GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 500,000 Max Cl/Cd: 98.62 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe413-il-500000-n5.txt Download as CSV file: xf-goe413-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 413 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7978 0.06221 0.05836 -0.0724 0.9222 0.0366
-14.000 -0.8293 0.05408 0.04990 -0.0791 0.8968 0.0367
-13.750 -0.8466 0.04775 0.04330 -0.0851 0.8814 0.0368
-13.500 -0.8552 0.04263 0.03793 -0.0905 0.8702 0.0369
-13.250 -0.8558 0.03866 0.03376 -0.0951 0.8606 0.0371
-13.000 -0.8497 0.03574 0.03070 -0.0985 0.8529 0.0372
-12.750 -0.8413 0.03346 0.02830 -0.1012 0.8455 0.0373
-12.500 -0.8265 0.03186 0.02659 -0.1026 0.8389 0.0375
-12.250 -0.8094 0.03056 0.02518 -0.1035 0.8332 0.0376
-12.000 -0.7902 0.02937 0.02391 -0.1042 0.8278 0.0378
-11.750 -0.7699 0.02831 0.02277 -0.1048 0.8226 0.0380
-11.500 -0.7485 0.02737 0.02174 -0.1052 0.8174 0.0382
-11.250 -0.7262 0.02650 0.02077 -0.1056 0.8124 0.0384
-11.000 -0.7030 0.02565 0.01985 -0.1060 0.8069 0.0387
-10.750 -0.6795 0.02482 0.01891 -0.1062 0.8011 0.0390
-10.500 -0.6557 0.02399 0.01797 -0.1065 0.7958 0.0393
-10.250 -0.6311 0.02317 0.01706 -0.1067 0.7909 0.0396
-10.000 -0.6061 0.02239 0.01618 -0.1070 0.7849 0.0399
-9.750 -0.5808 0.02166 0.01535 -0.1071 0.7785 0.0402
-9.500 -0.5551 0.02096 0.01455 -0.1073 0.7722 0.0405
-9.250 -0.5288 0.02031 0.01380 -0.1074 0.7648 0.0408
-9.000 -0.5025 0.01971 0.01310 -0.1076 0.7575 0.0410
-8.750 -0.4755 0.01916 0.01246 -0.1077 0.7501 0.0413
-8.500 -0.4488 0.01856 0.01178 -0.1078 0.7410 0.0415
-8.250 -0.4221 0.01794 0.01113 -0.1079 0.7315 0.0418
-8.000 -0.3950 0.01746 0.01060 -0.1080 0.7195 0.0421
-7.750 -0.3675 0.01703 0.01012 -0.1081 0.7066 0.0425
-7.500 -0.3400 0.01665 0.00966 -0.1082 0.6936 0.0429
-7.000 -0.2845 0.01590 0.00876 -0.1084 0.6693 0.0436
-6.750 -0.2567 0.01556 0.00833 -0.1085 0.6588 0.0439
-6.500 -0.2286 0.01523 0.00792 -0.1086 0.6487 0.0443
-6.250 -0.2004 0.01493 0.00753 -0.1087 0.6398 0.0447
-6.000 -0.1719 0.01462 0.00717 -0.1088 0.6321 0.0451
-5.750 -0.1434 0.01436 0.00683 -0.1089 0.6251 0.0455
-5.500 -0.1147 0.01411 0.00653 -0.1091 0.6194 0.0459
-5.250 -0.0857 0.01388 0.00624 -0.1093 0.6136 0.0462
-5.000 -0.0572 0.01350 0.00585 -0.1095 0.6076 0.0467
-4.500 0.0007 0.01301 0.00531 -0.1099 0.5975 0.0479
-4.250 0.0300 0.01279 0.00508 -0.1101 0.5928 0.0485
-4.000 0.0591 0.01260 0.00485 -0.1103 0.5878 0.0490
-3.750 0.0883 0.01243 0.00464 -0.1104 0.5829 0.0496
-3.500 0.1177 0.01227 0.00444 -0.1106 0.5788 0.0502
-3.250 0.1472 0.01210 0.00426 -0.1108 0.5745 0.0508
-3.000 0.1767 0.01198 0.00411 -0.1110 0.5698 0.0513
-2.750 0.2060 0.01178 0.00389 -0.1112 0.5650 0.0521
-2.500 0.2353 0.01164 0.00372 -0.1114 0.5603 0.0530
-2.250 0.2649 0.01150 0.00358 -0.1117 0.5555 0.0540
-2.000 0.2944 0.01140 0.00346 -0.1118 0.5503 0.0552
-1.750 0.3238 0.01133 0.00336 -0.1120 0.5455 0.0563
-1.500 0.3531 0.01127 0.00326 -0.1121 0.5411 0.0575
-1.250 0.3828 0.01116 0.00316 -0.1123 0.5373 0.0592
-1.000 0.4124 0.01108 0.00308 -0.1125 0.5329 0.0611
-0.750 0.4419 0.01102 0.00301 -0.1127 0.5283 0.0640
-0.500 0.4712 0.01090 0.00293 -0.1129 0.5239 0.0749
-0.250 0.5007 0.01059 0.00289 -0.1133 0.5201 0.1509
0.000 0.5303 0.01052 0.00289 -0.1136 0.5157 0.1702
0.250 0.5597 0.01048 0.00290 -0.1138 0.5109 0.1859
0.500 0.5890 0.01047 0.00291 -0.1139 0.5064 0.2010
0.750 0.6181 0.01045 0.00294 -0.1141 0.5021 0.2199
1.000 0.6476 0.01041 0.00298 -0.1143 0.4975 0.2415
1.250 0.6769 0.01038 0.00303 -0.1145 0.4924 0.2679
1.500 0.7059 0.01036 0.00309 -0.1146 0.4875 0.2959
1.750 0.7348 0.01038 0.00316 -0.1148 0.4822 0.3217
2.000 0.7640 0.01037 0.00322 -0.1149 0.4753 0.3482
2.250 0.7925 0.01042 0.00330 -0.1150 0.4678 0.3729
2.500 0.8213 0.01044 0.00338 -0.1151 0.4607 0.3975
2.750 0.8498 0.01047 0.00348 -0.1152 0.4518 0.4262
3.000 0.8781 0.01050 0.00360 -0.1153 0.4433 0.4681
3.250 0.9064 0.01053 0.00374 -0.1153 0.4340 0.5175
3.500 0.9345 0.01062 0.00388 -0.1153 0.4262 0.5506
4.000 0.9898 0.01085 0.00416 -0.1152 0.4051 0.6015
4.250 1.0166 0.01100 0.00434 -0.1150 0.3930 0.6332
4.500 1.0432 0.01105 0.00456 -0.1148 0.3807 0.6980
4.750 1.0667 0.01105 0.00481 -0.1138 0.3686 0.8123
5.000 1.0838 0.01099 0.00494 -0.1113 0.3576 1.0000
5.250 1.1104 0.01126 0.00515 -0.1111 0.3461 1.0000
5.500 1.1362 0.01159 0.00540 -0.1109 0.3337 1.0000
5.750 1.1614 0.01195 0.00567 -0.1105 0.3214 1.0000
6.000 1.1871 0.01226 0.00593 -0.1102 0.3108 1.0000
6.250 1.2122 0.01260 0.00622 -0.1098 0.3005 1.0000
6.500 1.2361 0.01301 0.00654 -0.1093 0.2889 1.0000
6.750 1.2607 0.01336 0.00685 -0.1089 0.2774 1.0000
7.000 1.2835 0.01381 0.00722 -0.1082 0.2636 1.0000
7.250 1.3052 0.01432 0.00764 -0.1075 0.2482 1.0000
7.500 1.3256 0.01489 0.00811 -0.1065 0.2313 1.0000
7.750 1.3434 0.01558 0.00868 -0.1052 0.2109 1.0000
8.000 1.3578 0.01642 0.00937 -0.1035 0.1874 1.0000
8.250 1.3657 0.01747 0.01025 -0.1009 0.1608 1.0000
8.500 1.3542 0.01982 0.01223 -0.0965 0.1000 1.0000
8.750 1.3564 0.02153 0.01380 -0.0941 0.0778 1.0000
9.000 1.3687 0.02263 0.01489 -0.0928 0.0726 1.0000
9.250 1.3812 0.02374 0.01600 -0.0916 0.0694 1.0000
9.500 1.3945 0.02483 0.01712 -0.0906 0.0673 1.0000
9.750 1.4079 0.02593 0.01825 -0.0896 0.0658 1.0000
10.000 1.4203 0.02714 0.01948 -0.0886 0.0646 1.0000
10.250 1.4317 0.02845 0.02083 -0.0876 0.0634 1.0000
10.500 1.4418 0.02989 0.02229 -0.0866 0.0624 1.0000
10.750 1.4510 0.03143 0.02387 -0.0856 0.0616 1.0000
11.000 1.4589 0.03314 0.02562 -0.0846 0.0607 1.0000
11.250 1.4684 0.03472 0.02726 -0.0838 0.0603 1.0000
11.500 1.4771 0.03642 0.02900 -0.0830 0.0599 1.0000
11.750 1.4848 0.03824 0.03088 -0.0822 0.0594 1.0000
12.000 1.4916 0.04018 0.03289 -0.0815 0.0590 1.0000
12.250 1.4974 0.04225 0.03502 -0.0808 0.0585 1.0000
12.500 1.5024 0.04446 0.03729 -0.0802 0.0581 1.0000
12.750 1.5068 0.04678 0.03968 -0.0797 0.0577 1.0000
13.000 1.5105 0.04922 0.04218 -0.0792 0.0574 1.0000
13.250 1.5136 0.05176 0.04479 -0.0788 0.0570 1.0000
13.500 1.5158 0.05446 0.04755 -0.0784 0.0566 1.0000
13.750 1.5171 0.05731 0.05046 -0.0781 0.0562 1.0000
14.000 1.5179 0.06020 0.05342 -0.0779 0.0558 1.0000
14.250 1.5177 0.06327 0.05655 -0.0777 0.0555 1.0000
14.500 1.5165 0.06649 0.05984 -0.0775 0.0552 1.0000
14.750 1.5154 0.06973 0.06315 -0.0775 0.0549 1.0000
15.000 1.5130 0.07316 0.06665 -0.0774 0.0546 1.0000
15.250 1.5100 0.07671 0.07026 -0.0775 0.0543 1.0000
15.500 1.5074 0.08022 0.07385 -0.0776 0.0541 1.0000
15.750 1.5061 0.08364 0.07733 -0.0778 0.0539 1.0000
16.000 1.5069 0.08675 0.08052 -0.0779 0.0538 1.0000
16.250 1.5067 0.09004 0.08389 -0.0782 0.0536 1.0000
16.500 1.5074 0.09320 0.08712 -0.0784 0.0535 1.0000
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Polar data table (+)
Polar graphs
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