XFOIL Version 6.94 Calculated polar for: FX 75-193 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 1.000 0.5910 0.01740 0.01251 -0.1168 0.7181 0.7012 1.500 0.6292 0.01759 0.01278 -0.1141 0.7098 0.7058 2.000 0.6880 0.01710 0.01227 -0.1152 0.7049 0.7101 2.500 0.7550 0.01624 0.01140 -0.1177 0.7010 0.7144 3.000 0.8240 0.01546 0.01057 -0.1206 0.6966 0.7185 3.500 0.8806 0.01496 0.01005 -0.1210 0.6855 0.7211 4.000 0.9367 0.01318 0.00811 -0.1210 0.6600 0.7254 4.500 0.9724 0.01292 0.00773 -0.1171 0.6288 0.7292 5.000 1.0048 0.01308 0.00798 -0.1131 0.6145 0.7333 5.500 0.9954 0.01417 0.00861 -0.1016 0.5394 0.7374 6.000 1.0197 0.01515 0.00955 -0.0975 0.5166 0.7410 6.500 0.9868 0.01882 0.01278 -0.0862 0.4352 0.7448 7.500 0.8988 0.02858 0.02085 -0.0636 0.1471 0.7482 8.000 0.9214 0.03056 0.02269 -0.0609 0.1105 0.7494 9.000 0.9461 0.03579 0.02753 -0.0540 0.0137 0.7524 9.500 0.9695 0.03792 0.02977 -0.0517 0.0113 0.7542 10.000 0.9975 0.03982 0.03172 -0.0501 0.0110 0.7555 10.500 1.0225 0.04207 0.03414 -0.0483 0.0113 0.7564 11.000 1.0412 0.04490 0.03716 -0.0462 0.0105 0.7578 11.500 1.0596 0.04791 0.04031 -0.0444 0.0098 0.7584 12.000 1.0720 0.05156 0.04413 -0.0422 0.0110 0.7587 12.500 1.0975 0.05406 0.04669 -0.0415 0.0111 0.7591 13.000 1.1066 0.05828 0.05110 -0.0396 0.0111 0.7605 13.500 1.1289 0.06127 0.05410 -0.0393 0.0082 0.7604 14.000 1.1132 0.06837 0.06153 -0.0369 0.0098 0.7598 14.500 1.1431 0.07096 0.06417 -0.0373 0.0082 0.7597 15.000 1.1659 0.07414 0.06741 -0.0375 0.0075 0.7595 15.500 1.1487 0.08121 0.07482 -0.0348 0.0100 0.7589 16.000 1.1640 0.08557 0.07930 -0.0357 0.0088 0.7587 16.500 1.1785 0.08936 0.08326 -0.0348 0.0103 0.7583 17.000 1.1885 0.09497 0.08898 -0.0372 0.0076 0.7583 17.500 1.1961 0.09961 0.09388 -0.0365 0.0086 0.7580 18.000 1.2064 0.10543 0.09972 -0.0397 0.0067 0.7576 18.500 1.2075 0.11049 0.10522 -0.0384 0.0082 0.7576 19.000 1.2113 0.11634 0.11130 -0.0401 0.0084 0.7571 19.500 1.2126 0.12307 0.11818 -0.0432 0.0075 0.7571 20.000 1.2107 0.12988 0.12528 -0.0459 0.0081 0.7577 20.500 1.2053 0.13767 0.13327 -0.0500 0.0072 0.7580 21.000 1.2075 0.14428 0.13998 -0.0544 0.0067 0.7580 21.500 1.1934 0.15323 0.14926 -0.0598 0.0069 0.7575 22.000 1.1665 0.16570 0.16211 -0.0671 0.0075 0.7574 22.500 1.1252 0.18340 0.18022 -0.0777 0.0080 0.7567 23.000 0.9889 0.24055 0.23792 -0.1042 0.0100 0.7560 24.500 0.9701 0.29699 0.29439 -0.1222 0.0170 0.7556 25.000 0.9781 0.30734 0.30478 -0.1270 0.0167 0.7558 25.500 0.9850 0.31833 0.31579 -0.1312 0.0168 0.7562 26.000 0.9928 0.32837 0.32587 -0.1351 0.0168 0.7565 26.500 1.0067 0.33166 0.32917 -0.1404 0.0082 0.7569 27.500 1.0171 0.35367 0.35125 -0.1484 0.0087 0.7575 28.000 1.0196 0.36808 0.36570 -0.1530 0.0065 0.7587 28.500 1.0326 0.36992 0.36762 -0.1565 0.0049 0.7598