XFOIL Version 6.96 Calculated polar for: GOE 255 (MVA CA.6) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.5776 0.11408 0.11120 -0.0649 1.0000 0.0155 -17.000 -0.6293 0.09985 0.09666 -0.0731 1.0000 0.0152 -16.750 -0.6522 0.09179 0.08842 -0.0778 1.0000 0.0152 -16.500 -0.6684 0.08525 0.08175 -0.0817 1.0000 0.0151 -16.250 -0.6805 0.07975 0.07613 -0.0848 1.0000 0.0152 -16.000 -0.6904 0.07487 0.07115 -0.0875 1.0000 0.0152 -15.750 -0.6994 0.07045 0.06664 -0.0898 1.0000 0.0153 -15.500 -0.7088 0.06648 0.06259 -0.0915 1.0000 0.0154 -15.250 -0.7191 0.06289 0.05892 -0.0925 1.0000 0.0154 -15.000 -0.7303 0.05962 0.05558 -0.0930 1.0000 0.0155 -14.750 -0.7421 0.05656 0.05245 -0.0930 1.0000 0.0156 -14.500 -0.7545 0.05369 0.04952 -0.0925 1.0000 0.0156 -14.250 -0.7633 0.05075 0.04651 -0.0928 0.9996 0.0157 -14.000 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0.7836 0.0265 -9.000 -0.4427 0.01580 0.00913 -0.1100 0.7782 0.0285 -8.750 -0.4174 0.01535 0.00859 -0.1099 0.7728 0.0305 -8.500 -0.3933 0.01473 0.00792 -0.1096 0.7677 0.0345 -8.250 -0.3684 0.01414 0.00734 -0.1095 0.7629 0.0425 -8.000 -0.3440 0.01345 0.00679 -0.1094 0.7577 0.0643 -7.750 -0.3177 0.01307 0.00641 -0.1094 0.7526 0.0812 -7.500 -0.2912 0.01270 0.00605 -0.1094 0.7478 0.0951 -7.250 -0.2644 0.01232 0.00573 -0.1095 0.7424 0.1108 -7.000 -0.2372 0.01201 0.00546 -0.1096 0.7372 0.1305 -6.750 -0.2096 0.01178 0.00523 -0.1097 0.7323 0.1501 -6.500 -0.1817 0.01153 0.00504 -0.1099 0.7271 0.1673 -6.250 -0.1535 0.01134 0.00484 -0.1101 0.7217 0.1819 -6.000 -0.1253 0.01120 0.00465 -0.1103 0.7166 0.1962 -5.750 -0.0972 0.01098 0.00447 -0.1105 0.7112 0.2122 -5.500 -0.0692 0.01075 0.00427 -0.1106 0.7054 0.2290 -5.250 -0.0414 0.01055 0.00408 -0.1108 0.7000 0.2484 -5.000 -0.0134 0.01032 0.00393 -0.1110 0.6938 0.2712 -4.750 0.0147 0.01015 0.00384 -0.1111 0.6871 0.2992 -4.500 0.0434 0.01011 0.00379 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0.4554 0.500 0.6163 0.01060 0.00357 -0.1153 0.5623 0.4610 0.750 0.6447 0.01065 0.00361 -0.1156 0.5589 0.4665 1.000 0.6732 0.01076 0.00367 -0.1158 0.5559 0.4720 1.250 0.7015 0.01078 0.00373 -0.1161 0.5530 0.4780 1.500 0.7299 0.01080 0.00380 -0.1163 0.5499 0.4839 1.750 0.7582 0.01085 0.00386 -0.1165 0.5467 0.4893 2.000 0.7862 0.01088 0.00393 -0.1167 0.5433 0.4955 2.250 0.8142 0.01097 0.00401 -0.1169 0.5399 0.5030 2.500 0.8424 0.01103 0.00411 -0.1172 0.5370 0.5119 2.750 0.8702 0.01105 0.00421 -0.1174 0.5341 0.5241 3.250 0.9251 0.01106 0.00444 -0.1176 0.5275 0.5709 3.500 0.9519 0.01106 0.00458 -0.1176 0.5235 0.6217 3.750 0.9772 0.01094 0.00475 -0.1173 0.5191 0.7047 4.000 0.9978 0.01065 0.00491 -0.1157 0.5140 0.8315 4.250 1.0304 0.01058 0.00502 -0.1166 0.5083 1.0000 4.500 1.0564 0.01073 0.00515 -0.1164 0.5038 1.0000 4.750 1.0821 0.01082 0.00527 -0.1162 0.4992 1.0000 5.000 1.1076 0.01095 0.00539 -0.1159 0.4942 1.0000 5.250 1.1326 0.01115 0.00554 -0.1156 0.4891 1.0000 5.500 1.1573 0.01122 0.00568 -0.1152 0.4830 1.0000 5.750 1.1808 0.01138 0.00582 -0.1145 0.4757 1.0000 6.000 1.2044 0.01152 0.00598 -0.1139 0.4679 1.0000 6.250 1.2260 0.01170 0.00614 -0.1130 0.4582 1.0000 6.500 1.2472 0.01187 0.00632 -0.1119 0.4451 1.0000 6.750 1.2632 0.01214 0.00654 -0.1099 0.4254 1.0000 7.000 1.2710 0.01264 0.00690 -0.1064 0.3906 1.0000 7.250 1.2738 0.01353 0.00757 -0.1024 0.3598 1.0000 7.500 1.2820 0.01435 0.00827 -0.0994 0.3429 1.0000 7.750 1.2935 0.01509 0.00894 -0.0972 0.3326 1.0000 8.000 1.3075 0.01575 0.00958 -0.0953 0.3245 1.0000 8.250 1.3208 0.01647 0.01027 -0.0935 0.3175 1.0000 8.500 1.3364 0.01710 0.01091 -0.0921 0.3106 1.0000 8.750 1.3475 0.01797 0.01174 -0.0901 0.3037 1.0000 9.000 1.3656 0.01851 0.01234 -0.0891 0.2987 1.0000 9.250 1.3808 0.01922 0.01306 -0.0878 0.2932 1.0000 9.500 1.3916 0.02021 0.01403 -0.0861 0.2873 1.0000 9.750 1.4100 0.02080 0.01468 -0.0853 0.2813 1.0000 10.000 1.4226 0.02175 0.01563 -0.0840 0.2742 1.0000 10.250 1.4368 0.02265 0.01656 -0.0829 0.2663 1.0000 10.500 1.4488 0.02373 0.01764 -0.0817 0.2575 1.0000 10.750 1.4625 0.02474 0.01867 -0.0808 0.2479 1.0000 11.000 1.4718 0.02608 0.02000 -0.0795 0.2354 1.0000 11.250 1.4769 0.02780 0.02164 -0.0780 0.2151 1.0000 11.500 1.4697 0.03051 0.02418 -0.0757 0.1849 1.0000 11.750 1.4576 0.03370 0.02719 -0.0732 0.1604 1.0000 12.000 1.4497 0.03665 0.03005 -0.0711 0.1434 1.0000 12.250 1.4445 0.03944 0.03277 -0.0694 0.1270 1.0000 12.500 1.4354 0.04266 0.03587 -0.0676 0.1034 1.0000 12.750 1.4190 0.04668 0.03971 -0.0656 0.0776 1.0000 13.000 1.4069 0.05045 0.04339 -0.0641 0.0587 1.0000 13.500 1.3756 0.05920 0.05201 -0.0615 0.0200 1.0000 13.750 1.3769 0.06196 0.05484 -0.0610 0.0184 1.0000 14.000 1.3788 0.06469 0.05766 -0.0606 0.0176 1.0000 14.250 1.3798 0.06757 0.06062 -0.0602 0.0169 1.0000 14.500 1.3790 0.07067 0.06382 -0.0599 0.0162 1.0000 14.750 1.3761 0.07407 0.06731 -0.0596 0.0155 1.0000 15.000 1.3770 0.07706 0.07039 -0.0595 0.0152 1.0000 15.250 1.3769 0.08018 0.07361 -0.0594 0.0148 1.0000 15.500 1.3748 0.08363 0.07715 -0.0594 0.0145 1.0000 15.750 1.3716 0.08722 0.08084 -0.0595 0.0142 1.0000 16.000 1.3675 0.09097 0.08469 -0.0596 0.0139 1.0000 16.250 1.3616 0.09503 0.08884 -0.0599 0.0137 1.0000 16.500 1.3543 0.09935 0.09325 -0.0603 0.0135 1.0000 16.750 1.3465 0.10379 0.09780 -0.0609 0.0133 1.0000 17.000 1.3366 0.10860 0.10271 -0.0617 0.0131 1.0000 17.250 1.3247 0.11379 0.10801 -0.0627 0.0129 1.0000