XFOIL Version 6.96 Calculated polar for: Dayton-Wright T-1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.7493 0.05931 0.05621 -0.0860 1.0000 0.0262 -15.250 -0.8146 0.03916 0.03555 -0.1115 0.9920 0.0260 -15.000 -0.8123 0.03535 0.03148 -0.1148 0.9849 0.0262 -14.750 -0.8030 0.03282 0.02874 -0.1159 0.9788 0.0264 -14.500 -0.7888 0.03080 0.02653 -0.1165 0.9734 0.0266 -14.250 -0.7711 0.02912 0.02467 -0.1169 0.9692 0.0269 -14.000 -0.7554 0.02775 0.02312 -0.1163 0.9628 0.0272 -13.750 -0.7356 0.02643 0.02163 -0.1162 0.9586 0.0275 -13.500 -0.7174 0.02528 0.02031 -0.1154 0.9531 0.0276 -13.250 -0.6983 0.02424 0.01912 -0.1146 0.9474 0.0278 -13.000 -0.6767 0.02328 0.01800 -0.1140 0.9432 0.0280 -12.750 -0.6571 0.02235 0.01694 -0.1130 0.9378 0.0281 -12.500 -0.6384 0.02122 0.01570 -0.1119 0.9320 0.0284 -12.250 -0.6167 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0.3887 0.00942 0.00225 -0.0909 0.6087 0.2308 -2.250 0.4143 0.00945 0.00226 -0.0904 0.5952 0.2486 -2.000 0.4402 0.00948 0.00228 -0.0900 0.5812 0.2639 -1.750 0.4660 0.00953 0.00232 -0.0895 0.5679 0.2792 -1.500 0.4917 0.00958 0.00236 -0.0891 0.5554 0.2949 -1.250 0.5172 0.00964 0.00240 -0.0886 0.5424 0.3091 -1.000 0.5428 0.00971 0.00245 -0.0882 0.5289 0.3238 -0.750 0.5681 0.00977 0.00252 -0.0877 0.5151 0.3431 -0.500 0.5932 0.00984 0.00259 -0.0872 0.5009 0.3626 -0.250 0.6181 0.00993 0.00266 -0.0867 0.4863 0.3804 0.000 0.6427 0.01003 0.00275 -0.0861 0.4706 0.3994 0.250 0.6668 0.01013 0.00284 -0.0855 0.4538 0.4241 0.500 0.6901 0.01018 0.00294 -0.0848 0.4359 0.4669 0.750 0.7007 0.00930 0.00314 -0.0812 0.4209 0.8611 1.000 0.7406 0.00952 0.00343 -0.0837 0.4009 0.9458 1.250 0.7804 0.00983 0.00364 -0.0866 0.3826 0.9742 1.500 0.8150 0.01012 0.00383 -0.0883 0.3667 0.9865 1.750 0.8500 0.01040 0.00402 -0.0902 0.3523 0.9944 2.000 0.8863 0.01068 0.00421 -0.0924 0.3394 0.9993 2.500 0.9285 0.01110 0.00453 -0.0901 0.3206 1.0000 2.750 0.9474 0.01133 0.00470 -0.0885 0.3125 1.0000 3.000 0.9674 0.01151 0.00486 -0.0872 0.3057 1.0000 3.250 0.9867 0.01173 0.00504 -0.0856 0.2988 1.0000 3.500 1.0061 0.01194 0.00523 -0.0842 0.2931 1.0000 3.750 1.0261 0.01215 0.00542 -0.0829 0.2866 1.0000 4.250 1.0650 0.01264 0.00585 -0.0801 0.2724 1.0000 4.500 1.0837 0.01290 0.00608 -0.0786 0.2662 1.0000 4.750 1.1020 0.01316 0.00633 -0.0770 0.2620 1.0000 5.000 1.1221 0.01337 0.00656 -0.0758 0.2580 1.0000 5.250 1.1417 0.01362 0.00682 -0.0746 0.2534 1.0000 5.500 1.1609 0.01392 0.00710 -0.0733 0.2493 1.0000 5.750 1.1802 0.01423 0.00741 -0.0721 0.2455 1.0000 6.000 1.2011 0.01449 0.00770 -0.0712 0.2421 1.0000 6.250 1.2213 0.01479 0.00802 -0.0703 0.2379 1.0000 6.500 1.2403 0.01515 0.00838 -0.0692 0.2334 1.0000 6.750 1.2593 0.01553 0.00876 -0.0681 0.2291 1.0000 7.000 1.2798 0.01584 0.00910 -0.0673 0.2241 1.0000 7.250 1.2982 0.01626 0.00951 -0.0662 0.2179 1.0000 7.500 1.3165 0.01669 0.00995 -0.0652 0.2128 1.0000 7.750 1.3363 0.01706 0.01036 -0.0644 0.2079 1.0000 8.000 1.3539 0.01755 0.01085 -0.0633 0.2015 1.0000 8.250 1.3719 0.01803 0.01134 -0.0624 0.1949 1.0000 8.500 1.3891 0.01856 0.01187 -0.0613 0.1869 1.0000 8.750 1.4060 0.01912 0.01244 -0.0603 0.1788 1.0000 9.000 1.4206 0.01983 0.01311 -0.0590 0.1648 1.0000 9.250 1.4286 0.02096 0.01408 -0.0570 0.1383 1.0000 9.500 1.4337 0.02232 0.01530 -0.0548 0.1168 1.0000 9.750 1.4407 0.02360 0.01652 -0.0529 0.1036 1.0000 10.250 1.4580 0.02603 0.01893 -0.0497 0.0861 1.0000 10.500 1.4659 0.02734 0.02023 -0.0482 0.0787 1.0000 10.750 1.4725 0.02878 0.02166 -0.0467 0.0709 1.0000 11.000 1.4795 0.03023 0.02311 -0.0454 0.0622 1.0000 11.250 1.4823 0.03205 0.02489 -0.0438 0.0503 1.0000 11.500 1.4787 0.03446 0.02723 -0.0420 0.0359 1.0000 11.750 1.4754 0.03698 0.02973 -0.0404 0.0270 1.0000 12.000 1.4753 0.03932 0.03210 -0.0392 0.0227 1.0000 12.250 1.4762 0.04167 0.03451 -0.0383 0.0202 1.0000 12.500 1.4785 0.04398 0.03689 -0.0376 0.0188 1.0000 12.750 1.4795 0.04649 0.03947 -0.0370 0.0176 1.0000 13.000 1.4792 0.04923 0.04230 -0.0366 0.0167 1.0000 13.250 1.4800 0.05194 0.04510 -0.0364 0.0160 1.0000 13.500 1.4797 0.05485 0.04810 -0.0362 0.0155 1.0000 13.750 1.4780 0.05802 0.05136 -0.0362 0.0150 1.0000 14.000 1.4747 0.06143 0.05487 -0.0364 0.0145 1.0000 14.250 1.4698 0.06514 0.05868 -0.0366 0.0141 1.0000 14.500 1.4632 0.06917 0.06282 -0.0371 0.0138 1.0000 14.750 1.4547 0.07354 0.06730 -0.0377 0.0135 1.0000 15.000 1.4470 0.07788 0.07174 -0.0384 0.0133 1.0000 15.250 1.4395 0.08228 0.07626 -0.0392 0.0131 1.0000 15.500 1.4308 0.08693 0.08103 -0.0402 0.0130 1.0000 15.750 1.4209 0.09181 0.08603 -0.0414 0.0128 1.0000 16.000 1.4103 0.09685 0.09119 -0.0427 0.0126 1.0000 16.250 1.3995 0.10200 0.09645 -0.0441 0.0124 1.0000 16.500 1.3888 0.10721 0.10177 -0.0456 0.0123 1.0000