GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 499 AIRFOIL (goe499-il) Reynolds number: 50,000 Max Cl/Cd: 44.92 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe499-il-50000-n5.txt Download as CSV file: xf-goe499-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 499 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3593 0.11573 0.10945 -0.0266 1.0000 0.0997
-7.500 -0.3757 0.11581 0.10965 -0.0247 1.0000 0.1002
-7.250 -0.3892 0.11543 0.10938 -0.0239 1.0000 0.1006
-7.000 -0.3967 0.11436 0.10840 -0.0249 1.0000 0.1009
-6.750 -0.3831 0.10782 0.10185 -0.0202 1.0000 0.1030
-6.500 -0.3815 0.10505 0.09909 -0.0184 1.0000 0.1057
-6.250 -0.3838 0.10307 0.09717 -0.0176 1.0000 0.1101
-6.000 -0.3895 0.10209 0.09627 -0.0205 1.0000 0.1143
-5.750 -0.3873 0.10012 0.09438 -0.0262 1.0000 0.1155
-5.500 -0.3809 0.09556 0.08980 -0.0194 0.9991 0.1197
-5.250 -0.3621 0.09184 0.08601 -0.0237 0.9949 0.1238
-5.000 -0.3290 0.08798 0.08205 -0.0383 0.9888 0.1293
-4.750 -0.2983 0.08320 0.07718 -0.0475 0.9847 0.1299
-4.250 -0.2380 0.06983 0.06349 -0.0604 0.9779 0.0846
-4.000 -0.2059 0.06505 0.05857 -0.0667 0.9745 0.0802
-3.750 -0.1275 0.05431 0.04724 -0.0895 0.9728 0.0737
-3.500 -0.1076 0.05360 0.04653 -0.0891 0.9688 0.0790
-3.250 -0.0506 0.04815 0.04058 -0.1006 0.9670 0.0804
-3.000 0.0148 0.04186 0.03353 -0.1135 0.9663 0.0776
-2.750 0.0721 0.03734 0.02815 -0.1225 0.9654 0.0764
-2.500 0.1148 0.03472 0.02486 -0.1270 0.9627 0.0764
-2.250 0.1529 0.03303 0.02265 -0.1300 0.9591 0.0772
-2.000 0.1915 0.03177 0.02096 -0.1327 0.9555 0.0789
-1.750 0.2306 0.03082 0.01962 -0.1353 0.9512 0.0817
-1.500 0.2662 0.03007 0.01847 -0.1369 0.9443 0.0856
-1.250 0.3096 0.02956 0.01779 -0.1401 0.9387 0.0941
-1.000 0.3429 0.02923 0.01734 -0.1414 0.9299 0.1107
-0.750 0.3864 0.02872 0.01681 -0.1445 0.9243 0.1448
-0.500 0.4182 0.02844 0.01668 -0.1455 0.9159 0.2085
-0.250 0.4565 0.02838 0.01677 -0.1478 0.9102 0.2956
0.000 0.4845 0.02830 0.01689 -0.1482 0.9017 0.3613
0.250 0.5228 0.02807 0.01697 -0.1502 0.8966 0.4424
0.500 0.5482 0.02794 0.01710 -0.1498 0.8876 0.5307
0.750 0.5732 0.02702 0.01691 -0.1487 0.8804 0.8653
1.000 0.6040 0.02723 0.01685 -0.1494 0.8717 1.0000
1.250 0.6329 0.02752 0.01696 -0.1497 0.8624 1.0000
1.500 0.6708 0.02765 0.01695 -0.1514 0.8560 1.0000
1.750 0.6965 0.02796 0.01718 -0.1511 0.8453 1.0000
2.000 0.7255 0.02820 0.01736 -0.1513 0.8356 1.0000
2.250 0.7625 0.02822 0.01739 -0.1526 0.8285 1.0000
2.500 0.7878 0.02851 0.01769 -0.1522 0.8170 1.0000
2.750 0.8149 0.02874 0.01796 -0.1519 0.8059 1.0000
3.000 0.8474 0.02879 0.01811 -0.1525 0.7969 1.0000
3.250 0.8786 0.02884 0.01826 -0.1527 0.7870 1.0000
3.500 0.9039 0.02909 0.01862 -0.1521 0.7746 1.0000
3.750 0.9303 0.02930 0.01897 -0.1516 0.7625 1.0000
4.000 0.9584 0.02945 0.01933 -0.1513 0.7511 1.0000
4.250 0.9944 0.02928 0.01939 -0.1521 0.7428 1.0000
4.500 1.0190 0.02957 0.01989 -0.1513 0.7297 1.0000
4.750 1.0438 0.02987 0.02047 -0.1505 0.7168 1.0000
5.000 1.0692 0.03017 0.02105 -0.1498 0.7042 1.0000
5.250 1.0993 0.02892 0.02007 -0.1476 0.6776 1.0000
5.500 1.1292 0.02651 0.01767 -0.1433 0.6127 1.0000
5.750 1.1559 0.02573 0.01634 -0.1393 0.5038 1.0000
6.000 1.1534 0.02745 0.01703 -0.1335 0.3373 1.0000
6.250 1.1336 0.03185 0.01930 -0.1278 0.0922 1.0000
6.500 1.1421 0.03408 0.02128 -0.1253 0.0593 1.0000
6.750 1.1522 0.03594 0.02322 -0.1229 0.0518 1.0000
7.000 1.1609 0.03785 0.02528 -0.1204 0.0470 1.0000
7.250 1.1691 0.03974 0.02735 -0.1180 0.0427 1.0000
7.500 1.1743 0.04193 0.02968 -0.1155 0.0397 1.0000
7.750 1.1802 0.04415 0.03207 -0.1130 0.0383 1.0000
8.000 1.1903 0.04614 0.03438 -0.1107 0.0372 1.0000
8.250 1.2069 0.04801 0.03648 -0.1088 0.0359 1.0000
8.500 1.2339 0.04976 0.03842 -0.1075 0.0336 1.0000
8.750 1.2835 0.05239 0.04101 -0.1090 0.0303 1.0000
9.000 1.3423 0.05627 0.04522 -0.1119 0.0295 1.0000
9.250 1.3719 0.05999 0.04937 -0.1117 0.0293 1.0000
9.500 1.3905 0.06378 0.05360 -0.1104 0.0293 1.0000
9.750 1.4001 0.06747 0.05784 -0.1082 0.0292 1.0000
10.000 1.4025 0.07105 0.06186 -0.1055 0.0290 1.0000
10.250 1.3983 0.07451 0.06572 -0.1022 0.0288 1.0000
10.500 1.3900 0.07797 0.06955 -0.0989 0.0286 1.0000
10.750 1.3788 0.08161 0.07353 -0.0958 0.0285 1.0000
11.000 1.3649 0.08546 0.07770 -0.0932 0.0284 1.0000
11.250 1.3499 0.08964 0.08218 -0.0913 0.0285 1.0000
11.500 1.3334 0.09411 0.08693 -0.0900 0.0285 1.0000
11.750 1.3166 0.09892 0.09199 -0.0895 0.0286 1.0000
12.000 1.2984 0.10412 0.09743 -0.0898 0.0287 1.0000
12.250 1.2801 0.10973 0.10325 -0.0910 0.0288 1.0000
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Polar data table (+)
Polar graphs
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