GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 410 AIRFOIL (goe410-il) Reynolds number: 50,000 Max Cl/Cd: 25.16 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe410-il-50000-n5.txt Download as CSV file: xf-goe410-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 410 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6540 0.12458 0.11571 0.0045 1.0000 0.1383
-13.000 -0.6593 0.11919 0.11031 0.0020 1.0000 0.1417
-12.500 -0.9275 0.06803 0.05861 -0.0297 1.0000 0.1470
-12.250 -0.8655 0.07144 0.06225 -0.0260 1.0000 0.1512
-12.000 -0.9054 0.06393 0.05455 -0.0293 1.0000 0.1528
-11.750 -0.9289 0.05900 0.04943 -0.0305 1.0000 0.1546
-11.500 -0.9472 0.05506 0.04529 -0.0305 1.0000 0.1566
-11.250 -0.9622 0.05185 0.04185 -0.0295 1.0000 0.1587
-11.000 -0.9754 0.04913 0.03886 -0.0275 1.0000 0.1610
-10.750 -0.9752 0.04681 0.03632 -0.0261 1.0000 0.1636
-10.500 -0.9496 0.04554 0.03515 -0.0259 1.0000 0.1671
-10.250 -0.9351 0.04394 0.03349 -0.0250 1.0000 0.1704
-10.000 -0.9243 0.04222 0.03161 -0.0240 1.0000 0.1740
-9.750 -0.9156 0.04043 0.02958 -0.0228 1.0000 0.1778
-9.500 -0.8942 0.03916 0.02835 -0.0222 1.0000 0.1817
-9.250 -0.8738 0.03801 0.02724 -0.0215 1.0000 0.1860
-9.000 -0.8569 0.03671 0.02586 -0.0206 1.0000 0.1905
-8.750 -0.8405 0.03541 0.02444 -0.0197 1.0000 0.1954
-8.500 -0.8198 0.03447 0.02363 -0.0188 1.0000 0.2006
-8.250 -0.8024 0.03340 0.02254 -0.0178 1.0000 0.2069
-8.000 -0.7845 0.03238 0.02154 -0.0168 1.0000 0.2131
-7.750 -0.7666 0.03146 0.02070 -0.0157 1.0000 0.2199
-7.500 -0.7497 0.03050 0.01977 -0.0145 1.0000 0.2282
-7.250 -0.7331 0.02966 0.01904 -0.0132 1.0000 0.2375
-7.000 -0.7170 0.02883 0.01833 -0.0118 1.0000 0.2481
-6.750 -0.7011 0.02803 0.01762 -0.0104 1.0000 0.2610
-6.500 -0.6859 0.02730 0.01704 -0.0088 1.0000 0.2765
-6.250 -0.6712 0.02668 0.01658 -0.0070 1.0000 0.2942
-6.000 -0.6572 0.02618 0.01627 -0.0051 1.0000 0.3139
-5.750 -0.6443 0.02581 0.01606 -0.0029 1.0000 0.3352
-5.500 -0.6329 0.02555 0.01592 -0.0005 1.0000 0.3567
-5.250 -0.6240 0.02538 0.01582 0.0021 1.0000 0.3767
-5.000 -0.5912 0.02535 0.01582 0.0006 0.9819 0.4016
-4.750 -0.5478 0.02543 0.01590 -0.0024 0.9594 0.4254
-4.500 -0.5047 0.02545 0.01586 -0.0053 0.9380 0.4469
-4.250 -0.4633 0.02544 0.01580 -0.0077 0.9171 0.4647
-4.000 -0.4263 0.02539 0.01569 -0.0091 0.8948 0.4803
-3.750 -0.3922 0.02529 0.01548 -0.0100 0.8732 0.4954
-3.500 -0.3614 0.02522 0.01531 -0.0102 0.8528 0.5108
-3.250 -0.3309 0.02538 0.01548 -0.0097 0.8334 0.5241
-3.000 -0.3039 0.02540 0.01545 -0.0089 0.8149 0.5376
-2.750 -0.2795 0.02533 0.01527 -0.0080 0.7975 0.5519
-2.500 -0.2527 0.02544 0.01538 -0.0069 0.7814 0.5631
-2.250 -0.2281 0.02537 0.01523 -0.0059 0.7664 0.5748
-2.000 -0.2037 0.02532 0.01514 -0.0049 0.7509 0.5853
-1.750 -0.1790 0.02521 0.01499 -0.0041 0.7367 0.5946
-1.500 -0.1533 0.02512 0.01482 -0.0034 0.7243 0.6033
-1.250 -0.1287 0.02496 0.01460 -0.0028 0.7116 0.6122
-1.000 -0.1028 0.02492 0.01456 -0.0021 0.6994 0.6202
-0.750 -0.0777 0.02476 0.01430 -0.0016 0.6892 0.6302
-0.500 -0.0517 0.02479 0.01438 -0.0010 0.6774 0.6380
0.000 0.0000 0.02474 0.01430 0.0000 0.6570 0.6570
0.500 0.0517 0.02479 0.01438 0.0010 0.6380 0.6774
0.750 0.0777 0.02476 0.01429 0.0016 0.6302 0.6891
1.000 0.1028 0.02492 0.01456 0.0021 0.6202 0.6994
1.250 0.1287 0.02496 0.01460 0.0028 0.6122 0.7117
1.500 0.1534 0.02511 0.01482 0.0034 0.6033 0.7243
1.750 0.1790 0.02521 0.01499 0.0041 0.5945 0.7367
2.000 0.2037 0.02532 0.01514 0.0049 0.5853 0.7509
2.250 0.2281 0.02536 0.01523 0.0059 0.5748 0.7664
2.500 0.2527 0.02544 0.01538 0.0069 0.5630 0.7814
2.750 0.2795 0.02533 0.01527 0.0080 0.5520 0.7976
3.000 0.3039 0.02540 0.01545 0.0089 0.5376 0.8149
3.250 0.3309 0.02537 0.01548 0.0097 0.5241 0.8334
3.500 0.3614 0.02522 0.01531 0.0102 0.5108 0.8528
3.750 0.3922 0.02528 0.01548 0.0100 0.4954 0.8732
4.000 0.4263 0.02539 0.01569 0.0091 0.4804 0.8948
4.250 0.4633 0.02544 0.01580 0.0076 0.4647 0.9172
4.500 0.5047 0.02545 0.01586 0.0053 0.4468 0.9380
4.750 0.5478 0.02543 0.01590 0.0024 0.4254 0.9594
5.000 0.5913 0.02534 0.01581 -0.0006 0.4016 0.9819
5.250 0.6239 0.02537 0.01582 -0.0021 0.3767 1.0000
5.500 0.6329 0.02555 0.01591 0.0005 0.3568 1.0000
5.750 0.6442 0.02581 0.01606 0.0029 0.3352 1.0000
6.000 0.6571 0.02618 0.01627 0.0051 0.3139 1.0000
6.250 0.6712 0.02668 0.01658 0.0070 0.2943 1.0000
6.500 0.6859 0.02730 0.01703 0.0088 0.2765 1.0000
6.750 0.7011 0.02803 0.01762 0.0103 0.2610 1.0000
7.000 0.7170 0.02883 0.01833 0.0118 0.2481 1.0000
7.250 0.7332 0.02966 0.01903 0.0132 0.2376 1.0000
7.500 0.7498 0.03050 0.01977 0.0145 0.2282 1.0000
7.750 0.7668 0.03146 0.02070 0.0156 0.2200 1.0000
8.000 0.7846 0.03238 0.02154 0.0168 0.2131 1.0000
8.250 0.8026 0.03340 0.02254 0.0178 0.2069 1.0000
8.500 0.8200 0.03446 0.02362 0.0188 0.2006 1.0000
8.750 0.8407 0.03541 0.02443 0.0196 0.1954 1.0000
9.000 0.8571 0.03671 0.02586 0.0206 0.1905 1.0000
9.250 0.8741 0.03801 0.02724 0.0215 0.1860 1.0000
9.500 0.8945 0.03916 0.02835 0.0222 0.1817 1.0000
9.750 0.9157 0.04043 0.02958 0.0227 0.1778 1.0000
10.000 0.9245 0.04222 0.03161 0.0240 0.1740 1.0000
10.250 0.9354 0.04394 0.03349 0.0250 0.1704 1.0000
10.500 0.9500 0.04553 0.03513 0.0258 0.1671 1.0000
10.750 0.9759 0.04680 0.03630 0.0260 0.1636 1.0000
11.000 0.9757 0.04913 0.03886 0.0274 0.1610 1.0000
11.250 0.9630 0.05184 0.04184 0.0294 0.1588 1.0000
11.500 0.9478 0.05506 0.04529 0.0305 0.1565 1.0000
11.750 0.9298 0.05898 0.04941 0.0305 0.1546 1.0000
12.000 0.9073 0.06382 0.05443 0.0293 0.1527 1.0000
12.250 0.8824 0.06955 0.06031 0.0272 0.1508 1.0000
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