EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 100,000 Max Cl/Cd: 50.58 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e598-il-100000-n5.txt Download as CSV file: xf-e598-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 598 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3218 0.09487 0.09000 -0.0139 0.7560 0.0237
-8.250 -0.3189 0.09135 0.08646 -0.0157 0.7445 0.0238
-8.000 -0.3166 0.08772 0.08281 -0.0176 0.7340 0.0238
-7.750 -0.3151 0.08392 0.07901 -0.0198 0.7242 0.0236
-7.500 -0.3153 0.08016 0.07524 -0.0219 0.7159 0.0236
-7.250 -0.3157 0.07649 0.07158 -0.0246 0.7073 0.0238
-7.000 -0.3128 0.07218 0.06724 -0.0283 0.7001 0.0239
-6.750 -0.3078 0.06722 0.06224 -0.0326 0.6929 0.0238
-6.500 -0.3009 0.06180 0.05672 -0.0370 0.6863 0.0238
-6.250 -0.2921 0.05567 0.05041 -0.0414 0.6808 0.0238
-6.000 -0.2822 0.04739 0.04182 -0.0461 0.6751 0.0234
-5.750 -0.2725 0.03797 0.03169 -0.0493 0.6704 0.0234
-5.250 -0.2351 0.02834 0.02047 -0.0499 0.6589 0.0254
-5.000 -0.2110 0.02655 0.01829 -0.0496 0.6525 0.0274
-4.750 -0.1860 0.02491 0.01618 -0.0491 0.6467 0.0310
-4.500 -0.1599 0.02383 0.01490 -0.0489 0.6400 0.0344
-4.250 -0.1339 0.02290 0.01373 -0.0485 0.6344 0.0396
-4.000 -0.1073 0.02209 0.01273 -0.0481 0.6287 0.0462
-3.750 -0.0803 0.02144 0.01191 -0.0479 0.6225 0.0550
-3.500 -0.0536 0.02092 0.01120 -0.0475 0.6174 0.0646
-3.250 -0.0265 0.02046 0.01064 -0.0472 0.6120 0.0744
-3.000 0.0007 0.02002 0.01014 -0.0470 0.6063 0.0845
-2.750 0.0276 0.01961 0.00962 -0.0467 0.6014 0.0949
-2.500 0.0547 0.01923 0.00914 -0.0463 0.5966 0.1061
-2.250 0.0821 0.01890 0.00873 -0.0461 0.5910 0.1181
-2.000 0.1091 0.01861 0.00835 -0.0458 0.5862 0.1310
-1.500 0.1629 0.01807 0.00779 -0.0452 0.5766 0.1607
-1.250 0.1899 0.01785 0.00756 -0.0449 0.5716 0.1793
-1.000 0.2167 0.01762 0.00733 -0.0446 0.5676 0.2017
-0.750 0.2439 0.01743 0.00720 -0.0444 0.5630 0.2331
-0.500 0.2714 0.01719 0.00712 -0.0444 0.5577 0.2826
-0.250 0.2976 0.01670 0.00701 -0.0442 0.5533 0.3947
0.000 0.3628 0.01519 0.00679 -0.0505 0.5487 1.0000
0.250 0.3890 0.01539 0.00687 -0.0502 0.5433 1.0000
0.500 0.4150 0.01556 0.00687 -0.0498 0.5385 1.0000
0.750 0.4410 0.01572 0.00683 -0.0493 0.5347 1.0000
1.000 0.4671 0.01592 0.00691 -0.0489 0.5303 1.0000
1.250 0.4932 0.01615 0.00706 -0.0486 0.5250 1.0000
1.500 0.5193 0.01633 0.00712 -0.0482 0.5207 1.0000
1.750 0.5454 0.01650 0.00714 -0.0477 0.5171 1.0000
2.000 0.5714 0.01678 0.00740 -0.0475 0.5117 1.0000
2.250 0.5974 0.01701 0.00758 -0.0471 0.5068 1.0000
2.500 0.6236 0.01719 0.00767 -0.0467 0.5028 1.0000
2.750 0.6497 0.01742 0.00782 -0.0463 0.4987 1.0000
3.000 0.6754 0.01773 0.00817 -0.0461 0.4930 1.0000
3.250 0.7014 0.01795 0.00834 -0.0458 0.4885 1.0000
3.500 0.7278 0.01812 0.00842 -0.0453 0.4849 1.0000
3.750 0.7531 0.01848 0.00884 -0.0451 0.4792 1.0000
4.000 0.7788 0.01875 0.00914 -0.0448 0.4741 1.0000
4.250 0.8050 0.01893 0.00926 -0.0444 0.4701 1.0000
4.500 0.8304 0.01925 0.00962 -0.0441 0.4650 1.0000
4.750 0.8555 0.01959 0.01001 -0.0438 0.4593 1.0000
5.000 0.8815 0.01978 0.01021 -0.0435 0.4549 1.0000
5.250 0.9069 0.02006 0.01052 -0.0431 0.4501 1.0000
5.500 0.9314 0.02046 0.01101 -0.0428 0.4440 1.0000
5.750 0.9571 0.02065 0.01123 -0.0424 0.4393 1.0000
6.000 0.9821 0.02096 0.01158 -0.0421 0.4342 1.0000
6.250 1.0060 0.02136 0.01211 -0.0417 0.4279 1.0000
6.500 1.0318 0.02152 0.01228 -0.0413 0.4231 1.0000
6.750 1.0554 0.02195 0.01283 -0.0409 0.4170 1.0000
7.000 1.0794 0.02228 0.01325 -0.0404 0.4107 1.0000
7.250 1.1055 0.02238 0.01335 -0.0400 0.4062 1.0000
7.500 1.1268 0.02298 0.01415 -0.0395 0.3983 1.0000
7.750 1.1517 0.02314 0.01436 -0.0390 0.3926 1.0000
8.000 1.1734 0.02363 0.01500 -0.0385 0.3852 1.0000
8.250 1.1969 0.02388 0.01533 -0.0379 0.3783 1.0000
8.500 1.2184 0.02431 0.01590 -0.0372 0.3707 1.0000
8.750 1.2408 0.02460 0.01627 -0.0366 0.3629 1.0000
9.000 1.2608 0.02511 0.01693 -0.0358 0.3544 1.0000
9.250 1.2827 0.02536 0.01723 -0.0350 0.3465 1.0000
9.500 1.2999 0.02603 0.01809 -0.0341 0.3368 1.0000
9.750 1.3193 0.02644 0.01857 -0.0332 0.3280 1.0000
10.000 1.3354 0.02706 0.01932 -0.0321 0.3181 1.0000
10.250 1.3493 0.02783 0.02022 -0.0309 0.3078 1.0000
10.500 1.3630 0.02851 0.02098 -0.0295 0.2979 1.0000
10.750 1.3730 0.02938 0.02193 -0.0280 0.2873 1.0000
11.000 1.3762 0.03058 0.02326 -0.0260 0.2768 1.0000
11.250 1.3773 0.03192 0.02466 -0.0241 0.2671 1.0000
11.500 1.3775 0.03353 0.02630 -0.0226 0.2571 1.0000
11.750 1.3735 0.03581 0.02869 -0.0218 0.2467 1.0000
12.000 1.3705 0.03818 0.03114 -0.0212 0.2365 1.0000
12.250 1.3673 0.04068 0.03366 -0.0208 0.2263 1.0000
12.500 1.3614 0.04368 0.03673 -0.0207 0.2157 1.0000
12.750 1.3549 0.04686 0.03998 -0.0208 0.2055 1.0000
13.000 1.3490 0.05002 0.04317 -0.0210 0.1956 1.0000
13.250 1.3425 0.05333 0.04648 -0.0212 0.1857 1.0000
13.500 1.3343 0.05703 0.05027 -0.0217 0.1761 1.0000
13.750 1.3268 0.06066 0.05393 -0.0222 0.1669 1.0000
14.000 1.3195 0.06432 0.05758 -0.0228 0.1581 1.0000
14.250 1.3117 0.06836 0.06170 -0.0237 0.1493 1.0000
14.500 1.3051 0.07226 0.06564 -0.0246 0.1411 1.0000
14.750 1.2981 0.07639 0.06980 -0.0257 0.1331 1.0000
15.000 1.2918 0.08057 0.07405 -0.0269 0.1255 1.0000
15.250 1.2857 0.08471 0.07816 -0.0281 0.1185 1.0000
15.500 1.2795 0.08913 0.08270 -0.0295 0.1115 1.0000
15.750 1.2740 0.09332 0.08686 -0.0308 0.1054 1.0000
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Polar data table (+)
Polar graphs
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