GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 480 AIRFOIL (goe480-il) Reynolds number: 500,000 Max Cl/Cd: 112.5 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe480-il-500000.txt Download as CSV file: xf-goe480-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 480 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2756 0.12345 0.12096 -0.0405 1.0000 0.0358
-11.500 -0.2724 0.12077 0.11830 -0.0409 1.0000 0.0369
-11.250 -0.2983 0.11569 0.11325 -0.0460 1.0000 0.0384
-11.000 -0.2925 0.11261 0.11019 -0.0448 1.0000 0.0386
-10.750 -0.2835 0.11057 0.10818 -0.0432 1.0000 0.0388
-10.500 -0.2801 0.10877 0.10642 -0.0417 1.0000 0.0391
-10.250 -0.2665 0.10622 0.10387 -0.0431 0.9991 0.0395
-10.000 -0.2469 0.10277 0.10041 -0.0470 0.9967 0.0403
-9.750 -0.2294 0.09900 0.09664 -0.0514 0.9923 0.0419
-9.500 -0.2355 0.08999 0.08761 -0.0647 0.9838 0.0439
-9.250 -0.2147 0.08733 0.08494 -0.0657 0.9780 0.0443
-9.000 -0.1924 0.08478 0.08239 -0.0676 0.9716 0.0447
-8.750 -0.1706 0.08189 0.07949 -0.0708 0.9633 0.0452
-8.500 -0.1447 0.07862 0.07620 -0.0760 0.9562 0.0465
-8.250 -0.1333 0.06598 0.06345 -0.1019 0.9301 0.0501
-8.000 -0.1070 0.06374 0.06116 -0.1033 0.9170 0.0505
-7.750 -0.0835 0.06186 0.05919 -0.1051 0.8989 0.0510
-7.500 -0.0673 0.05996 0.05720 -0.1064 0.8790 0.0516
-7.250 -0.0571 0.05777 0.05490 -0.1077 0.8604 0.0524
-7.000 -0.0840 0.04383 0.04044 -0.1222 0.8365 0.0574
-6.750 -0.0678 0.04242 0.03904 -0.1214 0.8263 0.0578
-6.500 -0.0503 0.04148 0.03805 -0.1207 0.8174 0.0582
-6.250 -0.0327 0.04033 0.03685 -0.1202 0.8084 0.0587
-6.000 -0.0148 0.03896 0.03540 -0.1201 0.8007 0.0594
-5.750 0.0030 0.03713 0.03346 -0.1203 0.7926 0.0605
-5.500 0.0085 0.02962 0.02522 -0.1222 0.7855 0.0665
-5.250 0.0305 0.02858 0.02421 -0.1218 0.7786 0.0672
-5.000 0.0531 0.02774 0.02331 -0.1215 0.7721 0.0680
-4.750 0.0757 0.02680 0.02231 -0.1211 0.7660 0.0692
-4.500 0.0978 0.02540 0.02075 -0.1207 0.7594 0.0716
-4.250 0.1166 0.02279 0.01765 -0.1201 0.7536 0.0771
-4.000 0.1407 0.02190 0.01675 -0.1198 0.7477 0.0782
-3.750 0.1600 0.01729 0.01130 -0.1180 0.7419 0.0635
-3.500 0.1845 0.01596 0.00972 -0.1173 0.7362 0.0623
-3.250 0.2099 0.01500 0.00858 -0.1168 0.7305 0.0617
-3.000 0.2357 0.01427 0.00772 -0.1162 0.7242 0.0617
-2.750 0.2622 0.01371 0.00700 -0.1158 0.7185 0.0619
-2.500 0.2886 0.01328 0.00651 -0.1153 0.7125 0.0626
-2.250 0.3151 0.01287 0.00603 -0.1149 0.7060 0.0632
-2.000 0.3420 0.01251 0.00555 -0.1145 0.7001 0.0636
-1.750 0.3684 0.01214 0.00515 -0.1140 0.6937 0.0640
-1.500 0.3950 0.01184 0.00480 -0.1135 0.6869 0.0644
-1.250 0.4218 0.01160 0.00451 -0.1131 0.6807 0.0649
-1.000 0.4483 0.01138 0.00428 -0.1126 0.6734 0.0653
-0.750 0.4741 0.01096 0.00381 -0.1121 0.6667 0.0662
-0.500 0.4998 0.01062 0.00350 -0.1115 0.6594 0.0677
-0.250 0.5259 0.01043 0.00330 -0.1110 0.6518 0.0690
0.000 0.5520 0.01028 0.00315 -0.1105 0.6444 0.0701
0.250 0.5781 0.01015 0.00301 -0.1099 0.6361 0.0713
0.500 0.6042 0.01005 0.00290 -0.1094 0.6281 0.0728
0.750 0.6302 0.00997 0.00280 -0.1089 0.6192 0.0742
1.000 0.6561 0.00991 0.00272 -0.1083 0.6106 0.0758
1.250 0.6817 0.00981 0.00261 -0.1077 0.6012 0.0796
1.500 0.7075 0.00978 0.00258 -0.1071 0.5917 0.0838
1.750 0.7329 0.00977 0.00254 -0.1065 0.5822 0.0912
2.000 0.7577 0.00958 0.00262 -0.1058 0.5724 0.1765
2.250 0.7797 0.00916 0.00274 -0.1048 0.5634 0.3999
2.500 0.8472 0.00806 0.00296 -0.1136 0.5517 1.0000
2.750 0.8714 0.00819 0.00303 -0.1128 0.5426 1.0000
3.000 0.8950 0.00835 0.00311 -0.1118 0.5333 1.0000
3.250 0.9192 0.00847 0.00320 -0.1109 0.5244 1.0000
3.500 0.9426 0.00866 0.00330 -0.1099 0.5157 1.0000
3.750 0.9668 0.00878 0.00341 -0.1091 0.5067 1.0000
4.000 0.9899 0.00898 0.00353 -0.1080 0.4979 1.0000
4.250 1.0140 0.00911 0.00366 -0.1072 0.4889 1.0000
4.500 1.0371 0.00931 0.00380 -0.1062 0.4806 1.0000
4.750 1.0609 0.00946 0.00394 -0.1053 0.4716 1.0000
5.000 1.0838 0.00967 0.00410 -0.1043 0.4629 1.0000
5.250 1.1069 0.00984 0.00426 -0.1033 0.4532 1.0000
5.500 1.1295 0.01004 0.00443 -0.1022 0.4435 1.0000
5.750 1.1510 0.01028 0.00461 -0.1010 0.4327 1.0000
6.000 1.1739 0.01046 0.00480 -0.1000 0.4227 1.0000
6.250 1.1953 0.01070 0.00500 -0.0987 0.4121 1.0000
6.500 1.2161 0.01095 0.00521 -0.0974 0.4009 1.0000
6.750 1.2378 0.01117 0.00544 -0.0962 0.3903 1.0000
7.000 1.2581 0.01145 0.00568 -0.0948 0.3805 1.0000
7.250 1.2775 0.01174 0.00594 -0.0933 0.3683 1.0000
7.500 1.2965 0.01203 0.00620 -0.0916 0.3545 1.0000
7.750 1.3147 0.01235 0.00649 -0.0899 0.3412 1.0000
8.000 1.3315 0.01269 0.00679 -0.0879 0.3291 1.0000
8.250 1.3458 0.01306 0.00712 -0.0855 0.3170 1.0000
8.500 1.3602 0.01345 0.00748 -0.0831 0.3042 1.0000
8.750 1.3753 0.01383 0.00784 -0.0809 0.2918 1.0000
9.000 1.3891 0.01428 0.00825 -0.0785 0.2790 1.0000
9.250 1.4022 0.01477 0.00871 -0.0762 0.2660 1.0000
9.500 1.4146 0.01532 0.00922 -0.0738 0.2535 1.0000
9.750 1.4267 0.01592 0.00978 -0.0714 0.2407 1.0000
10.000 1.4391 0.01652 0.01036 -0.0692 0.2276 1.0000
10.250 1.4498 0.01724 0.01103 -0.0669 0.2132 1.0000
10.500 1.4581 0.01811 0.01184 -0.0643 0.1964 1.0000
10.750 1.4648 0.01912 0.01277 -0.0617 0.1757 1.0000
11.000 1.4651 0.02058 0.01406 -0.0586 0.1459 1.0000
11.250 1.4570 0.02268 0.01591 -0.0550 0.1082 1.0000
11.500 1.4517 0.02478 0.01785 -0.0520 0.0852 1.0000
11.750 1.4520 0.02660 0.01964 -0.0498 0.0742 1.0000
12.000 1.4545 0.02836 0.02139 -0.0479 0.0675 1.0000
12.250 1.4575 0.03015 0.02320 -0.0462 0.0624 1.0000
12.500 1.4607 0.03198 0.02507 -0.0447 0.0584 1.0000
12.750 1.4645 0.03383 0.02696 -0.0434 0.0548 1.0000
13.000 1.4625 0.03624 0.02940 -0.0420 0.0516 1.0000
13.250 1.4691 0.03794 0.03118 -0.0410 0.0491 1.0000
13.500 1.4707 0.04016 0.03344 -0.0400 0.0467 1.0000
13.750 1.4660 0.04308 0.03640 -0.0389 0.0446 1.0000
14.000 1.4716 0.04504 0.03846 -0.0383 0.0427 1.0000
14.250 1.4739 0.04740 0.04089 -0.0377 0.0410 1.0000
14.500 1.4719 0.05029 0.04381 -0.0371 0.0393 1.0000
14.750 1.4661 0.05368 0.04727 -0.0367 0.0380 1.0000
15.000 1.4685 0.05625 0.04993 -0.0364 0.0368 1.0000
15.250 1.4686 0.05913 0.05290 -0.0363 0.0357 1.0000
15.500 1.4680 0.06217 0.05601 -0.0363 0.0346 1.0000
15.750 1.4625 0.06587 0.05976 -0.0364 0.0336 1.0000
16.000 1.4529 0.07016 0.06413 -0.0367 0.0328 1.0000
16.250 1.4538 0.07320 0.06726 -0.0369 0.0320 1.0000
16.500 1.4522 0.07660 0.07075 -0.0373 0.0311 1.0000
16.750 1.4501 0.08011 0.07434 -0.0378 0.0303 1.0000
17.000 1.4468 0.08382 0.07813 -0.0384 0.0297 1.0000
17.250 1.4419 0.08781 0.08218 -0.0392 0.0291 1.0000
17.500 1.4348 0.09213 0.08655 -0.0401 0.0285 1.0000
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