GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 500,000 Max Cl/Cd: 99.17 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe358-il-500000-n5.txt Download as CSV file: xf-goe358-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 358 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5592 0.08645 0.08382 -0.0513 1.0000 0.0146
-12.000 -0.6417 0.07043 0.06768 -0.0594 1.0000 0.0141
-11.750 -0.7059 0.06265 0.05985 -0.0590 1.0000 0.0137
-11.500 -0.7261 0.04649 0.04338 -0.0819 0.9939 0.0136
-11.250 -0.6999 0.03491 0.03146 -0.1047 0.9884 0.0139
-11.000 -0.6591 0.02817 0.02443 -0.1200 0.9864 0.0146
-10.750 -0.6185 0.02400 0.02000 -0.1297 0.9853 0.0153
-10.500 -0.5835 0.02147 0.01723 -0.1350 0.9832 0.0161
-10.250 -0.5499 0.01962 0.01521 -0.1389 0.9812 0.0171
-10.000 -0.5163 0.01837 0.01384 -0.1417 0.9796 0.0184
-9.750 -0.4823 0.01738 0.01270 -0.1441 0.9781 0.0198
-9.500 -0.4478 0.01640 0.01164 -0.1465 0.9770 0.0215
-9.250 -0.4137 0.01565 0.01079 -0.1485 0.9759 0.0235
-9.000 -0.3821 0.01503 0.01010 -0.1498 0.9738 0.0258
-8.750 -0.3516 0.01460 0.00964 -0.1507 0.9707 0.0286
-8.500 -0.3194 0.01418 0.00916 -0.1518 0.9683 0.0313
-8.250 -0.2867 0.01395 0.00893 -0.1529 0.9663 0.0340
-8.000 -0.2543 0.01371 0.00862 -0.1538 0.9642 0.0366
-7.750 -0.2256 0.01349 0.00832 -0.1540 0.9595 0.0382
-7.500 -0.1941 0.01313 0.00794 -0.1548 0.9560 0.0403
-7.250 -0.1624 0.01294 0.00771 -0.1556 0.9525 0.0422
-7.000 -0.1339 0.01273 0.00746 -0.1556 0.9457 0.0441
-6.750 -0.1026 0.01248 0.00713 -0.1562 0.9405 0.0459
-6.500 -0.0743 0.01228 0.00686 -0.1562 0.9324 0.0473
-6.250 -0.0446 0.01211 0.00661 -0.1564 0.9251 0.0481
-6.000 -0.0155 0.01158 0.00600 -0.1567 0.9151 0.0499
-5.750 0.0134 0.01118 0.00555 -0.1568 0.9030 0.0516
-5.500 0.0421 0.01091 0.00520 -0.1569 0.8890 0.0530
-5.250 0.0708 0.01066 0.00486 -0.1569 0.8723 0.0543
-5.000 0.0990 0.01046 0.00453 -0.1567 0.8510 0.0556
-4.750 0.1270 0.01028 0.00420 -0.1565 0.8264 0.0566
-4.500 0.1550 0.01014 0.00390 -0.1563 0.8026 0.0575
-4.250 0.1832 0.01002 0.00364 -0.1562 0.7834 0.0584
-3.750 0.2398 0.00986 0.00324 -0.1561 0.7524 0.0600
-3.500 0.2684 0.00977 0.00305 -0.1561 0.7393 0.0607
-3.250 0.2971 0.00963 0.00281 -0.1561 0.7267 0.0621
-3.000 0.3256 0.00954 0.00262 -0.1561 0.7144 0.0636
-2.750 0.3542 0.00947 0.00247 -0.1561 0.7020 0.0653
-2.500 0.3828 0.00940 0.00235 -0.1562 0.6903 0.0671
-2.250 0.4114 0.00936 0.00224 -0.1561 0.6791 0.0693
-2.000 0.4398 0.00934 0.00215 -0.1561 0.6672 0.0720
-1.750 0.4683 0.00929 0.00207 -0.1561 0.6544 0.0779
-1.500 0.4970 0.00914 0.00198 -0.1562 0.6409 0.1069
-1.250 0.5255 0.00898 0.00190 -0.1563 0.6258 0.1592
-1.000 0.5538 0.00882 0.00187 -0.1565 0.6089 0.2250
-0.750 0.5814 0.00886 0.00191 -0.1563 0.5900 0.2573
-0.500 0.6088 0.00897 0.00195 -0.1561 0.5694 0.2752
-0.250 0.6361 0.00910 0.00202 -0.1558 0.5489 0.2910
0.000 0.6632 0.00927 0.00209 -0.1555 0.5262 0.3012
0.250 0.6901 0.00946 0.00217 -0.1552 0.5036 0.3088
0.500 0.7172 0.00963 0.00226 -0.1549 0.4842 0.3164
0.750 0.7444 0.00979 0.00234 -0.1547 0.4676 0.3226
1.000 0.7717 0.00994 0.00245 -0.1544 0.4527 0.3303
1.250 0.7989 0.01010 0.00255 -0.1542 0.4386 0.3382
1.500 0.8261 0.01024 0.00268 -0.1539 0.4248 0.3453
1.750 0.8531 0.01043 0.00280 -0.1537 0.4102 0.3528
2.000 0.8800 0.01060 0.00293 -0.1534 0.3967 0.3590
2.250 0.9070 0.01077 0.00307 -0.1531 0.3865 0.3647
2.500 0.9343 0.01090 0.00319 -0.1529 0.3785 0.3696
2.750 0.9612 0.01106 0.00333 -0.1526 0.3714 0.3734
3.000 0.9884 0.01118 0.00347 -0.1524 0.3645 0.3773
3.500 1.0420 0.01151 0.00379 -0.1518 0.3488 0.3856
3.750 1.0687 0.01167 0.00395 -0.1515 0.3429 0.3896
4.000 1.0953 0.01184 0.00414 -0.1512 0.3380 0.3938
4.250 1.1223 0.01196 0.00431 -0.1509 0.3340 0.3989
4.500 1.1490 0.01211 0.00449 -0.1506 0.3296 0.4042
4.750 1.1751 0.01231 0.00470 -0.1502 0.3233 0.4092
5.000 1.2014 0.01247 0.00490 -0.1499 0.3162 0.4146
5.250 1.2275 0.01267 0.00511 -0.1495 0.3091 0.4201
5.500 1.2533 0.01287 0.00535 -0.1491 0.3039 0.4255
5.750 1.2797 0.01301 0.00557 -0.1487 0.2983 0.4319
6.000 1.3051 0.01324 0.00582 -0.1482 0.2904 0.4387
6.250 1.3309 0.01342 0.00607 -0.1478 0.2839 0.4463
6.500 1.3558 0.01368 0.00633 -0.1473 0.2714 0.4539
6.750 1.3775 0.01422 0.00669 -0.1463 0.2246 0.4617
7.250 1.4133 0.01605 0.00808 -0.1432 0.1452 0.4792
7.500 1.4355 0.01651 0.00856 -0.1423 0.1319 0.4912
7.750 1.4557 0.01713 0.00911 -0.1411 0.1099 0.5057
8.000 1.4729 0.01798 0.00982 -0.1395 0.0803 0.5240
8.250 1.4920 0.01860 0.01048 -0.1381 0.0684 0.5568
8.500 1.5078 0.01859 0.01104 -0.1360 0.0616 1.0000
8.750 1.5267 0.01920 0.01165 -0.1345 0.0556 1.0000
9.000 1.5457 0.01975 0.01222 -0.1331 0.0507 1.0000
9.250 1.5627 0.02041 0.01288 -0.1314 0.0435 1.0000
9.500 1.5786 0.02108 0.01354 -0.1295 0.0362 1.0000
9.750 1.5907 0.02185 0.01428 -0.1269 0.0300 1.0000
10.000 1.6018 0.02267 0.01510 -0.1243 0.0256 1.0000
10.250 1.6137 0.02348 0.01594 -0.1219 0.0229 1.0000
10.500 1.6235 0.02443 0.01693 -0.1192 0.0206 1.0000
10.750 1.6347 0.02532 0.01789 -0.1169 0.0190 1.0000
11.000 1.6443 0.02635 0.01896 -0.1145 0.0177 1.0000
11.250 1.6520 0.02754 0.02021 -0.1120 0.0165 1.0000
11.500 1.6611 0.02868 0.02142 -0.1098 0.0157 1.0000
11.750 1.6691 0.02994 0.02276 -0.1076 0.0148 1.0000
12.000 1.6756 0.03137 0.02427 -0.1055 0.0141 1.0000
12.250 1.6801 0.03303 0.02600 -0.1033 0.0134 1.0000
12.500 1.6851 0.03474 0.02781 -0.1014 0.0129 1.0000
12.750 1.6900 0.03654 0.02970 -0.0997 0.0124 1.0000
13.000 1.6936 0.03854 0.03180 -0.0982 0.0119 1.0000
13.250 1.6959 0.04077 0.03413 -0.0968 0.0115 1.0000
13.500 1.6968 0.04327 0.03671 -0.0955 0.0111 1.0000
13.750 1.6957 0.04606 0.03960 -0.0945 0.0108 1.0000
14.000 1.6921 0.04928 0.04292 -0.0936 0.0105 1.0000
14.250 1.6910 0.05232 0.04608 -0.0930 0.0103 1.0000
14.500 1.6885 0.05560 0.04948 -0.0925 0.0101 1.0000
14.750 1.6846 0.05917 0.05317 -0.0923 0.0098 1.0000
15.000 1.6803 0.06292 0.05704 -0.0923 0.0096 1.0000
15.250 1.6748 0.06694 0.06119 -0.0924 0.0094 1.0000
15.500 1.6681 0.07120 0.06556 -0.0928 0.0092 1.0000
15.750 1.6611 0.07562 0.07010 -0.0933 0.0090 1.0000
16.000 1.6530 0.08031 0.07490 -0.0940 0.0089 1.0000
16.250 1.6439 0.08522 0.07992 -0.0949 0.0087 1.0000
16.500 1.6334 0.09041 0.08522 -0.0960 0.0086 1.0000
16.750 1.6223 0.09579 0.09071 -0.0973 0.0084 1.0000
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