 0.0358 -7.250 -0.4830 0.01456 0.00838 -0.0503 0.9421 0.0373 -7.000 -0.4587 0.01422 0.00800 -0.0493 0.9323 0.0391 -6.750 -0.4342 0.01383 0.00753 -0.0484 0.9229 0.0410 -6.500 -0.4131 0.01340 0.00713 -0.0468 0.9115 0.0433 -6.250 -0.3891 0.01318 0.00686 -0.0458 0.9008 0.0462 -6.000 -0.3662 0.01277 0.00642 -0.0445 0.8903 0.0493 -5.750 -0.3424 0.01255 0.00619 -0.0435 0.8778 0.0526 -5.500 -0.3190 0.01220 0.00580 -0.0423 0.8653 0.0560 -5.250 -0.2949 0.01193 0.00552 -0.0413 0.8519 0.0596 -5.000 -0.2696 0.01177 0.00527 -0.0405 0.8376 0.0627 -4.750 -0.2466 0.01139 0.00489 -0.0393 0.8211 0.0670 -4.500 -0.2216 0.01123 0.00467 -0.0384 0.8015 0.0710 -4.250 -0.1980 0.01097 0.00435 -0.0373 0.7783 0.0754 -4.000 -0.1737 0.01083 0.00412 -0.0363 0.7534 0.0801 -3.750 -0.1496 0.01068 0.00387 -0.0353 0.7276 0.0855 -3.500 -0.1254 0.01058 0.00369 -0.0344 0.7014 0.0922 -3.250 -0.1015 0.01044 0.00349 -0.0334 0.6736 0.1011 -3.000 -0.0778 0.01034 0.00331 -0.0324 0.6432 0.1129 -2.750 -0.0546 0.01025 0.00316 -0.0313 0.6119 0.1302 -2.500 -0.0312 0.01016 0.00303 -0.0303 0.5810 0.1544 -2.000 0.0142 0.00988 0.00279 -0.0282 0.5121 0.2325 -1.750 0.0323 0.00948 0.00264 -0.0265 0.4650 0.3477 -1.500 0.0497 0.00913 0.00258 -0.0246 0.4280 0.4786 -1.250 0.0686 0.00890 0.00259 -0.0228 0.4049 0.5771 -1.000 0.0897 0.00880 0.00264 -0.0213 0.3886 0.6518 -0.750 0.1130 0.00876 0.00267 -0.0202 0.3761 0.7003 -0.500 0.1367 0.00874 0.00272 -0.0190 0.3664 0.7403 -0.250 0.1608 0.00873 0.00279 -0.0179 0.3578 0.7780 0.000 0.1851 0.00876 0.00290 -0.0168 0.3506 0.8193 0.250 0.2102 0.00884 0.00304 -0.0158 0.3438 0.8560 0.500 0.2343 0.00904 0.00321 -0.0145 0.3372 0.8866 0.750 0.2597 0.00918 0.00336 -0.0135 0.3318 0.9083 1.000 0.2850 0.00933 0.00348 -0.0126 0.3264 0.9242 1.250 0.3115 0.00956 0.00363 -0.0119 0.3212 0.9369 1.500 0.3438 0.00977 0.00380 -0.0125 0.3165 0.9462 1.750 0.3781 0.00998 0.00398 -0.0134 0.3120 0.9568 2.000 0.4225 0.01026 0.00417 -0.0166 0.3067 0.9617 2.250 0.4569 0.01052 0.00433 -0.0179 0.3015 0.9667 2.500 0.4948 0.01063 0.00443 -0.0199 0.2978 0.9699 2.750 0.5355 0.01077 0.00453 -0.0225 0.2937 0.9719 3.000 0.5743 0.01096 0.00464 -0.0248 0.2898 0.9746 3.250 0.6105 0.01126 0.00485 -0.0266 0.2853 0.9790 3.500 0.6501 0.01136 0.00496 -0.0290 0.2823 0.9829 3.750 0.6928 0.01147 0.00504 -0.0321 0.2784 0.9856 4.000 0.7314 0.01160 0.00514 -0.0344 0.2749 0.9889 4.250 0.7666 0.01181 0.00528 -0.0360 0.2716 0.9924 4.500 0.8032 0.01204 0.00546 -0.0380 0.2681 0.9948 4.750 0.8405 0.01210 0.00555 -0.0401 0.2655 0.9974 5.000 0.8768 0.01220 0.00565 -0.0420 0.2623 0.9997 5.250 0.8998 0.01231 0.00575 -0.0412 0.2595 1.0000 5.500 0.9196 0.01246 0.00588 -0.0397 0.2571 1.0000 5.750 0.9388 0.01270 0.00608 -0.0382 0.2545 1.0000 6.000 0.9582 0.01295 0.00632 -0.0367 0.2521 1.0000 6.250 0.9781 0.01306 0.00647 -0.0352 0.2502 1.0000 6.500 0.9975 0.01319 0.00663 -0.0337 0.2479 1.0000 6.750 1.0166 0.01334 0.00679 -0.0321 0.2454 1.0000 7.000 1.0353 0.01350 0.00696 -0.0304 0.2432 1.0000 7.250 1.0534 0.01371 0.00716 -0.0286 0.2410 1.0000 7.500 1.0711 0.01401 0.00743 -0.0268 0.2386 1.0000 7.750 1.0891 0.01429 0.00772 -0.0251 0.2363 1.0000 8.000 1.1073 0.01443 0.00791 -0.0233 0.2345 1.0000 8.250 1.1255 0.01459 0.00811 -0.0215 0.2323 1.0000 8.500 1.1439 0.01478 0.00833 -0.0198 0.2301 1.0000 8.750 1.1625 0.01498 0.00854 -0.0182 0.2280 1.0000 9.000 1.1810 0.01520 0.00876 -0.0166 0.2257 1.0000 9.250 1.1998 0.01559 0.00911 -0.0151 0.2229 1.0000 9.500 1.2191 0.01588 0.00944 -0.0137 0.2209 1.0000 9.750 1.2381 0.01607 0.00970 -0.0122 0.2191 1.0000 10.000 1.2570 0.01628 0.00996 -0.0108 0.2168 1.0000 10.250 1.2757 0.01650 0.01022 -0.0093 0.2144 1.0000 10.500 1.2940 0.01676 0.01050 -0.0078 0.2123 1.0000 10.750 1.3106 0.01707 0.01081 -0.0060 0.2099 1.0000 11.000 1.3286 0.01757 0.01129 -0.0046 0.2070 1.0000 11.250 1.3435 0.01778 0.01160 -0.0025 0.2054 1.0000 11.500 1.3593 0.01805 0.01194 -0.0007 0.2033 1.0000 11.750 1.3751 0.01834 0.01229 0.0011 0.2009 1.0000 12.000 1.3908 0.01866 0.01265 0.0028 0.1985 1.0000 12.250 1.4061 0.01906 0.01306 0.0044 0.1962 1.0000 12.500 1.4219 0.01966 0.01363 0.0058 0.1933 1.0000 12.750 1.4366 0.02004 0.01412 0.0074 0.1913 1.0000 13.000 1.4514 0.02046 0.01464 0.0089 0.1891 1.0000 13.250 1.4659 0.02092 0.01518 0.0103 0.1866 1.0000 13.500 1.4796 0.02143 0.01573 0.0118 0.1840 1.0000 13.750 1.4917 0.02207 0.01637 0.0133 0.1812 1.0000 14.000 1.5041 0.02281 0.01714 0.0147 0.1785 1.0000 14.250 1.5168 0.02342 0.01788 0.0160 0.1759 1.0000 14.500 1.5288 0.02409 0.01863 0.0172 0.1725 1.0000 14.750 1.5385 0.02493 0.01949 0.0185 0.1689 1.0000 15.000 1.5461 0.02601 0.02058 0.0198 0.1651 1.0000 15.250 1.5580 0.02685 0.02154 0.0206 0.1610 1.0000 15.500 1.5666 0.02797 0.02272 0.0216 0.1573 1.0000 15.750 1.5714 0.02944 0.02420 0.0226 0.1541 1.0000 16.000 1.5790 0.03079 0.02565 0.0233 0.1508 1.0000 16.250 1.5868 0.03220 0.02716 0.0238 0.1475 1.0000 16.500 1.5895 0.03407 0.02907 0.0243 0.1435 1.0000 16.750 1.5874 0.03645 0.03148 0.0247 0.1403 1.0000 17.000 1.5932 0.03827 0.03342 0.0247 0.1367 1.0000 17.250 1.5934 0.04069 0.03594 0.0247 0.1334 1.0000 17.500 1.5855 0.04406 0.03933 0.0243 0.1293 1.0000 17.750 1.5819 0.04710 0.04247 0.0238 0.1264 1.0000 18.000 1.5765 0.05045 0.04594 0.0231 0.1228 1.0000 18.250 1.5643 0.05470 0.05026 0.0219 0.1197 1.0000 18.500 1.5445 0.06002 0.05563 0.0203 0.1166 1.0000 18.750 1.5333 0.06449 0.06024 0.0188 0.1136 1.0000 19.000 1.5142 0.07011 0.06596 0.0167 0.1102 1.0000 19.250 1.4903 0.07644 0.07237 0.0143 0.1075 1.0000