XFOIL Version 6.96 Calculated polar for: FX 60-100 (126) 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4186 0.08234 0.08015 -0.0405 1.0000 0.0060 -9.250 -0.4339 0.07589 0.07376 -0.0429 1.0000 0.0059 -9.000 -0.5390 0.04476 0.04252 -0.0652 0.9927 0.0052 -8.750 -0.5115 0.02998 0.02687 -0.0938 0.9814 0.0051 -8.500 -0.4781 0.02548 0.02187 -0.1010 0.9774 0.0052 -8.250 -0.4478 0.02278 0.01883 -0.1045 0.9712 0.0054 -8.000 -0.4151 0.02052 0.01626 -0.1076 0.9667 0.0055 -7.750 -0.3859 0.01884 0.01433 -0.1093 0.9614 0.0058 -7.500 -0.3557 0.01737 0.01263 -0.1108 0.9566 0.0061 -7.250 -0.3240 0.01609 0.01114 -0.1124 0.9527 0.0064 -7.000 -0.2963 0.01506 0.00994 -0.1129 0.9457 0.0067 -6.750 -0.2661 0.01417 0.00890 -0.1138 0.9401 0.0070 -6.500 -0.2375 0.01352 0.00812 -0.1143 0.9334 0.0072 -6.250 -0.2085 0.01236 0.00678 -0.1151 0.9266 0.0082 -6.000 -0.1800 0.01176 0.00610 -0.1155 0.9193 0.0089 -5.750 -0.1509 0.01121 0.00544 -0.1159 0.9115 0.0096 -5.500 -0.1224 0.01073 0.00485 -0.1162 0.9026 0.0104 -5.250 -0.0935 0.01033 0.00433 -0.1164 0.8938 0.0113 -5.000 -0.0649 0.01000 0.00390 -0.1165 0.8844 0.0123 -4.750 -0.0360 0.00960 0.00337 -0.1167 0.8752 0.0171 -4.500 -0.0073 0.00927 0.00304 -0.1169 0.8662 0.0270 -4.250 0.0211 0.00903 0.00282 -0.1171 0.8563 0.0446 -4.000 0.0494 0.00887 0.00262 -0.1172 0.8463 0.0543 -3.750 0.0778 0.00873 0.00242 -0.1172 0.8363 0.0616 -3.500 0.1061 0.00855 0.00222 -0.1173 0.8265 0.0761 -3.250 0.1348 0.00823 0.00201 -0.1177 0.8168 0.1151 -3.000 0.1635 0.00790 0.00181 -0.1180 0.8072 0.1763 -2.500 0.2206 0.00737 0.00151 -0.1186 0.7863 0.2897 -2.250 0.2491 0.00711 0.00144 -0.1189 0.7759 0.3675 -2.000 0.2773 0.00708 0.00148 -0.1189 0.7651 0.4170 -1.500 0.3333 0.00721 0.00151 -0.1186 0.7400 0.4564 -1.250 0.3611 0.00731 0.00151 -0.1184 0.7236 0.4664 -1.000 0.3886 0.00743 0.00152 -0.1182 0.7030 0.4769 -0.750 0.4158 0.00755 0.00155 -0.1179 0.6818 0.4854 -0.500 0.4434 0.00767 0.00155 -0.1177 0.6636 0.4908 -0.250 0.4710 0.00776 0.00156 -0.1176 0.6475 0.4944 0.000 0.4984 0.00785 0.00159 -0.1174 0.6312 0.4980 0.250 0.5259 0.00796 0.00162 -0.1172 0.6150 0.5013 0.500 0.5535 0.00808 0.00166 -0.1171 0.5997 0.5049 0.750 0.5809 0.00819 0.00170 -0.1170 0.5839 0.5076 1.000 0.6082 0.00830 0.00176 -0.1168 0.5680 0.5105 1.250 0.6357 0.00840 0.00182 -0.1167 0.5550 0.5139 1.500 0.6635 0.00849 0.00190 -0.1166 0.5454 0.5170 1.750 0.6911 0.00860 0.00197 -0.1165 0.5355 0.5194 2.000 0.7189 0.00868 0.00205 -0.1165 0.5252 0.5213 2.250 0.7465 0.00876 0.00215 -0.1164 0.5147 0.5233 2.500 0.7739 0.00887 0.00225 -0.1163 0.5025 0.5253 2.750 0.8012 0.00899 0.00236 -0.1161 0.4872 0.5272 3.000 0.8283 0.00913 0.00249 -0.1160 0.4687 0.5292 3.250 0.8550 0.00931 0.00262 -0.1157 0.4470 0.5316 3.500 0.8812 0.00954 0.00277 -0.1155 0.4190 0.5338 3.750 0.9069 0.00985 0.00297 -0.1151 0.3867 0.5359 4.000 0.9320 0.01022 0.00323 -0.1147 0.3524 0.5379 4.250 0.9574 0.01056 0.00349 -0.1144 0.3254 0.5401 4.500 0.9828 0.01090 0.00377 -0.1140 0.3004 0.5427 4.750 1.0077 0.01131 0.00407 -0.1136 0.2689 0.5456 5.000 1.0306 0.01197 0.00448 -0.1130 0.2180 0.5484 5.250 1.0542 0.01252 0.00487 -0.1125 0.1802 0.5512 5.500 1.0787 0.01295 0.00523 -0.1120 0.1584 0.5543 5.750 1.1029 0.01342 0.00561 -0.1115 0.1343 0.5578 6.000 1.1238 0.01428 0.00618 -0.1107 0.0826 0.5617 6.250 1.1443 0.01519 0.00689 -0.1097 0.0420 0.5661 6.500 1.1653 0.01603 0.00765 -0.1088 0.0166 0.5719 7.000 1.2122 0.01705 0.00883 -0.1074 0.0098 0.5879 7.250 1.2354 0.01754 0.00945 -0.1067 0.0088 0.6005 7.500 1.2578 0.01809 0.01015 -0.1060 0.0080 0.6211 7.750 1.2792 0.01873 0.01096 -0.1050 0.0072 0.6555 8.000 1.2978 0.01966 0.01213 -0.1037 0.0065 0.7060 8.250 1.3185 0.02017 0.01288 -0.1027 0.0061 0.7767 8.500 1.3330 0.02046 0.01351 -0.1002 0.0057 1.0000 8.750 1.3523 0.02124 0.01436 -0.0990 0.0053 1.0000 9.000 1.3701 0.02211 0.01531 -0.0977 0.0050 1.0000 9.250 1.3869 0.02303 0.01630 -0.0962 0.0048 1.0000 9.500 1.4020 0.02402 0.01742 -0.0945 0.0045 1.0000 9.750 1.4137 0.02518 0.01867 -0.0924 0.0043 1.0000 10.000 1.4177 0.02666 0.02025 -0.0891 0.0042 1.0000 10.250 1.4219 0.02810 0.02181 -0.0861 0.0041 1.0000 10.500 1.4285 0.02943 0.02326 -0.0835 0.0040 1.0000 10.750 1.4341 0.03091 0.02487 -0.0811 0.0039 1.0000 11.000 1.4381 0.03261 0.02670 -0.0787 0.0038 1.0000 11.250 1.4415 0.03446 0.02870 -0.0766 0.0037 1.0000 11.500 1.4443 0.03647 0.03084 -0.0747 0.0036 1.0000 11.750 1.4469 0.03859 0.03311 -0.0731 0.0035 1.0000 12.000 1.4487 0.04089 0.03555 -0.0717 0.0034 1.0000 12.250 1.4506 0.04328 0.03808 -0.0707 0.0032 1.0000 12.500 1.4516 0.04587 0.04081 -0.0699 0.0031 1.0000 12.750 1.4519 0.04864 0.04371 -0.0694 0.0030 1.0000 13.000 1.4506 0.05178 0.04698 -0.0691 0.0030 1.0000 13.250 1.4492 0.05504 0.05036 -0.0692 0.0029 1.0000 13.500 1.4455 0.05880 0.05426 -0.0696 0.0028 1.0000 13.750 1.4408 0.06288 0.05848 -0.0704 0.0028 1.0000 14.000 1.4340 0.06745 0.06320 -0.0715 0.0028 1.0000 14.250 1.4265 0.07235 0.06825 -0.0730 0.0027 1.0000 14.500 1.4180 0.07767 0.07372 -0.0750 0.0027 1.0000 14.750 1.4076 0.08356 0.07976 -0.0773 0.0027 1.0000 15.000 1.3962 0.08988 0.08625 -0.0801 0.0027 1.0000 15.250 1.3843 0.09661 0.09313 -0.0833 0.0026 1.0000 15.500 1.3712 0.10387 0.10055 -0.0870 0.0026 1.0000 15.750 1.3580 0.11144 0.10828 -0.0910 0.0026 1.0000 16.000 1.3446 0.11938 0.11638 -0.0954 0.0026 1.0000 16.250 1.3308 0.12763 0.12479 -0.1002 0.0026 1.0000 16.500 1.3173 0.13608 0.13339 -0.1051 0.0026 1.0000 16.750 1.3039 0.14469 0.14214 -0.1104 0.0026 1.0000 17.000 1.2909 0.15351 0.15111 -0.1158 0.0026 1.0000 17.250 1.2770 0.16291 0.16066 -0.1218 0.0026 1.0000 17.500 1.2614 0.17316 0.17106 -0.1283 0.0027 1.0000 17.750 1.2476 0.18332 0.18134 -0.1348 0.0027 1.0000 18.000 1.2255 0.19723 0.19543 -0.1436 0.0027 1.0000