EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 100,000 Max Cl/Cd: 40.81 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e550-il-100000-n5.txt Download as CSV file: xf-e550-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 550 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5322 0.09377 0.08831 -0.0548 1.0000 0.0185
-13.500 -0.5521 0.08661 0.08105 -0.0589 1.0000 0.0183
-13.250 -0.5738 0.08009 0.07439 -0.0623 1.0000 0.0182
-13.000 -0.5947 0.07438 0.06852 -0.0648 1.0000 0.0182
-12.750 -0.6128 0.06950 0.06348 -0.0665 1.0000 0.0181
-12.500 -0.6277 0.06529 0.05911 -0.0674 1.0000 0.0180
-12.250 -0.6449 0.06107 0.05467 -0.0679 1.0000 0.0181
-12.000 -0.6574 0.05749 0.05090 -0.0677 1.0000 0.0181
-11.750 -0.6679 0.05424 0.04743 -0.0671 1.0000 0.0181
-11.500 -0.6768 0.05114 0.04408 -0.0660 1.0000 0.0182
-11.250 -0.6817 0.04846 0.04116 -0.0646 1.0000 0.0184
-11.000 -0.6825 0.04612 0.03858 -0.0631 1.0000 0.0185
-10.750 -0.6794 0.04403 0.03636 -0.0615 1.0000 0.0187
-10.500 -0.6740 0.04232 0.03460 -0.0599 1.0000 0.0191
-10.250 -0.6693 0.04089 0.03312 -0.0582 1.0000 0.0196
-10.000 -0.6637 0.03949 0.03165 -0.0562 1.0000 0.0203
-9.750 -0.6571 0.03818 0.03026 -0.0541 1.0000 0.0209
-9.500 -0.6323 0.03634 0.02819 -0.0547 0.9854 0.0226
-9.250 -0.5999 0.03469 0.02652 -0.0571 0.9575 0.0241
-9.000 -0.5579 0.03302 0.02470 -0.0600 0.9355 0.0258
-8.750 -0.5149 0.03133 0.02292 -0.0637 0.9122 0.0282
-8.500 -0.4731 0.02990 0.02129 -0.0675 0.8858 0.0321
-8.250 -0.4399 0.02854 0.01984 -0.0702 0.8584 0.0368
-8.000 -0.4169 0.02738 0.01857 -0.0709 0.8323 0.0417
-7.750 -0.3997 0.02635 0.01745 -0.0704 0.8101 0.0489
-7.500 -0.3873 0.02541 0.01644 -0.0691 0.7904 0.0580
-7.250 -0.3781 0.02453 0.01553 -0.0672 0.7734 0.0698
-7.000 -0.3706 0.02365 0.01468 -0.0651 0.7587 0.0882
-6.750 -0.3629 0.02269 0.01385 -0.0631 0.7456 0.1170
-6.500 -0.3579 0.02156 0.01295 -0.0609 0.7337 0.1631
-6.250 -0.3567 0.02010 0.01189 -0.0585 0.7234 0.2396
-6.000 -0.3575 0.01868 0.01135 -0.0552 0.7134 0.3818
-5.750 -0.3329 0.01968 0.01274 -0.0529 0.7038 0.5017
-5.500 -0.3109 0.01983 0.01261 -0.0522 0.6949 0.5379
-5.250 -0.2846 0.02056 0.01317 -0.0510 0.6859 0.5595
-5.000 -0.2578 0.02119 0.01360 -0.0500 0.6783 0.5758
-4.750 -0.2316 0.02176 0.01402 -0.0489 0.6707 0.5897
-4.500 -0.2045 0.02264 0.01476 -0.0474 0.6636 0.6051
-4.250 -0.1787 0.02331 0.01527 -0.0461 0.6572 0.6194
-4.000 -0.1498 0.02387 0.01575 -0.0450 0.6500 0.6247
-3.750 -0.1250 0.02370 0.01536 -0.0448 0.6444 0.6300
-3.500 -0.1028 0.02325 0.01474 -0.0448 0.6381 0.6360
-3.250 -0.0763 0.02321 0.01458 -0.0445 0.6323 0.6384
-3.000 -0.0498 0.02312 0.01432 -0.0444 0.6278 0.6412
-2.750 -0.0247 0.02293 0.01402 -0.0443 0.6225 0.6445
-2.500 -0.0001 0.02262 0.01357 -0.0445 0.6171 0.6487
-2.250 0.0255 0.02229 0.01305 -0.0450 0.6126 0.6524
-2.000 0.0520 0.02222 0.01288 -0.0449 0.6081 0.6542
-1.750 0.0777 0.02215 0.01276 -0.0447 0.6030 0.6564
-1.500 0.1040 0.02206 0.01257 -0.0448 0.5988 0.6587
-1.250 0.1311 0.02193 0.01231 -0.0451 0.5953 0.6611
-1.000 0.1576 0.02180 0.01209 -0.0454 0.5915 0.6641
-0.750 0.1837 0.02164 0.01185 -0.0459 0.5869 0.6676
-0.500 0.2103 0.02156 0.01171 -0.0461 0.5828 0.6696
-0.250 0.2376 0.02154 0.01161 -0.0462 0.5794 0.6711
0.000 0.2649 0.02154 0.01154 -0.0464 0.5763 0.6729
0.250 0.2902 0.02159 0.01161 -0.0463 0.5723 0.6752
0.500 0.3165 0.02161 0.01162 -0.0465 0.5686 0.6778
0.750 0.3438 0.02160 0.01156 -0.0468 0.5652 0.6804
1.000 0.3723 0.02157 0.01143 -0.0475 0.5622 0.6830
1.250 0.3996 0.02160 0.01143 -0.0480 0.5589 0.6854
1.500 0.4244 0.02174 0.01163 -0.0477 0.5552 0.6871
1.750 0.4500 0.02186 0.01179 -0.0476 0.5518 0.6892
2.000 0.4767 0.02195 0.01189 -0.0477 0.5486 0.6915
2.250 0.5047 0.02203 0.01193 -0.0480 0.5458 0.6941
2.500 0.5316 0.02216 0.01206 -0.0483 0.5429 0.6967
2.750 0.5562 0.02237 0.01234 -0.0484 0.5391 0.6995
3.000 0.5823 0.02253 0.01255 -0.0486 0.5355 0.7021
3.250 0.6084 0.02267 0.01273 -0.0486 0.5323 0.7040
3.500 0.6357 0.02280 0.01287 -0.0487 0.5297 0.7064
3.750 0.6621 0.02300 0.01312 -0.0488 0.5269 0.7092
4.000 0.6839 0.02334 0.01360 -0.0483 0.5226 0.7124
4.250 0.7090 0.02358 0.01391 -0.0484 0.5188 0.7157
4.500 0.7361 0.02375 0.01412 -0.0487 0.5156 0.7186
4.750 0.7638 0.02387 0.01427 -0.0488 0.5129 0.7210
5.000 0.7858 0.02421 0.01475 -0.0482 0.5090 0.7237
5.250 0.8066 0.02460 0.01529 -0.0476 0.5043 0.7269
5.500 0.8321 0.02481 0.01557 -0.0476 0.5004 0.7305
5.750 0.8612 0.02491 0.01569 -0.0481 0.4972 0.7346
6.000 0.8829 0.02522 0.01615 -0.0474 0.4930 0.7378
6.250 0.9009 0.02567 0.01679 -0.0463 0.4876 0.7415
6.500 0.9264 0.02582 0.01701 -0.0461 0.4834 0.7456
6.750 0.9574 0.02579 0.01701 -0.0468 0.4800 0.7499
7.000 0.9702 0.02641 0.01786 -0.0450 0.4738 0.7536
7.250 0.9920 0.02663 0.01821 -0.0443 0.4685 0.7577
7.500 1.0224 0.02651 0.01814 -0.0447 0.4644 0.7626
7.750 1.0352 0.02712 0.01896 -0.0430 0.4576 0.7680
8.000 1.0560 0.02724 0.01922 -0.0420 0.4517 0.7730
8.250 1.0860 0.02704 0.01907 -0.0423 0.4469 0.7791
8.500 1.0916 0.02776 0.02005 -0.0396 0.4387 0.7855
8.750 1.1187 0.02752 0.01989 -0.0393 0.4330 0.7918
9.250 1.1455 0.02807 0.02079 -0.0355 0.4179 0.8069
9.500 1.1467 0.02873 0.02166 -0.0322 0.4095 0.8166
9.750 1.1623 0.02866 0.02170 -0.0302 0.4019 0.8269
10.000 1.1537 0.02974 0.02301 -0.0259 0.3928 0.8411
10.250 1.1670 0.02978 0.02317 -0.0239 0.3844 0.8584
10.500 1.1533 0.03128 0.02493 -0.0199 0.3741 0.8889
10.750 1.1482 0.03269 0.02653 -0.0179 0.3632 1.0000
11.000 1.1525 0.03411 0.02799 -0.0171 0.3512 1.0000
11.250 1.1565 0.03565 0.02955 -0.0164 0.3383 1.0000
11.500 1.1588 0.03742 0.03132 -0.0157 0.3245 1.0000
11.750 1.1605 0.03933 0.03322 -0.0151 0.3101 1.0000
12.000 1.1599 0.04154 0.03540 -0.0146 0.2947 1.0000
12.250 1.1599 0.04377 0.03761 -0.0141 0.2795 1.0000
12.500 1.1589 0.04615 0.03995 -0.0138 0.2642 1.0000
12.750 1.1577 0.04863 0.04238 -0.0134 0.2494 1.0000
13.000 1.1556 0.05126 0.04497 -0.0132 0.2352 1.0000
13.250 1.1522 0.05415 0.04783 -0.0132 0.2212 1.0000
13.500 1.1491 0.05712 0.05079 -0.0133 0.2080 1.0000
13.750 1.1465 0.06013 0.05379 -0.0135 0.1952 1.0000
14.000 1.1443 0.06318 0.05684 -0.0138 0.1831 1.0000
14.250 1.1426 0.06626 0.05991 -0.0142 0.1718 1.0000
14.500 1.1406 0.06942 0.06303 -0.0147 0.1609 1.0000
14.750 1.1385 0.07278 0.06643 -0.0154 0.1503 1.0000
15.000 1.1368 0.07615 0.06983 -0.0161 0.1405 1.0000
15.250 1.1349 0.07956 0.07322 -0.0170 0.1314 1.0000
15.500 1.1329 0.08312 0.07681 -0.0179 0.1225 1.0000
15.750 1.1315 0.08669 0.08042 -0.0189 0.1143 1.0000
16.000 1.1289 0.09039 0.08409 -0.0201 0.1071 1.0000
16.250 1.1281 0.09403 0.08784 -0.0212 0.0997 1.0000
16.500 1.1256 0.09785 0.09163 -0.0226 0.0935 1.0000
16.750 1.1247 0.10162 0.09553 -0.0239 0.0870 1.0000
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