RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 50,000 Max Cl/Cd: 30.42 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5212-il-50000-n5.txt Download as CSV file: xf-rae5212-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5212 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4977 0.10840 0.10050 -0.0430 1.0000 0.0574
-11.000 -0.4972 0.10425 0.09639 -0.0439 1.0000 0.0569
-10.750 -0.4993 0.09969 0.09188 -0.0452 1.0000 0.0564
-10.500 -0.5047 0.09450 0.08674 -0.0472 1.0000 0.0559
-10.250 -0.5143 0.08883 0.08111 -0.0498 1.0000 0.0553
-10.000 -0.5298 0.08307 0.07540 -0.0526 1.0000 0.0546
-9.750 -0.5514 0.07761 0.06996 -0.0550 1.0000 0.0541
-9.500 -0.5760 0.07315 0.06551 -0.0560 1.0000 0.0535
-9.250 -0.6027 0.06966 0.06201 -0.0549 1.0000 0.0531
-9.000 -0.6231 0.06613 0.05838 -0.0535 1.0000 0.0528
-8.750 -0.6391 0.06269 0.05479 -0.0518 1.0000 0.0526
-8.500 -0.6501 0.05939 0.05130 -0.0499 1.0000 0.0525
-8.250 -0.6565 0.05624 0.04790 -0.0479 1.0000 0.0529
-8.000 -0.6588 0.05326 0.04465 -0.0460 1.0000 0.0537
-7.750 -0.6580 0.05035 0.04137 -0.0440 1.0000 0.0547
-7.500 -0.6542 0.04750 0.03810 -0.0421 1.0000 0.0559
-7.250 -0.6466 0.04478 0.03492 -0.0402 1.0000 0.0569
-7.000 -0.6354 0.04225 0.03201 -0.0385 1.0000 0.0576
-6.750 -0.6210 0.04004 0.02966 -0.0371 1.0000 0.0587
-6.500 -0.6056 0.03829 0.02780 -0.0357 1.0000 0.0606
-6.250 -0.5892 0.03669 0.02601 -0.0343 1.0000 0.0633
-6.000 -0.5714 0.03506 0.02407 -0.0328 1.0000 0.0662
-5.750 -0.5519 0.03355 0.02222 -0.0313 1.0000 0.0682
-5.500 -0.5333 0.03217 0.02093 -0.0298 1.0000 0.0712
-5.250 -0.5147 0.03114 0.01983 -0.0283 1.0000 0.0756
-5.000 -0.4951 0.03019 0.01869 -0.0265 1.0000 0.0799
-4.750 -0.4776 0.02920 0.01778 -0.0248 1.0000 0.0841
-4.500 -0.4602 0.02840 0.01692 -0.0231 1.0000 0.0911
-4.250 -0.4434 0.02753 0.01604 -0.0215 1.0000 0.0979
-4.000 -0.4259 0.02675 0.01520 -0.0201 1.0000 0.1083
-3.750 -0.4083 0.02585 0.01434 -0.0190 1.0000 0.1226
-3.500 -0.3893 0.02473 0.01343 -0.0185 1.0000 0.1491
-3.250 -0.3706 0.02276 0.01232 -0.0189 1.0000 0.2571
-3.000 -0.3598 0.02228 0.01336 -0.0150 0.9984 0.5473
-2.750 -0.3337 0.02309 0.01408 -0.0138 0.9921 0.6271
-2.500 -0.3117 0.02392 0.01490 -0.0113 0.9855 0.6842
-2.250 -0.2974 0.02466 0.01573 -0.0062 0.9788 0.7346
-2.000 -0.2778 0.02506 0.01610 -0.0029 0.9728 0.7695
-1.750 -0.2507 0.02501 0.01586 -0.0031 0.9664 0.7827
-1.500 -0.2188 0.02501 0.01566 -0.0043 0.9608 0.7913
-1.250 -0.1894 0.02495 0.01543 -0.0053 0.9545 0.7997
-1.000 -0.1583 0.02496 0.01530 -0.0064 0.9483 0.8077
-0.750 -0.1271 0.02497 0.01517 -0.0077 0.9423 0.8158
-0.500 -0.0979 0.02497 0.01507 -0.0085 0.9355 0.8237
-0.250 -0.0628 0.02506 0.01506 -0.0105 0.9300 0.8317
0.000 -0.0370 0.02505 0.01499 -0.0107 0.9221 0.8399
0.250 -0.0015 0.02515 0.01504 -0.0127 0.9163 0.8482
0.500 0.0251 0.02518 0.01504 -0.0130 0.9081 0.8572
0.750 0.0610 0.02529 0.01514 -0.0150 0.9017 0.8660
1.000 0.0892 0.02535 0.01521 -0.0156 0.8930 0.8764
1.250 0.1281 0.02544 0.01533 -0.0180 0.8860 0.8859
1.500 0.1589 0.02552 0.01547 -0.0191 0.8762 0.8976
1.750 0.2027 0.02560 0.01560 -0.0223 0.8691 0.9091
2.000 0.2379 0.02570 0.01580 -0.0243 0.8583 0.9232
2.250 0.2854 0.02574 0.01593 -0.0282 0.8493 0.9377
2.500 0.3334 0.02567 0.01598 -0.0321 0.8380 0.9556
2.750 0.3787 0.02546 0.01590 -0.0354 0.8237 0.9896
3.000 0.4156 0.02519 0.01571 -0.0369 0.8084 1.0000
3.250 0.4553 0.02471 0.01531 -0.0383 0.7913 1.0000
3.500 0.5007 0.02378 0.01448 -0.0398 0.7689 1.0000
3.750 0.5387 0.02275 0.01351 -0.0396 0.7378 1.0000
4.000 0.5636 0.02215 0.01293 -0.0377 0.7000 1.0000
4.250 0.5912 0.02164 0.01239 -0.0364 0.6558 1.0000
4.500 0.6137 0.02144 0.01215 -0.0346 0.5992 1.0000
4.750 0.6456 0.02122 0.01156 -0.0338 0.5070 1.0000
5.000 0.6660 0.02192 0.01145 -0.0318 0.3937 1.0000
5.250 0.6770 0.02318 0.01207 -0.0294 0.3076 1.0000
5.500 0.6893 0.02449 0.01289 -0.0274 0.2520 1.0000
5.750 0.7051 0.02569 0.01379 -0.0260 0.2181 1.0000
6.000 0.7237 0.02680 0.01472 -0.0250 0.1964 1.0000
6.250 0.7443 0.02787 0.01568 -0.0242 0.1805 1.0000
6.500 0.7670 0.02890 0.01662 -0.0237 0.1681 1.0000
6.750 0.7916 0.02996 0.01756 -0.0235 0.1586 1.0000
7.000 0.8218 0.03097 0.01870 -0.0239 0.1509 1.0000
7.250 0.8521 0.03213 0.01975 -0.0245 0.1447 1.0000
7.500 0.8822 0.03326 0.02104 -0.0249 0.1382 1.0000
7.750 0.9107 0.03446 0.02229 -0.0252 0.1326 1.0000
8.000 0.9424 0.03594 0.02371 -0.0261 0.1288 1.0000
8.250 0.9691 0.03745 0.02551 -0.0261 0.1249 1.0000
8.500 0.9935 0.03896 0.02723 -0.0259 0.1208 1.0000
8.750 1.0172 0.04047 0.02880 -0.0257 0.1171 1.0000
9.000 1.0428 0.04237 0.03072 -0.0259 0.1145 1.0000
9.250 1.0602 0.04446 0.03324 -0.0248 0.1123 1.0000
9.500 1.0750 0.04663 0.03580 -0.0235 0.1097 1.0000
9.750 1.0885 0.04874 0.03820 -0.0222 0.1070 1.0000
10.000 1.1020 0.05078 0.04043 -0.0210 0.1044 1.0000
10.250 1.1160 0.05302 0.04283 -0.0199 0.1025 1.0000
10.500 1.1299 0.05561 0.04558 -0.0190 0.1011 1.0000
10.750 1.1282 0.05866 0.04902 -0.0166 0.1000 1.0000
11.000 1.1174 0.06190 0.05269 -0.0135 0.0989 1.0000
11.250 1.1009 0.06520 0.05634 -0.0101 0.0980 1.0000
11.500 1.0792 0.06878 0.06020 -0.0071 0.0972 1.0000
11.750 1.0532 0.07297 0.06465 -0.0050 0.0967 1.0000
12.000 1.0220 0.07816 0.07006 -0.0044 0.0966 1.0000
12.250 0.9833 0.08503 0.07711 -0.0059 0.0968 1.0000
12.500 0.9370 0.09462 0.08684 -0.0106 0.0975 1.0000
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Polar data table (+)
Polar graphs
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