GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 481A AIRFOIL (goe481a-il) Reynolds number: 500,000 Max Cl/Cd: 80.16 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe481a-il-500000.txt Download as CSV file: xf-goe481a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 481A 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0691 0.09413 0.09144 -0.0901 0.9522 0.0597
-8.500 -0.0586 0.09112 0.08843 -0.0923 0.9496 0.0609
-8.250 -0.3908 0.03184 0.02769 -0.1188 0.9190 0.0560
-8.000 -0.3763 0.02836 0.02371 -0.1189 0.9174 0.0566
-7.750 -0.3784 0.02719 0.02231 -0.1138 0.9086 0.0569
-7.500 -0.3555 0.02563 0.02046 -0.1135 0.9060 0.0572
-7.250 -0.3304 0.02373 0.01830 -0.1137 0.9044 0.0577
-7.000 -0.3008 0.02225 0.01673 -0.1144 0.9033 0.0582
-6.750 -0.2684 0.02120 0.01561 -0.1154 0.9024 0.0586
-6.500 -0.2612 0.02083 0.01520 -0.1112 0.8940 0.0591
-6.250 -0.2316 0.01997 0.01426 -0.1115 0.8915 0.0596
-6.000 -0.1991 0.01912 0.01334 -0.1122 0.8899 0.0602
-5.750 -0.1657 0.01829 0.01243 -0.1131 0.8886 0.0609
-5.500 -0.1308 0.01747 0.01151 -0.1143 0.8876 0.0619
-5.250 -0.0937 0.01667 0.01060 -0.1159 0.8865 0.0626
-5.000 -0.0834 0.01639 0.01024 -0.1120 0.8775 0.0629
-4.750 -0.0521 0.01555 0.00931 -0.1124 0.8743 0.0636
-4.500 -0.0154 0.01464 0.00840 -0.1139 0.8718 0.0645
-4.250 0.0256 0.01392 0.00768 -0.1163 0.8695 0.0655
-4.000 0.0361 0.01369 0.00743 -0.1124 0.8580 0.0660
-3.750 0.0778 0.01305 0.00674 -0.1148 0.8530 0.0673
-3.500 0.0951 0.01278 0.00643 -0.1122 0.8399 0.0680
-3.250 0.1297 0.01236 0.00594 -0.1132 0.8296 0.0691
-3.000 0.1647 0.01183 0.00535 -0.1144 0.8165 0.0705
-2.750 0.1933 0.01149 0.00498 -0.1143 0.7986 0.0720
-2.500 0.2226 0.01126 0.00466 -0.1142 0.7759 0.0734
-2.250 0.2496 0.01111 0.00437 -0.1137 0.7491 0.0748
-2.000 0.2727 0.01110 0.00417 -0.1123 0.7213 0.0763
-1.750 0.2898 0.01102 0.00401 -0.1098 0.6964 0.0781
-1.500 0.3070 0.01105 0.00394 -0.1073 0.6749 0.0800
-1.250 0.3244 0.01110 0.00388 -0.1049 0.6561 0.0822
-1.000 0.3418 0.01113 0.00383 -0.1025 0.6395 0.0853
-0.750 0.3599 0.01117 0.00382 -0.1002 0.6248 0.0891
-0.500 0.3789 0.01118 0.00381 -0.0981 0.6124 0.0937
-0.250 0.3986 0.01125 0.00383 -0.0962 0.6011 0.1010
0.000 0.4193 0.01131 0.00391 -0.0945 0.5909 0.1112
0.250 0.4409 0.01148 0.00403 -0.0930 0.5811 0.1214
0.500 0.4629 0.01162 0.00419 -0.0916 0.5719 0.1295
1.000 0.5045 0.01188 0.00439 -0.0883 0.5526 0.1408
1.250 0.5260 0.01207 0.00448 -0.0868 0.5439 0.1448
1.500 0.5465 0.01204 0.00448 -0.0852 0.5362 0.1494
1.750 0.5676 0.01212 0.00455 -0.0836 0.5282 0.1535
2.000 0.5881 0.01227 0.00462 -0.0820 0.5201 0.1571
2.250 0.6082 0.01229 0.00465 -0.0802 0.5120 0.1602
2.500 0.6273 0.01233 0.00468 -0.0783 0.5041 0.1646
2.750 0.6477 0.01241 0.00476 -0.0767 0.4966 0.1683
3.000 0.6683 0.01249 0.00482 -0.0751 0.4889 0.1720
3.250 0.6876 0.01262 0.00489 -0.0733 0.4812 0.1755
3.500 0.7084 0.01261 0.00495 -0.0717 0.4743 0.1812
3.750 0.7281 0.01271 0.00503 -0.0700 0.4664 0.1858
4.000 0.7477 0.01285 0.00514 -0.0683 0.4593 0.1897
4.250 0.7677 0.01291 0.00523 -0.0666 0.4517 0.1947
4.500 0.7865 0.01304 0.00534 -0.0648 0.4441 0.1994
4.750 0.8068 0.01315 0.00547 -0.0632 0.4369 0.2048
5.000 0.8267 0.01327 0.00560 -0.0617 0.4291 0.2120
5.250 1.0174 0.01274 0.00685 -0.0982 0.4088 1.0000
5.500 1.0365 0.01300 0.00703 -0.0965 0.4014 1.0000
5.750 1.0573 0.01319 0.00721 -0.0950 0.3944 1.0000
6.000 1.0760 0.01347 0.00742 -0.0933 0.3875 1.0000
6.250 1.0957 0.01372 0.00764 -0.0917 0.3810 1.0000
6.500 1.1160 0.01395 0.00785 -0.0903 0.3746 1.0000
6.750 1.1343 0.01427 0.00811 -0.0886 0.3679 1.0000
7.000 1.1543 0.01453 0.00835 -0.0871 0.3614 1.0000
7.250 1.1736 0.01481 0.00861 -0.0856 0.3546 1.0000
7.500 1.1898 0.01522 0.00894 -0.0836 0.3470 1.0000
7.750 1.2103 0.01546 0.00921 -0.0823 0.3405 1.0000
8.000 1.2285 0.01581 0.00952 -0.0806 0.3338 1.0000
8.250 1.2458 0.01620 0.00987 -0.0789 0.3278 1.0000
8.500 1.2655 0.01649 0.01019 -0.0775 0.3219 1.0000
8.750 1.2825 0.01689 0.01057 -0.0758 0.3152 1.0000
9.000 1.2994 0.01731 0.01097 -0.0741 0.3083 1.0000
9.250 1.3175 0.01768 0.01135 -0.0726 0.3010 1.0000
9.500 1.3311 0.01825 0.01186 -0.0704 0.2927 1.0000
9.750 1.3493 0.01863 0.01226 -0.0690 0.2843 1.0000
10.000 1.3623 0.01926 0.01283 -0.0668 0.2754 1.0000
10.250 1.3790 0.01972 0.01331 -0.0653 0.2660 1.0000
10.500 1.3918 0.02039 0.01394 -0.0632 0.2566 1.0000
10.750 1.4054 0.02103 0.01456 -0.0613 0.2459 1.0000
11.000 1.4171 0.02179 0.01528 -0.0592 0.2348 1.0000
11.250 1.4270 0.02267 0.01611 -0.0569 0.2242 1.0000
11.500 1.4369 0.02356 0.01697 -0.0547 0.2139 1.0000
11.750 1.4469 0.02448 0.01787 -0.0527 0.2058 1.0000
12.000 1.4558 0.02550 0.01886 -0.0505 0.1989 1.0000
12.250 1.4649 0.02653 0.01988 -0.0485 0.1931 1.0000
12.500 1.4749 0.02753 0.02091 -0.0466 0.1885 1.0000
12.750 1.4827 0.02869 0.02207 -0.0446 0.1841 1.0000
13.000 1.4885 0.03003 0.02341 -0.0426 0.1802 1.0000
13.250 1.5004 0.03101 0.02444 -0.0411 0.1774 1.0000
13.500 1.5093 0.03221 0.02569 -0.0395 0.1742 1.0000
13.750 1.5162 0.03358 0.02708 -0.0379 0.1712 1.0000
14.000 1.5203 0.03521 0.02872 -0.0361 0.1680 1.0000
14.250 1.5269 0.03670 0.03026 -0.0346 0.1651 1.0000
14.500 1.5369 0.03797 0.03160 -0.0335 0.1623 1.0000
14.750 1.5436 0.03953 0.03322 -0.0323 0.1594 1.0000
15.000 1.5454 0.04156 0.03526 -0.0309 0.1556 1.0000
15.250 1.5459 0.04374 0.03746 -0.0295 0.1526 1.0000
15.500 1.5564 0.04512 0.03893 -0.0289 0.1492 1.0000
15.750 1.5611 0.04705 0.04092 -0.0280 0.1452 1.0000
16.000 1.5612 0.04947 0.04336 -0.0271 0.1418 1.0000
16.250 1.5627 0.05179 0.04574 -0.0263 0.1383 1.0000
16.500 1.5689 0.05370 0.04772 -0.0258 0.1337 1.0000
16.750 1.5677 0.05640 0.05045 -0.0252 0.1295 1.0000
17.000 1.5677 0.05902 0.05312 -0.0247 0.1253 1.0000
17.250 1.5683 0.06163 0.05578 -0.0244 0.1204 1.0000
17.500 1.5620 0.06504 0.05922 -0.0241 0.1155 1.0000
17.750 1.5602 0.06797 0.06220 -0.0239 0.1102 1.0000
18.000 1.5535 0.07151 0.06577 -0.0238 0.1065 1.0000
18.250 1.5484 0.07493 0.06923 -0.0239 0.1025 1.0000
18.500 1.5407 0.07869 0.07304 -0.0240 0.0991 1.0000
18.750 1.5307 0.08277 0.07714 -0.0243 0.0965 1.0000
19.000 1.5267 0.08612 0.08056 -0.0245 0.0941 1.0000
19.250 1.5201 0.08986 0.08436 -0.0249 0.0920 1.0000
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