EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 200,000 Max Cl/Cd: 73.24 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e559-il-200000-n5.txt Download as CSV file: xf-e559-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 559 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.5776 0.12045 0.11609 -0.0468 1.0000 0.0203
-15.750 -0.6123 0.10936 0.10479 -0.0524 1.0000 0.0203
-15.500 -0.6313 0.10195 0.09724 -0.0561 1.0000 0.0204
-15.250 -0.6481 0.09525 0.09039 -0.0595 1.0000 0.0206
-15.000 -0.6591 0.08986 0.08488 -0.0621 1.0000 0.0208
-14.750 -0.6709 0.08445 0.07933 -0.0648 1.0000 0.0210
-14.500 -0.6733 0.08105 0.07590 -0.0659 1.0000 0.0213
-14.250 -0.6750 0.07787 0.07271 -0.0669 1.0000 0.0215
-14.000 -0.6778 0.07455 0.06936 -0.0680 1.0000 0.0218
-13.750 -0.6814 0.07121 0.06600 -0.0691 1.0000 0.0220
-13.500 -0.6857 0.06793 0.06268 -0.0701 1.0000 0.0223
-13.250 -0.6907 0.06479 0.05949 -0.0708 1.0000 0.0224
-13.000 -0.6976 0.06150 0.05616 -0.0717 1.0000 0.0228
-12.750 -0.7044 0.05837 0.05298 -0.0723 1.0000 0.0231
-12.500 -0.7119 0.05534 0.04991 -0.0727 1.0000 0.0233
-12.250 -0.7209 0.05231 0.04683 -0.0729 1.0000 0.0237
-12.000 -0.7310 0.04939 0.04387 -0.0729 1.0000 0.0239
-11.750 -0.7438 0.04650 0.04094 -0.0724 1.0000 0.0242
-11.500 -0.7595 0.04374 0.03814 -0.0714 1.0000 0.0244
-11.250 -0.7827 0.04109 0.03547 -0.0694 1.0000 0.0245
-11.000 -0.7724 0.03766 0.03188 -0.0745 0.9948 0.0251
-10.750 -0.7504 0.03332 0.02743 -0.0833 0.9872 0.0259
-10.500 -0.7224 0.03037 0.02434 -0.0898 0.9810 0.0270
-10.250 -0.6964 0.02835 0.02219 -0.0934 0.9738 0.0281
-10.000 -0.6704 0.02668 0.02038 -0.0960 0.9667 0.0293
-9.500 -0.6163 0.02371 0.01723 -0.1004 0.9518 0.0328
-9.250 -0.5839 0.02250 0.01590 -0.1028 0.9464 0.0354
-9.000 -0.5582 0.02132 0.01467 -0.1039 0.9373 0.0384
-8.750 -0.5248 0.02019 0.01346 -0.1062 0.9322 0.0433
-8.500 -0.4978 0.01921 0.01244 -0.1070 0.9229 0.0505
-8.250 -0.4635 0.01816 0.01139 -0.1092 0.9174 0.0634
-8.000 -0.4336 0.01735 0.01058 -0.1102 0.9081 0.0776
-7.750 -0.3967 0.01655 0.00978 -0.1126 0.9021 0.0941
-7.500 -0.3631 0.01593 0.00915 -0.1142 0.8930 0.1100
-7.250 -0.3225 0.01535 0.00854 -0.1170 0.8861 0.1274
-7.000 -0.2845 0.01488 0.00804 -0.1193 0.8762 0.1436
-6.750 -0.2416 0.01442 0.00758 -0.1226 0.8674 0.1634
-6.500 -0.2029 0.01408 0.00721 -0.1249 0.8551 0.1820
-6.250 -0.1642 0.01382 0.00687 -0.1272 0.8420 0.1975
-6.000 -0.1272 0.01360 0.00657 -0.1290 0.8280 0.2095
-5.750 -0.0923 0.01344 0.00626 -0.1303 0.8133 0.2203
-5.500 -0.0597 0.01331 0.00603 -0.1312 0.7981 0.2305
-5.250 -0.0287 0.01320 0.00582 -0.1318 0.7833 0.2397
-5.000 0.0010 0.01314 0.00560 -0.1320 0.7683 0.2491
-4.750 0.0294 0.01306 0.00546 -0.1320 0.7536 0.2569
-4.500 0.0577 0.01301 0.00527 -0.1320 0.7395 0.2656
-4.250 0.0856 0.01295 0.00515 -0.1319 0.7259 0.2728
-4.000 0.1135 0.01293 0.00500 -0.1317 0.7129 0.2810
-3.500 0.1683 0.01289 0.00479 -0.1313 0.6874 0.2961
-3.250 0.1956 0.01287 0.00470 -0.1311 0.6754 0.3032
-3.000 0.2229 0.01287 0.00461 -0.1308 0.6638 0.3107
-2.750 0.2500 0.01287 0.00453 -0.1305 0.6521 0.3181
-2.500 0.2771 0.01287 0.00448 -0.1303 0.6410 0.3250
-2.250 0.3044 0.01291 0.00440 -0.1300 0.6305 0.3328
-2.000 0.3313 0.01291 0.00438 -0.1297 0.6195 0.3395
-1.750 0.3584 0.01294 0.00434 -0.1295 0.6095 0.3472
-1.500 0.3854 0.01297 0.00432 -0.1292 0.5997 0.3540
-1.250 0.4124 0.01300 0.00431 -0.1289 0.5898 0.3617
-1.000 0.4393 0.01306 0.00429 -0.1286 0.5805 0.3691
-0.750 0.4662 0.01309 0.00431 -0.1283 0.5708 0.3762
-0.500 0.4933 0.01316 0.00431 -0.1281 0.5623 0.3845
-0.250 0.5200 0.01320 0.00436 -0.1278 0.5533 0.3918
0.000 0.5469 0.01328 0.00438 -0.1275 0.5448 0.4000
0.250 0.5736 0.01333 0.00444 -0.1272 0.5361 0.4077
0.500 0.6004 0.01342 0.00448 -0.1269 0.5285 0.4165
0.750 0.6271 0.01348 0.00456 -0.1266 0.5204 0.4244
1.000 0.6536 0.01358 0.00462 -0.1263 0.5129 0.4336
1.250 0.6802 0.01365 0.00472 -0.1259 0.5049 0.4425
1.750 0.7332 0.01384 0.00493 -0.1253 0.4909 0.4617
2.000 0.7594 0.01396 0.00503 -0.1249 0.4839 0.4725
2.250 0.7858 0.01406 0.00517 -0.1246 0.4771 0.4838
2.500 0.8120 0.01417 0.00531 -0.1242 0.4704 0.4954
2.750 0.8380 0.01431 0.00545 -0.1239 0.4646 0.5085
3.250 0.8898 0.01454 0.00579 -0.1231 0.4516 0.5384
3.500 0.9156 0.01467 0.00598 -0.1226 0.4460 0.5558
3.750 0.9412 0.01479 0.00619 -0.1222 0.4400 0.5756
4.000 0.9663 0.01493 0.00639 -0.1216 0.4345 0.5978
4.250 0.9914 0.01506 0.00662 -0.1211 0.4290 0.6244
4.500 1.0160 0.01517 0.00687 -0.1204 0.4231 0.6553
4.750 1.0398 0.01530 0.00710 -0.1195 0.4181 0.6925
5.000 1.0626 0.01541 0.00735 -0.1185 0.4131 0.7393
5.250 1.0831 0.01545 0.00760 -0.1168 0.4076 0.8024
5.500 1.1012 0.01534 0.00769 -0.1145 0.4027 1.0000
5.750 1.1265 0.01563 0.00793 -0.1141 0.3980 1.0000
6.000 1.1515 0.01587 0.00822 -0.1137 0.3924 1.0000
6.250 1.1759 0.01615 0.00849 -0.1131 0.3870 1.0000
6.500 1.2000 0.01647 0.00876 -0.1125 0.3823 1.0000
6.750 1.2241 0.01673 0.00910 -0.1119 0.3767 1.0000
7.000 1.2473 0.01703 0.00940 -0.1112 0.3713 1.0000
7.250 1.2702 0.01737 0.00971 -0.1104 0.3665 1.0000
7.500 1.2931 0.01766 0.01008 -0.1096 0.3608 1.0000
7.750 1.3149 0.01798 0.01043 -0.1086 0.3552 1.0000
8.000 1.3362 0.01835 0.01077 -0.1076 0.3503 1.0000
8.250 1.3572 0.01865 0.01118 -0.1064 0.3444 1.0000
8.500 1.3763 0.01900 0.01155 -0.1050 0.3387 1.0000
8.750 1.3948 0.01938 0.01195 -0.1035 0.3334 1.0000
9.000 1.4130 0.01974 0.01239 -0.1019 0.3270 1.0000
9.250 1.4297 0.02016 0.01282 -0.1002 0.3210 1.0000
9.500 1.4467 0.02058 0.01332 -0.0985 0.3148 1.0000
9.750 1.4622 0.02103 0.01382 -0.0966 0.3079 1.0000
10.000 1.4769 0.02154 0.01435 -0.0947 0.3017 1.0000
10.250 1.4917 0.02204 0.01495 -0.0928 0.2943 1.0000
10.500 1.5036 0.02267 0.01557 -0.0906 0.2875 1.0000
10.750 1.5174 0.02325 0.01627 -0.0888 0.2797 1.0000
11.250 1.5390 0.02473 0.01785 -0.0845 0.2638 1.0000
11.500 1.5469 0.02565 0.01879 -0.0822 0.2560 1.0000
11.750 1.5559 0.02659 0.01982 -0.0802 0.2469 1.0000
12.000 1.5623 0.02772 0.02099 -0.0781 0.2383 1.0000
12.250 1.5670 0.02901 0.02232 -0.0760 0.2289 1.0000
12.500 1.5718 0.03040 0.02376 -0.0741 0.2190 1.0000
12.750 1.5735 0.03208 0.02547 -0.0721 0.2095 1.0000
13.000 1.5737 0.03398 0.02740 -0.0704 0.1993 1.0000
13.250 1.5741 0.03601 0.02946 -0.0688 0.1891 1.0000
13.500 1.5714 0.03841 0.03190 -0.0674 0.1796 1.0000
13.750 1.5673 0.04107 0.03459 -0.0662 0.1704 1.0000
14.000 1.5641 0.04382 0.03739 -0.0653 0.1611 1.0000
14.250 1.5577 0.04702 0.04063 -0.0646 0.1529 1.0000
14.500 1.5519 0.05031 0.04397 -0.0642 0.1445 1.0000
14.750 1.5451 0.05387 0.04758 -0.0640 0.1369 1.0000
15.000 1.5366 0.05779 0.05155 -0.0640 0.1296 1.0000
15.250 1.5297 0.06165 0.05548 -0.0643 0.1226 1.0000
15.500 1.5198 0.06603 0.05991 -0.0648 0.1162 1.0000
15.750 1.5126 0.07022 0.06417 -0.0654 0.1099 1.0000
16.000 1.5026 0.07490 0.06891 -0.0663 0.1040 1.0000
16.250 1.4947 0.07941 0.07350 -0.0673 0.0986 1.0000
16.500 1.4860 0.08415 0.07831 -0.0685 0.0932 1.0000
16.750 1.4765 0.08912 0.08334 -0.0699 0.0886 1.0000
17.000 1.4698 0.09374 0.08804 -0.0712 0.0835 1.0000
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Polar data table (+)
Polar graphs
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