XFOIL Version 6.96 Calculated polar for: US1000ROOT 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.7853 0.16282 0.15870 0.0012 1.0000 0.0162 -19.250 -0.8015 0.15461 0.15035 -0.0036 1.0000 0.0159 -19.000 -0.8138 0.14769 0.14330 -0.0076 1.0000 0.0155 -18.750 -0.8295 0.14018 0.13564 -0.0119 1.0000 0.0152 -18.500 -0.8447 0.13301 0.12829 -0.0157 1.0000 0.0149 -18.250 -0.8585 0.12632 0.12142 -0.0192 1.0000 0.0145 -18.000 -0.8677 0.12069 0.11562 -0.0220 1.0000 0.0143 -17.750 -0.8788 0.11481 0.10952 -0.0247 1.0000 0.0138 -17.500 -0.8877 0.10941 0.10388 -0.0269 1.0000 0.0134 -17.250 -0.8880 0.10570 0.10003 -0.0281 1.0000 0.0133 -17.000 -0.8864 0.10227 0.09644 -0.0288 1.0000 0.0131 -16.750 -0.8824 0.09934 0.09336 -0.0292 1.0000 0.0128 -16.500 -0.8762 0.09695 0.09091 -0.0293 1.0000 0.0130 -16.250 -0.8681 0.09485 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0.9603 0.3241 -6.750 -0.7974 0.01806 0.01103 0.0070 0.9538 0.3300 -6.500 -0.7581 0.01771 0.01063 0.0046 0.9472 0.3369 -6.250 -0.7138 0.01724 0.01011 0.0011 0.9430 0.3439 -6.000 -0.6753 0.01690 0.00974 -0.0011 0.9349 0.3504 -5.750 -0.6264 0.01643 0.00919 -0.0055 0.9302 0.3575 -5.500 -0.5812 0.01605 0.00882 -0.0091 0.9226 0.3642 -5.250 -0.5313 0.01563 0.00832 -0.0138 0.9155 0.3718 -5.000 -0.4883 0.01533 0.00802 -0.0169 0.9046 0.3789 -4.750 -0.4484 0.01506 0.00767 -0.0195 0.8926 0.3863 -4.500 -0.4129 0.01486 0.00747 -0.0210 0.8792 0.3934 -4.250 -0.3840 0.01471 0.00724 -0.0212 0.8650 0.4011 -4.000 -0.3573 0.01457 0.00710 -0.0209 0.8505 0.4085 -3.750 -0.3330 0.01442 0.00690 -0.0200 0.8358 0.4161 -3.500 -0.3093 0.01427 0.00673 -0.0190 0.8210 0.4238 -3.250 -0.2864 0.01409 0.00654 -0.0178 0.8061 0.4320 -3.000 -0.2646 0.01395 0.00636 -0.0163 0.7907 0.4414 -2.750 -0.2417 0.01376 0.00619 -0.0151 0.7751 0.4501 -2.500 -0.2199 0.01360 0.00598 -0.0137 0.7587 0.4603 -2.250 -0.1974 0.01344 0.00580 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2.750 0.2399 0.01375 0.00619 0.0155 0.4502 0.7749 3.000 0.2627 0.01395 0.00637 0.0168 0.4415 0.7907 3.250 0.2845 0.01409 0.00655 0.0182 0.4321 0.8061 3.500 0.3073 0.01426 0.00675 0.0194 0.4239 0.8212 3.750 0.3310 0.01441 0.00691 0.0205 0.4162 0.8361 4.000 0.3553 0.01456 0.00711 0.0213 0.4085 0.8506 4.250 0.3821 0.01470 0.00725 0.0216 0.4012 0.8653 4.500 0.4112 0.01485 0.00748 0.0214 0.3934 0.8794 4.750 0.4470 0.01505 0.00768 0.0198 0.3863 0.8927 5.000 0.4874 0.01532 0.00804 0.0172 0.3790 0.9047 5.250 0.5292 0.01553 0.00822 0.0142 0.3684 0.9158 5.500 0.5757 0.01574 0.00841 0.0103 0.3552 0.9236 5.750 0.6194 0.01592 0.00866 0.0069 0.3425 0.9313 6.000 0.6654 0.01625 0.00906 0.0031 0.3325 0.9370 6.250 0.7032 0.01650 0.00931 0.0010 0.3206 0.9449 6.500 0.7426 0.01670 0.00953 -0.0015 0.3037 0.9510 6.750 0.7783 0.01697 0.00981 -0.0034 0.2897 0.9593 7.000 0.8175 0.01732 0.01017 -0.0059 0.2793 0.9664 7.250 0.8537 0.01758 0.01049 -0.0080 0.2599 0.9748 7.500 0.8866 0.01804 0.01079 -0.0098 0.2235 0.9845 7.750 0.9065 0.01996 0.01192 -0.0108 0.1094 0.9951 8.000 0.8872 0.02204 0.01350 -0.0050 0.0254 1.0000 8.250 0.8780 0.02192 0.01345 0.0011 0.0297 1.0000 8.500 0.8560 0.02254 0.01405 0.0093 0.0208 1.0000 8.750 0.8497 0.02329 0.01484 0.0146 0.0179 1.0000 9.000 0.8510 0.02401 0.01564 0.0185 0.0166 1.0000 9.250 0.8545 0.02479 0.01651 0.0217 0.0161 1.0000 9.500 0.8575 0.02574 0.01755 0.0246 0.0157 1.0000 9.750 0.8595 0.02691 0.01882 0.0272 0.0150 1.0000 10.000 0.8610 0.02826 0.02028 0.0295 0.0144 1.0000 10.250 0.8618 0.02980 0.02194 0.0315 0.0140 1.0000 10.500 0.8627 0.03150 0.02378 0.0330 0.0140 1.0000 10.750 0.8628 0.03342 0.02580 0.0343 0.0138 1.0000 11.000 0.8592 0.03584 0.02835 0.0352 0.0136 1.0000 11.250 0.8547 0.03858 0.03121 0.0356 0.0134 1.0000 11.500 0.8435 0.04223 0.03500 0.0356 0.0131 1.0000 11.750 0.8385 0.04546 0.03835 0.0352 0.0131 1.0000 12.000 0.8324 0.04899 0.04198 0.0346 0.0131 1.0000 12.250 0.8253 0.05274 0.04585 0.0337 0.0131 1.0000 12.500 0.8165 0.05680 0.05000 0.0327 0.0131 1.0000 12.750 0.8032 0.06144 0.05472 0.0316 0.0128 1.0000 13.000 0.8002 0.06491 0.05825 0.0307 0.0129 1.0000 13.250 0.7972 0.06835 0.06176 0.0299 0.0130 1.0000 13.500 0.7940 0.07173 0.06516 0.0293 0.0129 1.0000 13.750 0.7945 0.07452 0.06795 0.0291 0.0127 1.0000 14.000 0.7991 0.07684 0.07028 0.0290 0.0128 1.0000 14.250 0.8052 0.07909 0.07258 0.0287 0.0129 1.0000 14.500 0.8142 0.08059 0.07407 0.0294 0.0128 1.0000 14.750 0.8251 0.08197 0.07546 0.0301 0.0129 1.0000 15.000 0.8358 0.08345 0.07698 0.0306 0.0129 1.0000 15.250 0.8492 0.08447 0.07801 0.0317 0.0129 1.0000 15.500 0.8578 0.08654 0.08017 0.0315 0.0132 1.0000 15.750 0.8699 0.08796 0.08166 0.0324 0.0134 1.0000 16.000 0.8790 0.08997 0.08378 0.0327 0.0136 1.0000 16.250 0.8856 0.09247 0.08642 0.0329 0.0140 1.0000 16.500 0.8882 0.09564 0.08976 0.0326 0.0144 1.0000 16.750 0.8887 0.09911 0.09335 0.0314 0.0146 1.0000 17.000 0.8862 0.10323 0.09765 0.0303 0.0150 1.0000 17.250 0.8820 0.10762 0.10219 0.0287 0.0153 1.0000 17.500 0.8754 0.11251 0.10724 0.0268 0.0157 1.0000 17.750 0.8666 0.11785 0.11274 0.0244 0.0160 1.0000 18.000 0.8579 0.12327 0.11830 0.0219 0.0163 1.0000 18.250 0.8481 0.12899 0.12416 0.0191 0.0167 1.0000 18.500 0.8376 0.13500 0.13030 0.0160 0.0169 1.0000 18.750 0.8511 0.13662 0.13194 0.0167 0.0179 1.0000 19.000 0.8394 0.14306 0.13853 0.0123 0.0182 1.0000 19.250 0.8166 0.15256 0.14827 0.0059 0.0188 1.0000