EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.13 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e557-il-1000000.txt Download as CSV file: xf-e557-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6711 0.12544 0.12317 -0.0423 1.0000 0.0047
-17.000 -0.7059 0.11394 0.11149 -0.0478 1.0000 0.0047
-16.750 -0.7267 0.10586 0.10328 -0.0517 1.0000 0.0046
-16.500 -0.7482 0.09794 0.09523 -0.0556 1.0000 0.0046
-16.250 -0.7658 0.09118 0.08835 -0.0588 1.0000 0.0045
-16.000 -0.7802 0.08513 0.08219 -0.0617 1.0000 0.0045
-15.750 -0.7925 0.07974 0.07669 -0.0641 1.0000 0.0045
-15.500 -0.8037 0.07472 0.07158 -0.0662 1.0000 0.0045
-15.250 -0.8158 0.06980 0.06654 -0.0682 1.0000 0.0045
-15.000 -0.8227 0.06578 0.06244 -0.0697 1.0000 0.0045
-14.750 -0.8301 0.06188 0.05845 -0.0710 1.0000 0.0046
-14.500 -0.8369 0.05825 0.05473 -0.0721 1.0000 0.0047
-14.250 -0.8442 0.05481 0.05121 -0.0728 1.0000 0.0045
-14.000 -0.8506 0.05165 0.04797 -0.0733 1.0000 0.0047
-13.750 -0.8565 0.04880 0.04505 -0.0734 1.0000 0.0047
-13.500 -0.8653 0.04602 0.04219 -0.0731 1.0000 0.0046
-13.250 -0.8712 0.04369 0.03981 -0.0724 1.0000 0.0046
-13.000 -0.8816 0.04124 0.03729 -0.0713 1.0000 0.0047
-12.750 -0.8768 0.03867 0.03464 -0.0731 0.9990 0.0047
-12.500 -0.8609 0.03596 0.03184 -0.0771 0.9968 0.0049
-12.250 -0.8428 0.03346 0.02925 -0.0811 0.9946 0.0049
-12.000 -0.8257 0.03112 0.02682 -0.0845 0.9917 0.0050
-11.750 -0.8077 0.02895 0.02457 -0.0877 0.9879 0.0052
-11.500 -0.7864 0.02672 0.02225 -0.0918 0.9850 0.0052
-11.250 -0.7649 0.02543 0.02089 -0.0937 0.9809 0.0054
-11.000 -0.7442 0.02242 0.01777 -0.0989 0.9752 0.0056
-10.750 -0.7104 0.01967 0.01492 -0.1061 0.9730 0.0060
-10.500 -0.6882 0.01846 0.01365 -0.1075 0.9664 0.0063
-10.250 -0.6562 0.01737 0.01249 -0.1103 0.9638 0.0065
-10.000 -0.6225 0.01648 0.01155 -0.1129 0.9621 0.0070
-9.750 -0.5881 0.01566 0.01067 -0.1155 0.9607 0.0074
-9.500 -0.5661 0.01466 0.00961 -0.1158 0.9534 0.0079
-9.250 -0.5332 0.01393 0.00885 -0.1177 0.9506 0.0088
-9.000 -0.4975 0.01329 0.00816 -0.1201 0.9485 0.0095
-8.750 -0.4660 0.01260 0.00745 -0.1217 0.9434 0.0111
-8.500 -0.4317 0.01201 0.00683 -0.1237 0.9384 0.0133
-8.250 -0.3913 0.01145 0.00626 -0.1270 0.9353 0.0164
-8.000 -0.3496 0.01093 0.00574 -0.1305 0.9317 0.0206
-7.750 -0.3118 0.01050 0.00531 -0.1331 0.9246 0.0253
-7.500 -0.2676 0.01008 0.00488 -0.1371 0.9194 0.0320
-7.250 -0.2310 0.00966 0.00448 -0.1395 0.9101 0.0419
-7.000 -0.1934 0.00924 0.00409 -0.1421 0.9009 0.0572
-6.750 -0.1614 0.00887 0.00375 -0.1434 0.8890 0.0767
-6.500 -0.1313 0.00848 0.00343 -0.1443 0.8772 0.1019
-6.250 -0.1017 0.00800 0.00306 -0.1452 0.8655 0.1436
-6.000 -0.0729 0.00722 0.00256 -0.1464 0.8537 0.2260
-5.750 -0.0449 0.00664 0.00224 -0.1471 0.8420 0.3118
-5.500 -0.0165 0.00652 0.00214 -0.1473 0.8310 0.3414
-5.250 0.0118 0.00649 0.00207 -0.1474 0.8201 0.3577
-5.000 0.0398 0.00647 0.00201 -0.1474 0.8089 0.3700
-4.750 0.0679 0.00647 0.00196 -0.1473 0.7985 0.3804
-4.500 0.0957 0.00651 0.00193 -0.1473 0.7879 0.3885
-4.250 0.1237 0.00652 0.00188 -0.1472 0.7773 0.3950
-4.000 0.1517 0.00654 0.00185 -0.1472 0.7672 0.4008
-3.500 0.2074 0.00661 0.00180 -0.1470 0.7465 0.4122
-3.250 0.2352 0.00670 0.00184 -0.1469 0.7365 0.4208
-3.000 0.2630 0.00675 0.00183 -0.1469 0.7264 0.4261
-2.750 0.2910 0.00674 0.00180 -0.1468 0.7168 0.4294
-2.250 0.3467 0.00681 0.00177 -0.1467 0.6975 0.4347
-2.000 0.3744 0.00686 0.00175 -0.1466 0.6883 0.4374
-1.750 0.4023 0.00691 0.00175 -0.1466 0.6785 0.4398
-1.500 0.4302 0.00692 0.00173 -0.1466 0.6695 0.4426
-1.250 0.4578 0.00695 0.00172 -0.1465 0.6600 0.4456
-1.000 0.4858 0.00698 0.00174 -0.1465 0.6509 0.4483
-0.500 0.5413 0.00709 0.00177 -0.1463 0.6326 0.4540
-0.250 0.5687 0.00718 0.00179 -0.1462 0.6233 0.4564
0.000 0.5965 0.00720 0.00181 -0.1462 0.6140 0.4595
0.250 0.6241 0.00725 0.00184 -0.1461 0.6051 0.4626
0.500 0.6515 0.00731 0.00188 -0.1460 0.5954 0.4656
0.750 0.6792 0.00738 0.00193 -0.1459 0.5865 0.4685
1.000 0.7061 0.00748 0.00198 -0.1457 0.5768 0.4714
1.250 0.7339 0.00755 0.00203 -0.1456 0.5677 0.4740
1.500 0.7608 0.00762 0.00208 -0.1455 0.5580 0.4779
1.750 0.7882 0.00769 0.00215 -0.1454 0.5481 0.4812
2.000 0.8152 0.00778 0.00222 -0.1452 0.5384 0.4844
2.500 0.8689 0.00799 0.00238 -0.1448 0.5178 0.4903
2.750 0.8955 0.00809 0.00247 -0.1445 0.5077 0.4945
3.000 0.9220 0.00820 0.00257 -0.1443 0.4971 0.4984
3.250 0.9488 0.00830 0.00267 -0.1441 0.4872 0.5023
3.500 0.9747 0.00845 0.00278 -0.1437 0.4770 0.5058
3.750 1.0013 0.00856 0.00289 -0.1435 0.4666 0.5096
4.000 1.0275 0.00868 0.00301 -0.1432 0.4564 0.5139
4.250 1.0530 0.00884 0.00315 -0.1427 0.4455 0.5182
4.500 1.0791 0.00898 0.00329 -0.1424 0.4347 0.5226
4.750 1.1047 0.00913 0.00343 -0.1420 0.4236 0.5274
5.000 1.1296 0.00931 0.00359 -0.1415 0.4118 0.5325
5.250 1.1547 0.00948 0.00376 -0.1410 0.4002 0.5377
5.500 1.1798 0.00966 0.00393 -0.1405 0.3884 0.5426
5.750 1.2042 0.00986 0.00412 -0.1399 0.3759 0.5483
6.000 1.2281 0.01008 0.00433 -0.1392 0.3630 0.5544
6.250 1.2514 0.01033 0.00454 -0.1384 0.3494 0.5607
6.500 1.2747 0.01057 0.00478 -0.1376 0.3351 0.5679
6.750 1.2972 0.01086 0.00502 -0.1367 0.3196 0.5749
7.000 1.3190 0.01115 0.00530 -0.1357 0.3032 0.5827
7.250 1.3395 0.01148 0.00558 -0.1344 0.2866 0.5907
7.500 1.3588 0.01182 0.00589 -0.1328 0.2684 0.5995
7.750 1.3767 0.01222 0.00623 -0.1311 0.2488 0.6089
8.000 1.3936 0.01268 0.00663 -0.1292 0.2287 0.6196
8.250 1.4098 0.01316 0.00705 -0.1272 0.2107 0.6304
8.500 1.4262 0.01364 0.00749 -0.1253 0.1941 0.6423
8.750 1.4422 0.01414 0.00796 -0.1233 0.1775 0.6553
9.000 1.4573 0.01468 0.00846 -0.1213 0.1613 0.6691
9.250 1.4718 0.01523 0.00899 -0.1191 0.1470 0.6848
9.500 1.4864 0.01579 0.00954 -0.1170 0.1343 0.7025
9.750 1.4998 0.01639 0.01013 -0.1148 0.1224 0.7232
10.000 1.5135 0.01697 0.01075 -0.1127 0.1118 0.7474
10.250 1.5267 0.01757 0.01140 -0.1105 0.1023 0.7771
10.500 1.5387 0.01820 0.01210 -0.1082 0.0937 0.8194
10.750 1.5425 0.01861 0.01275 -0.1043 0.0865 1.0000
11.000 1.5544 0.01938 0.01351 -0.1022 0.0792 1.0000
11.250 1.5641 0.02029 0.01440 -0.0999 0.0718 1.0000
11.500 1.5743 0.02121 0.01531 -0.0978 0.0656 1.0000
11.750 1.5839 0.02219 0.01629 -0.0957 0.0597 1.0000
12.000 1.5913 0.02335 0.01742 -0.0934 0.0539 1.0000
12.250 1.6007 0.02443 0.01852 -0.0916 0.0494 1.0000
12.500 1.6065 0.02578 0.01986 -0.0894 0.0445 1.0000
12.750 1.6152 0.02700 0.02112 -0.0877 0.0411 1.0000
13.000 1.6201 0.02855 0.02267 -0.0858 0.0371 1.0000
13.250 1.6274 0.02997 0.02413 -0.0842 0.0342 1.0000
13.500 1.6310 0.03175 0.02591 -0.0825 0.0309 1.0000
13.750 1.6375 0.03337 0.02758 -0.0812 0.0286 1.0000
14.000 1.6397 0.03543 0.02965 -0.0797 0.0259 1.0000
14.250 1.6455 0.03723 0.03151 -0.0787 0.0241 1.0000
14.500 1.6481 0.03941 0.03373 -0.0776 0.0224 1.0000
14.750 1.6511 0.04164 0.03602 -0.0766 0.0208 1.0000
15.000 1.6545 0.04392 0.03835 -0.0759 0.0194 1.0000
15.250 1.6550 0.04656 0.04104 -0.0752 0.0181 1.0000
15.500 1.6570 0.04916 0.04371 -0.0747 0.0170 1.0000
15.750 1.6591 0.05183 0.04645 -0.0744 0.0161 1.0000
16.000 1.6589 0.05484 0.04952 -0.0742 0.0151 1.0000
16.250 1.6567 0.05821 0.05295 -0.0742 0.0142 1.0000
16.500 1.6582 0.06119 0.05602 -0.0743 0.0135 1.0000
16.750 1.6575 0.06455 0.05946 -0.0746 0.0129 1.0000
17.000 1.6548 0.06827 0.06325 -0.0751 0.0121 1.0000
17.250 1.6498 0.07241 0.06747 -0.0758 0.0115 1.0000
17.500 1.6486 0.07612 0.07127 -0.0765 0.0111 1.0000
17.750 1.6463 0.08007 0.07531 -0.0774 0.0106 1.0000
18.000 1.6422 0.08436 0.07969 -0.0786 0.0101 1.0000
18.250 1.6364 0.08900 0.08442 -0.0799 0.0096 1.0000
18.500 1.6285 0.09407 0.08957 -0.0816 0.0092 1.0000
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