EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 200,000 Max Cl/Cd: 73.12 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e557-il-200000-n5.txt Download as CSV file: xf-e557-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 557 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4445 0.13878 0.13483 -0.0411 1.0000 0.0120
-14.500 -0.5642 0.10243 0.09826 -0.0564 1.0000 0.0109
-14.250 -0.6264 0.08575 0.08114 -0.0653 1.0000 0.0101
-14.000 -0.6351 0.08087 0.07620 -0.0678 1.0000 0.0104
-13.750 -0.6480 0.07553 0.07074 -0.0704 1.0000 0.0105
-13.500 -0.6661 0.06972 0.06473 -0.0727 1.0000 0.0103
-13.250 -0.6749 0.06573 0.06062 -0.0741 1.0000 0.0104
-13.000 -0.6833 0.06217 0.05697 -0.0751 1.0000 0.0107
-12.750 -0.6921 0.05874 0.05343 -0.0757 1.0000 0.0107
-12.500 -0.6989 0.05581 0.05040 -0.0761 1.0000 0.0110
-12.250 -0.7061 0.05298 0.04747 -0.0758 1.0000 0.0110
-12.000 -0.7130 0.05042 0.04481 -0.0753 1.0000 0.0113
-11.750 -0.7196 0.04813 0.04242 -0.0744 1.0000 0.0115
-11.500 -0.7269 0.04601 0.04022 -0.0729 1.0000 0.0115
-11.250 -0.7354 0.04409 0.03819 -0.0711 1.0000 0.0119
-11.000 -0.7326 0.04205 0.03603 -0.0712 0.9986 0.0120
-10.750 -0.7146 0.03966 0.03351 -0.0743 0.9944 0.0125
-10.500 -0.6976 0.03754 0.03133 -0.0770 0.9892 0.0128
-10.250 -0.6782 0.03556 0.02927 -0.0800 0.9840 0.0132
-10.000 -0.6649 0.03368 0.02731 -0.0815 0.9759 0.0138
-9.750 -0.6483 0.03178 0.02529 -0.0834 0.9681 0.0145
-9.250 -0.6049 0.02782 0.02115 -0.0892 0.9536 0.0161
-9.000 -0.5754 0.02613 0.01935 -0.0928 0.9488 0.0176
-8.750 -0.5519 0.02475 0.01788 -0.0946 0.9416 0.0194
-8.500 -0.5229 0.02346 0.01651 -0.0970 0.9364 0.0219
-8.250 -0.4900 0.02206 0.01503 -0.1002 0.9331 0.0244
-8.000 -0.4662 0.02103 0.01395 -0.1011 0.9249 0.0279
-7.750 -0.4333 0.01998 0.01283 -0.1035 0.9207 0.0328
-7.500 -0.3969 0.01892 0.01175 -0.1066 0.9179 0.0397
-7.250 -0.3705 0.01810 0.01091 -0.1075 0.9096 0.0476
-7.000 -0.3345 0.01719 0.01000 -0.1103 0.9053 0.0605
-6.750 -0.2947 0.01626 0.00911 -0.1138 0.9023 0.0801
-6.500 -0.2651 0.01549 0.00839 -0.1152 0.8940 0.1045
-6.250 -0.2256 0.01445 0.00752 -0.1189 0.8895 0.1509
-6.000 -0.1833 0.01302 0.00659 -0.1238 0.8853 0.2634
-5.750 -0.1503 0.01268 0.00646 -0.1253 0.8772 0.3368
-5.500 -0.1101 0.01258 0.00630 -0.1278 0.8717 0.3678
-5.250 -0.0766 0.01256 0.00619 -0.1289 0.8635 0.3857
-5.000 -0.0392 0.01254 0.00605 -0.1308 0.8563 0.3995
-4.750 -0.0059 0.01253 0.00591 -0.1318 0.8477 0.4104
-4.500 0.0298 0.01257 0.00582 -0.1333 0.8396 0.4223
-4.250 0.0606 0.01273 0.00595 -0.1337 0.8301 0.4350
-4.000 0.0951 0.01276 0.00586 -0.1350 0.8218 0.4436
-3.750 0.1242 0.01272 0.00573 -0.1351 0.8115 0.4469
-3.500 0.1560 0.01266 0.00556 -0.1359 0.8027 0.4506
-3.250 0.1861 0.01259 0.00536 -0.1364 0.7926 0.4542
-3.000 0.2161 0.01253 0.00518 -0.1368 0.7832 0.4578
-2.750 0.2460 0.01250 0.00508 -0.1371 0.7737 0.4604
-2.500 0.2741 0.01247 0.00500 -0.1371 0.7638 0.4632
-2.250 0.3039 0.01246 0.00488 -0.1375 0.7546 0.4662
-2.000 0.3320 0.01244 0.00479 -0.1375 0.7444 0.4698
-1.750 0.3611 0.01244 0.00467 -0.1378 0.7351 0.4736
-1.500 0.3892 0.01244 0.00462 -0.1378 0.7253 0.4762
-1.250 0.4167 0.01244 0.00460 -0.1377 0.7157 0.4788
-1.000 0.4453 0.01247 0.00455 -0.1378 0.7065 0.4819
-0.750 0.4725 0.01249 0.00454 -0.1376 0.6965 0.4854
-0.500 0.5007 0.01253 0.00449 -0.1377 0.6873 0.4894
-0.250 0.5281 0.01256 0.00449 -0.1376 0.6776 0.4924
0.000 0.5553 0.01260 0.00452 -0.1374 0.6683 0.4953
0.250 0.5828 0.01266 0.00454 -0.1373 0.6590 0.4985
0.500 0.6098 0.01271 0.00457 -0.1371 0.6496 0.5020
0.750 0.6375 0.01279 0.00458 -0.1371 0.6408 0.5061
1.000 0.6641 0.01285 0.00466 -0.1368 0.6310 0.5095
1.250 0.6910 0.01293 0.00473 -0.1366 0.6222 0.5129
1.500 0.7176 0.01301 0.00481 -0.1364 0.6126 0.5167
1.750 0.7444 0.01311 0.00488 -0.1362 0.6035 0.5207
2.000 0.7711 0.01321 0.00496 -0.1360 0.5942 0.5247
2.250 0.7972 0.01330 0.00509 -0.1356 0.5848 0.5282
2.750 0.8494 0.01354 0.00535 -0.1349 0.5659 0.5372
3.000 0.8755 0.01368 0.00547 -0.1346 0.5567 0.5419
3.250 0.9008 0.01380 0.00564 -0.1341 0.5467 0.5457
3.500 0.9263 0.01394 0.00581 -0.1336 0.5369 0.5502
4.000 0.9763 0.01426 0.00616 -0.1326 0.5162 0.5604
4.250 1.0008 0.01443 0.00637 -0.1320 0.5058 0.5656
4.500 1.0250 0.01463 0.00657 -0.1313 0.4952 0.5715
4.750 1.0491 0.01480 0.00679 -0.1306 0.4840 0.5769
5.000 1.0726 0.01500 0.00704 -0.1298 0.4732 0.5824
5.500 1.1188 0.01544 0.00755 -0.1281 0.4506 0.5955
5.750 1.1414 0.01568 0.00785 -0.1272 0.4393 0.6027
6.000 1.1632 0.01594 0.00814 -0.1261 0.4277 0.6101
6.250 1.1845 0.01621 0.00845 -0.1250 0.4154 0.6175
6.500 1.2057 0.01649 0.00879 -0.1238 0.4026 0.6257
6.750 1.2257 0.01679 0.00915 -0.1225 0.3896 0.6343
7.000 1.2449 0.01712 0.00952 -0.1210 0.3762 0.6439
7.250 1.2625 0.01747 0.00992 -0.1192 0.3625 0.6543
7.500 1.2786 0.01784 0.01033 -0.1172 0.3486 0.6648
7.750 1.2938 0.01827 0.01078 -0.1150 0.3338 0.6765
8.000 1.3089 0.01873 0.01128 -0.1129 0.3186 0.6894
8.250 1.3231 0.01923 0.01184 -0.1107 0.3027 0.7037
8.500 1.3360 0.01979 0.01243 -0.1084 0.2863 0.7200
8.750 1.3479 0.02040 0.01308 -0.1059 0.2693 0.7387
9.000 1.3583 0.02107 0.01379 -0.1033 0.2524 0.7603
9.250 1.3673 0.02179 0.01456 -0.1005 0.2360 0.7872
9.500 1.3738 0.02253 0.01538 -0.0973 0.2208 0.8256
9.750 1.3727 0.02308 0.01606 -0.0927 0.2083 1.0000
10.000 1.3815 0.02415 0.01709 -0.0906 0.1937 1.0000
10.250 1.3893 0.02532 0.01822 -0.0884 0.1799 1.0000
10.500 1.3972 0.02653 0.01942 -0.0864 0.1667 1.0000
10.750 1.4047 0.02782 0.02071 -0.0845 0.1546 1.0000
11.000 1.4115 0.02920 0.02210 -0.0826 0.1434 1.0000
11.250 1.4172 0.03072 0.02362 -0.0808 0.1336 1.0000
11.500 1.4223 0.03236 0.02526 -0.0791 0.1239 1.0000
11.750 1.4284 0.03399 0.02692 -0.0776 0.1149 1.0000
12.000 1.4322 0.03586 0.02881 -0.0762 0.1068 1.0000
12.250 1.4362 0.03779 0.03077 -0.0749 0.0989 1.0000
12.500 1.4400 0.03981 0.03285 -0.0737 0.0921 1.0000
12.750 1.4419 0.04209 0.03516 -0.0727 0.0855 1.0000
13.000 1.4454 0.04430 0.03743 -0.0718 0.0796 1.0000
13.250 1.4462 0.04685 0.04002 -0.0711 0.0741 1.0000
13.500 1.4486 0.04934 0.04259 -0.0705 0.0694 1.0000
13.750 1.4495 0.05208 0.04539 -0.0700 0.0647 1.0000
14.000 1.4492 0.05504 0.04842 -0.0697 0.0609 1.0000
14.250 1.4504 0.05792 0.05140 -0.0696 0.0569 1.0000
14.500 1.4481 0.06132 0.05486 -0.0697 0.0536 1.0000
14.750 1.4483 0.06452 0.05817 -0.0698 0.0505 1.0000
15.000 1.4473 0.06795 0.06169 -0.0702 0.0475 1.0000
15.250 1.4431 0.07192 0.06572 -0.0708 0.0449 1.0000
15.500 1.4421 0.07554 0.06947 -0.0714 0.0425 1.0000
15.750 1.4400 0.07942 0.07346 -0.0722 0.0402 1.0000
16.000 1.4353 0.08376 0.07788 -0.0733 0.0383 1.0000
16.250 1.4310 0.08813 0.08234 -0.0745 0.0365 1.0000
16.500 1.4287 0.09229 0.08665 -0.0757 0.0346 1.0000
16.750 1.4243 0.09685 0.09131 -0.0772 0.0329 1.0000
17.000 1.4176 0.10186 0.09640 -0.0791 0.0315 1.0000
17.250 1.4135 0.10651 0.10118 -0.0808 0.0302 1.0000
17.500 1.4100 0.11110 0.10591 -0.0827 0.0288 1.0000
17.750 1.4052 0.11598 0.11090 -0.0848 0.0275 1.0000
18.000 1.3989 0.12119 0.11619 -0.0872 0.0264 1.0000
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Polar data table (+)
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