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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4221 0.09866 0.09324 -0.0345 1.0000 0.0416 -11.000 -0.4959 0.07611 0.07067 -0.0488 1.0000 0.0405 -10.750 -0.5397 0.06523 0.05968 -0.0569 1.0000 0.0401 -10.500 -0.5789 0.05874 0.05304 -0.0596 1.0000 0.0399 -10.250 -0.6097 0.05479 0.04893 -0.0581 1.0000 0.0398 -10.000 -0.6401 0.05185 0.04583 -0.0537 1.0000 0.0398 -9.750 -0.6659 0.04875 0.04250 -0.0492 1.0000 0.0400 -9.500 -0.6863 0.04583 0.03930 -0.0445 1.0000 0.0402 -9.250 -0.7043 0.04297 0.03605 -0.0394 1.0000 0.0406 -9.000 -0.7023 0.04182 0.03488 -0.0362 1.0000 0.0412 -8.750 -0.6990 0.04080 0.03383 -0.0331 1.0000 0.0418 -8.500 -0.6963 0.03959 0.03251 -0.0299 1.0000 0.0426 -8.250 -0.6935 0.03817 0.03094 -0.0267 1.0000 0.0435 -8.000 -0.6835 0.03627 0.02875 -0.0248 0.9979 0.0448 -7.750 -0.6585 0.03350 0.02543 -0.0257 0.9913 0.0465 -7.500 -0.6298 0.03163 0.02331 -0.0268 0.9850 0.0478 -7.250 -0.5986 0.03046 0.02207 -0.0282 0.9790 0.0494 -7.000 -0.5671 0.02921 0.02062 -0.0294 0.9724 0.0521 -6.750 -0.5333 0.02782 0.01898 -0.0309 0.9653 0.0552 -6.500 -0.4947 0.02680 0.01795 -0.0333 0.9573 0.0581 -6.250 -0.4565 0.02560 0.01650 -0.0352 0.9477 0.0624 -6.000 -0.4118 0.02456 0.01553 -0.0386 0.9399 0.0667 -5.750 -0.3784 0.02369 0.01448 -0.0394 0.9279 0.0717 -5.500 -0.3457 0.02288 0.01375 -0.0404 0.9160 0.0765 -5.250 -0.3111 0.02213 0.01286 -0.0413 0.9041 0.0827 -5.000 -0.2803 0.02139 0.01220 -0.0417 0.8912 0.0884 -4.750 -0.2539 0.02080 0.01154 -0.0410 0.8765 0.0949 -4.500 -0.2288 0.02021 0.01101 -0.0403 0.8617 0.1011 -4.250 -0.2031 0.01966 0.01042 -0.0395 0.8462 0.1087 -4.000 -0.1783 0.01913 0.00992 -0.0386 0.8294 0.1170 -3.750 -0.1537 0.01860 0.00939 -0.0376 0.8115 0.1266 -3.500 -0.1289 0.01812 0.00890 -0.0366 0.7924 0.1390 -3.250 -0.1041 0.01763 0.00841 -0.0356 0.7720 0.1547 -3.000 -0.0801 0.01715 0.00795 -0.0345 0.7494 0.1758 -2.750 -0.0564 0.01669 0.00752 -0.0333 0.7249 0.2056 -2.500 -0.0337 0.01613 0.00709 -0.0321 0.6993 0.2553 -2.250 -0.0157 0.01531 0.00680 -0.0301 0.6717 0.3813 -2.000 0.0023 0.01469 0.00669 -0.0278 0.6434 0.5296 -1.750 0.0241 0.01446 0.00669 -0.0256 0.6138 0.6426 -1.500 0.0490 0.01445 0.00671 -0.0240 0.5831 0.7163 -1.250 0.0793 0.01463 0.00686 -0.0232 0.5506 0.7741 -1.000 0.1113 0.01496 0.00706 -0.0228 0.5171 0.8208 -0.750 0.1421 0.01533 0.00722 -0.0225 0.4859 0.8554 -0.500 0.1753 0.01573 0.00736 -0.0227 0.4596 0.8810 -0.250 0.2060 0.01613 0.00751 -0.0225 0.4397 0.9060 0.000 0.2491 0.01658 0.00769 -0.0248 0.4217 0.9247 0.250 0.2896 0.01689 0.00777 -0.0271 0.4072 0.9375 0.500 0.3293 0.01709 0.00778 -0.0294 0.3954 0.9447 0.750 0.3619 0.01732 0.00780 -0.0304 0.3866 0.9547 1.000 0.4025 0.01748 0.00783 -0.0331 0.3771 0.9612 1.250 0.4380 0.01771 0.00786 -0.0347 0.3695 0.9700 1.500 0.4782 0.01786 0.00791 -0.0374 0.3613 0.9776 1.750 0.5172 0.01807 0.00795 -0.0398 0.3549 0.9853 2.000 0.5559 0.01824 0.00803 -0.0423 0.3487 0.9927 2.250 0.5951 0.01839 0.00810 -0.0449 0.3424 0.9993 2.500 0.6164 0.01861 0.00820 -0.0440 0.3380 1.0000 2.750 0.6359 0.01884 0.00836 -0.0427 0.3338 1.0000 3.000 0.6554 0.01905 0.00857 -0.0413 0.3291 1.0000 3.250 0.6750 0.01930 0.00877 -0.0400 0.3250 1.0000 3.500 0.6949 0.01958 0.00897 -0.0387 0.3215 1.0000 3.750 0.7151 0.01991 0.00921 -0.0374 0.3183 1.0000 4.000 0.7347 0.02019 0.00953 -0.0361 0.3143 1.0000 4.250 0.7544 0.02050 0.00984 -0.0347 0.3103 1.0000 4.500 0.7743 0.02081 0.01012 -0.0334 0.3067 1.0000 4.750 0.7946 0.02116 0.01040 -0.0321 0.3036 1.0000 5.000 0.8150 0.02156 0.01076 -0.0309 0.3007 1.0000 5.250 0.8343 0.02194 0.01122 -0.0295 0.2974 1.0000 5.500 0.8539 0.02233 0.01164 -0.0281 0.2940 1.0000 5.750 0.8737 0.02271 0.01202 -0.0268 0.2907 1.0000 6.000 0.8940 0.02309 0.01236 -0.0255 0.2877 1.0000 6.250 0.9154 0.02354 0.01273 -0.0245 0.2852 1.0000 6.500 0.9335 0.02401 0.01334 -0.0229 0.2820 1.0000 6.750 0.9522 0.02451 0.01392 -0.0215 0.2789 1.0000 7.000 0.9714 0.02499 0.01444 -0.0202 0.2759 1.0000 7.250 0.9911 0.02543 0.01491 -0.0189 0.2730 1.0000 7.500 1.0121 0.02588 0.01532 -0.0179 0.2705 1.0000 7.750 1.0323 0.02640 0.01584 -0.0168 0.2679 1.0000 8.000 1.0484 0.02705 0.01667 -0.0151 0.2649 1.0000 8.250 1.0657 0.02768 0.01741 -0.0136 0.2620 1.0000 8.500 1.0838 0.02825 0.01806 -0.0122 0.2592 1.0000 8.750 1.1034 0.02875 0.01859 -0.0111 0.2565 1.0000 9.000 1.1247 0.02924 0.01907 -0.0102 0.2541 1.0000 9.250 1.1437 0.02989 0.01976 -0.0091 0.2518 1.0000 9.500 1.1559 0.03077 0.02086 -0.0071 0.2488 1.0000 9.750 1.1695 0.03158 0.02183 -0.0054 0.2458 1.0000 10.000 1.1849 0.03226 0.02262 -0.0039 0.2430 1.0000 10.250 1.2028 0.03285 0.02324 -0.0027 0.2406 1.0000 10.500 1.2236 0.03336 0.02375 -0.0019 0.2384 1.0000 10.750 1.2391 0.03417 0.02465 -0.0005 0.2361 1.0000 11.000 1.2413 0.03542 0.02616 0.0023 0.2331 1.0000 11.250 1.2463 0.03651 0.02743 0.0048 0.2302 1.0000 11.500 1.2535 0.03738 0.02841 0.0071 0.2275 1.0000 11.750 1.2648 0.03811 0.02921 0.0090 0.2253 1.0000 12.000 1.2833 0.03863 0.02972 0.0099 0.2233 1.0000 12.250 1.2929 0.03958 0.03074 0.0117 0.2212 1.0000 12.500 1.2708 0.04190 0.03336 0.0160 0.2184 1.0000 12.750 1.2539 0.04433 0.03601 0.0189 0.2157 1.0000 13.000 1.2444 0.04656 0.03839 0.0207 0.2131 1.0000 13.250 1.2460 0.04819 0.04011 0.0218 0.2108 1.0000 13.500 1.2652 0.04863 0.04057 0.0224 0.2087 1.0000 13.750 1.2736 0.04997 0.04195 0.0231 0.2067 1.0000 14.000 0.9881 0.08792 0.08046 0.0094 0.1932 1.0000