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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.250 -0.6841 0.06745 0.06296 -0.0555 1.0000 0.0254 -13.000 -0.7281 0.05663 0.05186 -0.0640 1.0000 0.0252 -12.750 -0.7615 0.04986 0.04481 -0.0679 1.0000 0.0253 -12.500 -0.7825 0.04562 0.04034 -0.0685 1.0000 0.0253 -12.250 -0.8014 0.04221 0.03667 -0.0675 1.0000 0.0254 -12.000 -0.8137 0.03969 0.03394 -0.0653 1.0000 0.0255 -11.750 -0.8172 0.03807 0.03226 -0.0627 1.0000 0.0257 -11.500 -0.8200 0.03677 0.03088 -0.0595 1.0000 0.0259 -11.250 -0.8224 0.03572 0.02978 -0.0559 1.0000 0.0261 -11.000 -0.8217 0.03465 0.02865 -0.0525 1.0000 0.0264 -10.750 -0.8203 0.03361 0.02751 -0.0491 1.0000 0.0267 -10.500 -0.8182 0.03272 0.02655 -0.0456 1.0000 0.0271 -10.250 -0.8175 0.03171 0.02543 -0.0418 1.0000 0.0274 -10.000 -0.8162 0.03076 0.02435 -0.0379 1.0000 0.0279 -9.750 -0.8023 0.02942 0.02281 -0.0365 0.9976 0.0286 -9.500 -0.7747 0.02776 0.02088 -0.0376 0.9919 0.0293 -9.250 -0.7478 0.02635 0.01925 -0.0382 0.9866 0.0300 -9.000 -0.7177 0.02539 0.01827 -0.0395 0.9826 0.0307 -8.750 -0.6898 0.02452 0.01735 -0.0400 0.9772 0.0315 -8.500 -0.6600 0.02362 0.01635 -0.0409 0.9727 0.0325 -8.250 -0.6273 0.02265 0.01525 -0.0423 0.9694 0.0337 -8.000 -0.5972 0.02177 0.01425 -0.0430 0.9627 0.0352 -7.750 -0.5607 0.02106 0.01354 -0.0449 0.9565 0.0368 -7.500 -0.5290 0.02040 0.01282 -0.0458 0.9473 0.0386 -7.250 -0.4940 0.01960 0.01189 -0.0472 0.9401 0.0408 -7.000 -0.4676 0.01901 0.01131 -0.0470 0.9291 0.0425 -6.750 -0.4388 0.01847 0.01072 -0.0471 0.9194 0.0448 -6.500 -0.4109 0.01792 0.01009 -0.0470 0.9086 0.0476 -6.250 -0.3868 0.01750 0.00968 -0.0461 0.8960 0.0504 -6.000 -0.3618 0.01708 0.00917 -0.0453 0.8829 0.0537 -5.750 -0.3379 0.01661 0.00869 -0.0444 0.8687 0.0566 -5.500 -0.3136 0.01625 0.00828 -0.0434 0.8533 0.0602 -5.250 -0.2897 0.01586 0.00782 -0.0424 0.8372 0.0639 -5.000 -0.2658 0.01552 0.00746 -0.0414 0.8198 0.0681 -4.750 -0.2415 0.01521 0.00707 -0.0404 0.8006 0.0726 -4.500 -0.2177 0.01488 0.00671 -0.0394 0.7798 0.0775 -4.000 -0.1697 0.01434 0.00600 -0.0373 0.7318 0.0888 -3.750 -0.1457 0.01414 0.00567 -0.0362 0.7054 0.0953 -3.500 -0.1223 0.01393 0.00539 -0.0351 0.6784 0.1035 -3.250 -0.0990 0.01376 0.00513 -0.0340 0.6505 0.1133 -3.000 -0.0758 0.01363 0.00489 -0.0329 0.6213 0.1258 -2.750 -0.0530 0.01351 0.00468 -0.0318 0.5928 0.1421 -2.500 -0.0302 0.01340 0.00451 -0.0307 0.5642 0.1626 -2.250 -0.0074 0.01327 0.00434 -0.0296 0.5348 0.1886 -2.000 0.0144 0.01310 0.00418 -0.0284 0.5025 0.2266 -1.750 0.0341 0.01278 0.00401 -0.0270 0.4689 0.2986 -1.250 0.0690 0.01206 0.00388 -0.0231 0.4193 0.5255 -1.000 0.0883 0.01188 0.00394 -0.0211 0.4025 0.6139 -0.500 0.1332 0.01180 0.00411 -0.0181 0.3784 0.7402 -0.250 0.1592 0.01188 0.00430 -0.0171 0.3693 0.7947 0.000 0.1879 0.01206 0.00449 -0.0167 0.3606 0.8354 0.250 0.2172 0.01231 0.00466 -0.0164 0.3529 0.8633 0.500 0.2455 0.01250 0.00480 -0.0161 0.3456 0.8867 0.750 0.2752 0.01276 0.00497 -0.0160 0.3389 0.9073 1.000 0.3081 0.01302 0.00515 -0.0166 0.3332 0.9247 1.250 0.3429 0.01323 0.00529 -0.0178 0.3275 0.9349 1.500 0.3751 0.01343 0.00538 -0.0186 0.3222 0.9421 1.750 0.4099 0.01365 0.00549 -0.0200 0.3174 0.9481 2.000 0.4420 0.01381 0.00560 -0.0208 0.3122 0.9555 2.250 0.4822 0.01401 0.00572 -0.0233 0.3070 0.9598 2.500 0.5173 0.01425 0.00585 -0.0247 0.3030 0.9671 2.750 0.5559 0.01444 0.00599 -0.0270 0.2990 0.9718 3.000 0.5927 0.01460 0.00612 -0.0289 0.2948 0.9766 3.250 0.6259 0.01479 0.00625 -0.0301 0.2907 0.9821 3.500 0.6624 0.01499 0.00636 -0.0320 0.2867 0.9857 3.750 0.6967 0.01518 0.00652 -0.0335 0.2833 0.9899 4.000 0.7305 0.01535 0.00669 -0.0349 0.2799 0.9938 4.250 0.7655 0.01552 0.00684 -0.0366 0.2765 0.9975 4.500 0.7958 0.01572 0.00701 -0.0373 0.2733 1.0000 4.750 0.8150 0.01594 0.00718 -0.0358 0.2706 1.0000 5.000 0.8342 0.01618 0.00738 -0.0343 0.2680 1.0000 5.250 0.8539 0.01636 0.00761 -0.0328 0.2652 1.0000 5.500 0.8734 0.01657 0.00784 -0.0314 0.2626 1.0000 5.750 0.8927 0.01680 0.00807 -0.0298 0.2601 1.0000 6.000 0.9117 0.01703 0.00830 -0.0283 0.2577 1.0000 6.250 0.9306 0.01729 0.00854 -0.0267 0.2553 1.0000 6.500 0.9495 0.01760 0.00879 -0.0252 0.2529 1.0000 6.750 0.9686 0.01784 0.00909 -0.0236 0.2504 1.0000 7.000 0.9877 0.01809 0.00940 -0.0221 0.2479 1.0000 7.250 1.0070 0.01837 0.00971 -0.0206 0.2455 1.0000 7.500 1.0262 0.01865 0.01001 -0.0192 0.2432 1.0000 7.750 1.0452 0.01893 0.01031 -0.0177 0.2409 1.0000 8.000 1.0642 0.01925 0.01060 -0.0162 0.2386 1.0000 8.250 1.0836 0.01960 0.01095 -0.0149 0.2364 1.0000 8.500 1.1026 0.01992 0.01135 -0.0135 0.2340 1.0000 8.750 1.1219 0.02026 0.01177 -0.0121 0.2317 1.0000 9.000 1.1408 0.02059 0.01216 -0.0107 0.2292 1.0000 9.250 1.1595 0.02092 0.01252 -0.0093 0.2268 1.0000 9.500 1.1782 0.02126 0.01288 -0.0080 0.2245 1.0000 9.750 1.1975 0.02167 0.01326 -0.0068 0.2225 1.0000 10.000 1.2158 0.02209 0.01377 -0.0054 0.2203 1.0000 10.250 1.2332 0.02250 0.01429 -0.0039 0.2178 1.0000 10.500 1.2500 0.02290 0.01479 -0.0024 0.2152 1.0000 10.750 1.2658 0.02330 0.01525 -0.0007 0.2128 1.0000 11.000 1.2807 0.02371 0.01570 0.0011 0.2107 1.0000 11.250 1.2959 0.02415 0.01614 0.0029 0.2086 1.0000 11.500 1.3108 0.02466 0.01669 0.0045 0.2065 1.0000 11.750 1.3230 0.02521 0.01739 0.0065 0.2040 1.0000 12.000 1.3355 0.02578 0.01808 0.0083 0.2015 1.0000 12.250 1.3480 0.02637 0.01876 0.0100 0.1991 1.0000 12.500 1.3600 0.02695 0.01941 0.0117 0.1967 1.0000 12.750 1.3726 0.02756 0.02003 0.0133 0.1945 1.0000 13.000 1.3849 0.02828 0.02079 0.0147 0.1924 1.0000 13.250 1.3934 0.02917 0.02186 0.0164 0.1898 1.0000 13.500 1.4018 0.03009 0.02292 0.0179 0.1872 1.0000 13.750 1.4101 0.03104 0.02397 0.0194 0.1846 1.0000 14.000 1.4185 0.03201 0.02500 0.0207 0.1823 1.0000 14.250 1.4276 0.03298 0.02599 0.0219 0.1800 1.0000 14.500 1.4333 0.03428 0.02741 0.0230 0.1776 1.0000 14.750 1.4362 0.03584 0.02915 0.0241 0.1749 1.0000 15.000 1.4388 0.03747 0.03092 0.0250 0.1721 1.0000 15.250 1.4416 0.03915 0.03269 0.0257 0.1695 1.0000 15.500 1.4454 0.04080 0.03437 0.0262 0.1670 1.0000 15.750 1.4456 0.04292 0.03659 0.0266 0.1645 1.0000 16.000 1.4403 0.04574 0.03961 0.0265 0.1615 1.0000 16.250 1.4345 0.04872 0.04273 0.0263 0.1585 1.0000 16.500 1.4303 0.05164 0.04573 0.0258 0.1556 1.0000 16.750 1.4293 0.05426 0.04835 0.0253 0.1529 1.0000 17.000 1.4110 0.05931 0.05363 0.0237 0.1499 1.0000 17.250 1.3902 0.06496 0.05946 0.0215 0.1466 1.0000 17.500 1.3729 0.07033 0.06494 0.0193 0.1436 1.0000 17.750 1.3695 0.07377 0.06836 0.0180 0.1403 1.0000 18.000 1.3237 0.08394 0.07878 0.0133 0.1372 1.0000 18.250 1.2665 0.09631 0.09137 0.0073 0.1335 1.0000 18.500 1.2609 0.10049 0.09555 0.0054 0.1300 1.0000 18.750 1.2353 0.10808 0.10322 0.0017 0.1264 1.0000 19.000 1.1461 0.12715 0.12247 -0.0081 0.1194 1.0000 19.250 1.1817 0.12427 0.11957 -0.0065 0.1176 1.0000