XFOIL Version 6.96 Calculated polar for: AUGUST 160 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.1515 0.09086 0.08546 -0.0504 0.4960 0.0322 -9.250 -0.1506 0.08733 0.08192 -0.0520 0.4911 0.0322 -8.750 -0.1870 0.07110 0.06576 -0.0603 0.4902 0.0197 -8.500 -0.1951 0.06656 0.06124 -0.0636 0.4869 0.0195 -8.250 -0.2019 0.06314 0.05781 -0.0650 0.4827 0.0192 -8.000 -0.2189 0.05893 0.05355 -0.0648 0.4796 0.0190 -7.750 -0.2314 0.05405 0.04853 -0.0647 0.4766 0.0190 -7.500 -0.2369 0.05004 0.04435 -0.0637 0.4728 0.0186 -7.250 -0.2485 0.04408 0.03801 -0.0618 0.4707 0.0192 -7.000 -0.2487 0.04009 0.03367 -0.0597 0.4670 0.0192 -6.750 -0.2458 0.03634 0.02951 -0.0572 0.4625 0.0192 -6.500 -0.2370 0.03343 0.02620 -0.0549 0.4578 0.0191 -6.250 -0.2244 0.03104 0.02342 -0.0529 0.4528 0.0189 -6.000 -0.2094 0.02882 0.02080 -0.0509 0.4482 0.0189 -5.750 -0.1915 0.02691 0.01852 -0.0492 0.4431 0.0189 -5.500 -0.1712 0.02541 0.01668 -0.0478 0.4378 0.0189 -5.250 -0.1498 0.02402 0.01495 -0.0464 0.4332 0.0191 -5.000 -0.1266 0.02289 0.01355 -0.0453 0.4285 0.0192 -4.750 -0.1025 0.02185 0.01226 -0.0443 0.4233 0.0195 -4.500 -0.0779 0.02105 0.01127 -0.0435 0.4183 0.0197 -4.250 -0.0537 0.02030 0.01042 -0.0426 0.4141 0.0201 -4.000 -0.0291 0.01970 0.00975 -0.0419 0.4099 0.0205 -3.750 -0.0042 0.01916 0.00916 -0.0411 0.4056 0.0209 -3.500 0.0206 0.01873 0.00866 -0.0404 0.4015 0.0219 -3.250 0.0454 0.01836 0.00817 -0.0396 0.3978 0.0231 -3.000 0.0693 0.01797 0.00773 -0.0387 0.3946 0.0241 -2.750 0.0939 0.01761 0.00736 -0.0379 0.3914 0.0248 -2.500 0.1187 0.01730 0.00701 -0.0371 0.3880 0.0256 -2.250 0.1435 0.01703 0.00667 -0.0363 0.3847 0.0266 -2.000 0.1683 0.01681 0.00639 -0.0355 0.3816 0.0278 -1.750 0.1932 0.01664 0.00615 -0.0348 0.3789 0.0296 -1.500 0.2181 0.01650 0.00593 -0.0340 0.3764 0.0328 -1.250 0.2434 0.01632 0.00577 -0.0333 0.3738 0.0396 -1.000 0.2670 0.01597 0.00561 -0.0325 0.3710 0.0768 -0.750 0.2899 0.01562 0.00554 -0.0316 0.3683 0.1588 -0.500 0.3090 0.01497 0.00549 -0.0302 0.3658 0.3197 -0.250 0.3192 0.01395 0.00547 -0.0268 0.3636 0.5918 0.000 0.3917 0.01389 0.00620 -0.0337 0.3600 0.9304 0.250 0.4337 0.01418 0.00632 -0.0362 0.3575 0.9484 0.500 0.4808 0.01441 0.00644 -0.0398 0.3550 0.9607 0.750 0.5304 0.01463 0.00654 -0.0439 0.3523 0.9723 1.000 0.5804 0.01480 0.00660 -0.0484 0.3498 0.9819 1.250 0.6271 0.01492 0.00660 -0.0522 0.3473 0.9894 1.500 0.6687 0.01504 0.00661 -0.0551 0.3453 0.9951 1.750 0.7098 0.01516 0.00661 -0.0580 0.3434 1.0000 2.000 0.7320 0.01534 0.00670 -0.0570 0.3419 1.0000 2.250 0.7541 0.01553 0.00684 -0.0561 0.3405 1.0000 2.500 0.7761 0.01570 0.00700 -0.0551 0.3390 1.0000 2.750 0.7980 0.01588 0.00719 -0.0540 0.3374 1.0000 3.000 0.8198 0.01608 0.00738 -0.0530 0.3359 1.0000 3.250 0.8415 0.01629 0.00757 -0.0520 0.3344 1.0000 3.500 0.8630 0.01650 0.00777 -0.0509 0.3329 1.0000 3.750 0.8845 0.01671 0.00796 -0.0498 0.3313 1.0000 4.000 0.9058 0.01692 0.00814 -0.0487 0.3297 1.0000 4.250 0.9271 0.01715 0.00834 -0.0476 0.3283 1.0000 4.500 0.9484 0.01739 0.00856 -0.0465 0.3271 1.0000 4.750 0.9697 0.01767 0.00880 -0.0455 0.3260 1.0000 5.000 0.9912 0.01799 0.00907 -0.0445 0.3249 1.0000 5.250 1.0119 0.01830 0.00940 -0.0433 0.3238 1.0000 5.500 1.0318 0.01861 0.00978 -0.0421 0.3227 1.0000 5.750 1.0514 0.01892 0.01014 -0.0408 0.3214 1.0000 6.000 1.0708 0.01923 0.01050 -0.0394 0.3199 1.0000 6.250 1.0903 0.01956 0.01087 -0.0381 0.3185 1.0000 6.500 1.1098 0.01990 0.01126 -0.0369 0.3172 1.0000 6.750 1.1294 0.02024 0.01163 -0.0356 0.3160 1.0000 7.000 1.1490 0.02056 0.01198 -0.0344 0.3146 1.0000 7.250 1.1688 0.02090 0.01234 -0.0332 0.3134 1.0000 7.500 1.1889 0.02123 0.01270 -0.0321 0.3123 1.0000 7.750 1.2091 0.02157 0.01305 -0.0311 0.3111 1.0000 8.000 1.2296 0.02195 0.01345 -0.0301 0.3102 1.0000 8.250 1.2506 0.02236 0.01388 -0.0292 0.3092 1.0000 8.500 1.2722 0.02282 0.01434 -0.0285 0.3083 1.0000 8.750 1.2900 0.02334 0.01494 -0.0272 0.3074 1.0000 9.000 1.3057 0.02389 0.01562 -0.0257 0.3063 1.0000 9.250 1.3210 0.02447 0.01633 -0.0241 0.3052 1.0000 9.500 1.3360 0.02508 0.01705 -0.0226 0.3041 1.0000 9.750 1.3506 0.02571 0.01779 -0.0210 0.3029 1.0000 10.000 1.3647 0.02635 0.01853 -0.0194 0.3016 1.0000 10.250 1.3785 0.02696 0.01925 -0.0178 0.3003 1.0000 10.500 1.3926 0.02751 0.01987 -0.0163 0.2988 1.0000 10.750 1.4073 0.02802 0.02045 -0.0148 0.2974 1.0000 11.000 1.4232 0.02838 0.02085 -0.0134 0.2958 1.0000 11.250 1.4400 0.02873 0.02122 -0.0122 0.2944 1.0000 11.500 1.4585 0.02911 0.02162 -0.0112 0.2931 1.0000 11.750 1.4642 0.02982 0.02241 -0.0088 0.2912 1.0000 12.000 1.4530 0.03127 0.02407 -0.0050 0.2893 1.0000 12.250 1.4421 0.03302 0.02599 -0.0023 0.2869 1.0000 12.500 1.4357 0.03495 0.02807 -0.0007 0.2848 1.0000 12.750 1.4358 0.03661 0.02982 0.0001 0.2825 1.0000 13.000 1.4517 0.03708 0.03032 0.0005 0.2802 1.0000 13.250 1.4711 0.03739 0.03063 0.0007 0.2784 1.0000 13.500 1.4755 0.03901 0.03234 0.0011 0.2765 1.0000 14.000 1.2347 0.07121 0.06514 -0.0058 0.2624 1.0000 14.250 1.2880 0.06708 0.06101 -0.0045 0.2626 1.0000