GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il) Reynolds number: 200,000 Max Cl/Cd: 76.24 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe602m-il-200000-n5.txt Download as CSV file: xf-goe602m-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 MOD. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3829 0.08870 0.08537 -0.0370 1.0000 0.0142
-8.500 -0.3927 0.08578 0.08252 -0.0361 1.0000 0.0143
-8.250 -0.4060 0.08314 0.07995 -0.0346 1.0000 0.0142
-8.000 -0.4106 0.07888 0.07575 -0.0370 0.9973 0.0144
-7.750 -0.4025 0.07100 0.06789 -0.0469 0.9895 0.0150
-7.500 -0.3889 0.06058 0.05745 -0.0613 0.9812 0.0151
-7.250 -0.3791 0.04113 0.03743 -0.0826 0.9704 0.0151
-7.000 -0.3586 0.03126 0.02654 -0.0904 0.9653 0.0157
-6.750 -0.3406 0.02684 0.02148 -0.0915 0.9584 0.0165
-6.500 -0.3112 0.02498 0.01937 -0.0933 0.9551 0.0175
-6.250 -0.2780 0.02400 0.01819 -0.0952 0.9529 0.0193
-6.000 -0.2538 0.02263 0.01650 -0.0950 0.9469 0.0217
-5.750 -0.2235 0.02089 0.01429 -0.0959 0.9432 0.0238
-5.500 -0.1913 0.01926 0.01239 -0.0973 0.9406 0.0265
-5.250 -0.1565 0.01842 0.01143 -0.0991 0.9386 0.0297
-5.000 -0.1316 0.01761 0.01044 -0.0985 0.9321 0.0325
-4.750 -0.0985 0.01707 0.00970 -0.0996 0.9284 0.0355
-4.500 -0.0657 0.01574 0.00826 -0.1009 0.9255 0.0386
-4.250 -0.0377 0.01518 0.00766 -0.1010 0.9197 0.0420
-4.000 -0.0071 0.01459 0.00696 -0.1015 0.9144 0.0442
-3.750 0.0273 0.01400 0.00627 -0.1028 0.9107 0.0459
-3.500 0.0540 0.01365 0.00581 -0.1025 0.9030 0.0480
-3.250 0.0863 0.01309 0.00519 -0.1034 0.8976 0.0510
-3.000 0.1149 0.01272 0.00476 -0.1035 0.8902 0.0541
-2.750 0.1459 0.01239 0.00435 -0.1039 0.8836 0.0596
-2.500 0.1742 0.01202 0.00406 -0.1040 0.8757 0.0809
-2.250 0.2044 0.01164 0.00376 -0.1044 0.8686 0.1233
-2.000 0.2305 0.01116 0.00357 -0.1043 0.8593 0.1993
-1.750 0.2600 0.01086 0.00346 -0.1046 0.8514 0.2843
-1.500 0.2875 0.01068 0.00334 -0.1045 0.8415 0.3237
-1.250 0.3145 0.01046 0.00323 -0.1042 0.8311 0.3658
-1.000 0.3411 0.01015 0.00320 -0.1040 0.8208 0.4443
-0.750 0.3684 0.00994 0.00315 -0.1037 0.8098 0.5152
-0.500 0.3951 0.00981 0.00307 -0.1032 0.7976 0.5623
-0.250 0.4214 0.00966 0.00299 -0.1027 0.7846 0.6042
0.000 0.4468 0.00945 0.00294 -0.1020 0.7713 0.6572
0.250 0.4712 0.00907 0.00293 -0.1007 0.7576 0.7998
0.500 0.5249 0.00884 0.00281 -0.1059 0.7430 1.0000
0.750 0.5514 0.00893 0.00277 -0.1055 0.7273 1.0000
1.000 0.5777 0.00904 0.00276 -0.1050 0.7113 1.0000
1.250 0.6036 0.00917 0.00277 -0.1045 0.6949 1.0000
1.500 0.6290 0.00931 0.00281 -0.1039 0.6775 1.0000
1.750 0.6542 0.00947 0.00286 -0.1032 0.6595 1.0000
2.000 0.6790 0.00965 0.00292 -0.1025 0.6394 1.0000
2.250 0.7031 0.00985 0.00301 -0.1016 0.6171 1.0000
2.500 0.7272 0.01006 0.00311 -0.1008 0.5960 1.0000
2.750 0.7512 0.01028 0.00323 -0.1000 0.5757 1.0000
3.000 0.7754 0.01049 0.00338 -0.0992 0.5573 1.0000
3.250 0.7997 0.01071 0.00355 -0.0984 0.5403 1.0000
3.500 0.8237 0.01095 0.00372 -0.0977 0.5232 1.0000
3.750 0.8473 0.01121 0.00393 -0.0968 0.5057 1.0000
4.000 0.8707 0.01147 0.00415 -0.0960 0.4860 1.0000
4.250 0.8940 0.01175 0.00438 -0.0951 0.4670 1.0000
4.500 0.9172 0.01203 0.00463 -0.0942 0.4496 1.0000
4.750 0.9401 0.01233 0.00492 -0.0933 0.4317 1.0000
5.000 0.9610 0.01272 0.00521 -0.0920 0.4021 1.0000
5.250 0.9802 0.01320 0.00552 -0.0905 0.3623 1.0000
5.500 0.9976 0.01381 0.00589 -0.0887 0.3115 1.0000
5.750 1.0131 0.01462 0.00638 -0.0867 0.2512 1.0000
6.000 1.0290 0.01548 0.00695 -0.0849 0.1973 1.0000
6.250 1.0398 0.01681 0.00777 -0.0825 0.1144 1.0000
6.500 1.0534 0.01793 0.00861 -0.0804 0.0708 1.0000
6.750 1.0654 0.01917 0.00960 -0.0779 0.0253 1.0000
7.000 1.0820 0.01997 0.01048 -0.0760 0.0205 1.0000
7.250 1.0975 0.02085 0.01153 -0.0740 0.0175 1.0000
7.500 1.1142 0.02157 0.01240 -0.0722 0.0167 1.0000
7.750 1.1286 0.02235 0.01333 -0.0699 0.0158 1.0000
8.000 1.1412 0.02321 0.01431 -0.0675 0.0145 1.0000
8.250 1.1523 0.02415 0.01537 -0.0650 0.0133 1.0000
8.500 1.1612 0.02525 0.01658 -0.0623 0.0127 1.0000
8.750 1.1679 0.02650 0.01795 -0.0594 0.0122 1.0000
9.000 1.1725 0.02794 0.01948 -0.0564 0.0117 1.0000
9.250 1.1747 0.02965 0.02128 -0.0533 0.0113 1.0000
9.500 1.1769 0.03156 0.02327 -0.0505 0.0111 1.0000
9.750 1.1802 0.03383 0.02564 -0.0479 0.0107 1.0000
10.000 1.1909 0.03517 0.02709 -0.0462 0.0103 1.0000
10.250 1.2013 0.03657 0.02862 -0.0446 0.0099 1.0000
10.500 1.2110 0.03812 0.03029 -0.0430 0.0093 1.0000
10.750 1.2208 0.03993 0.03222 -0.0414 0.0090 1.0000
11.000 1.2309 0.04185 0.03427 -0.0400 0.0088 1.0000
11.250 1.2401 0.04393 0.03648 -0.0385 0.0085 1.0000
11.500 1.2481 0.04613 0.03885 -0.0372 0.0083 1.0000
11.750 1.2545 0.04850 0.04139 -0.0358 0.0082 1.0000
12.000 1.2587 0.05104 0.04411 -0.0346 0.0081 1.0000
12.250 1.2609 0.05379 0.04706 -0.0334 0.0080 1.0000
12.500 1.2609 0.05675 0.05022 -0.0324 0.0079 1.0000
12.750 1.2586 0.05999 0.05367 -0.0316 0.0078 1.0000
13.000 1.2541 0.06350 0.05739 -0.0310 0.0078 1.0000
13.250 1.2476 0.06730 0.06139 -0.0309 0.0077 1.0000
13.500 1.2389 0.07151 0.06588 -0.0311 0.0077 1.0000
13.750 1.2287 0.07603 0.07061 -0.0318 0.0077 1.0000
14.000 1.2182 0.08072 0.07549 -0.0330 0.0076 1.0000
14.250 1.2063 0.08584 0.08080 -0.0347 0.0076 1.0000
14.500 1.1936 0.09139 0.08654 -0.0370 0.0075 1.0000
14.750 1.1795 0.09747 0.09282 -0.0398 0.0075 1.0000
15.000 1.1645 0.10415 0.09970 -0.0432 0.0076 1.0000
15.250 1.1417 0.11298 0.10882 -0.0485 0.0078 1.0000
15.500 1.1358 0.11830 0.11420 -0.0515 0.0075 1.0000
15.750 1.1055 0.13033 0.12651 -0.0594 0.0079 1.0000
16.000 1.0828 0.14147 0.13785 -0.0668 0.0081 1.0000
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Polar data table (+)
Polar graphs
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