EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 200,000 Max Cl/Cd: 75.56 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e598-il-200000-n5.txt Download as CSV file: xf-e598-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3489 0.09263 0.08846 -0.0103 0.6765 0.0125
-8.500 -0.3456 0.08915 0.08496 -0.0120 0.6687 0.0124
-8.250 -0.3433 0.08559 0.08139 -0.0137 0.6614 0.0122
-8.000 -0.3430 0.08175 0.07755 -0.0156 0.6545 0.0121
-7.000 -0.4119 0.03358 0.02830 -0.0460 0.6428 0.0102
-6.750 -0.3968 0.02894 0.02301 -0.0467 0.6367 0.0104
-6.500 -0.3764 0.02637 0.01998 -0.0467 0.6309 0.0106
-6.250 -0.3537 0.02437 0.01760 -0.0465 0.6242 0.0110
-6.000 -0.3302 0.02266 0.01549 -0.0461 0.6181 0.0114
-5.750 -0.3056 0.02116 0.01364 -0.0457 0.6122 0.0119
-5.500 -0.2802 0.01990 0.01204 -0.0452 0.6061 0.0126
-5.250 -0.2544 0.01908 0.01107 -0.0450 0.6009 0.0134
-5.000 -0.2279 0.01836 0.01015 -0.0447 0.5956 0.0150
-4.750 -0.2011 0.01775 0.00943 -0.0445 0.5898 0.0171
-4.500 -0.1744 0.01707 0.00857 -0.0441 0.5848 0.0193
-4.250 -0.1475 0.01643 0.00778 -0.0438 0.5802 0.0225
-4.000 -0.1203 0.01591 0.00722 -0.0436 0.5751 0.0274
-3.750 -0.0929 0.01551 0.00674 -0.0433 0.5702 0.0350
-3.500 -0.0656 0.01520 0.00635 -0.0431 0.5660 0.0434
-3.250 -0.0378 0.01495 0.00609 -0.0430 0.5611 0.0528
-3.000 -0.0100 0.01472 0.00581 -0.0428 0.5565 0.0621
-2.750 0.0175 0.01450 0.00552 -0.0426 0.5522 0.0709
-2.500 0.0451 0.01429 0.00524 -0.0424 0.5483 0.0797
-2.250 0.0731 0.01411 0.00502 -0.0422 0.5436 0.0893
-2.000 0.1008 0.01393 0.00482 -0.0421 0.5394 0.0995
-1.750 0.1284 0.01376 0.00462 -0.0419 0.5354 0.1101
-1.500 0.1560 0.01362 0.00444 -0.0417 0.5316 0.1216
-1.250 0.1838 0.01348 0.00430 -0.0416 0.5272 0.1346
-1.000 0.2116 0.01335 0.00417 -0.0414 0.5230 0.1496
-0.750 0.2391 0.01323 0.00404 -0.0412 0.5192 0.1675
-0.500 0.2665 0.01311 0.00395 -0.0411 0.5156 0.1908
-0.250 0.2941 0.01296 0.00391 -0.0410 0.5113 0.2229
0.000 0.3213 0.01279 0.00387 -0.0408 0.5071 0.2713
0.250 0.3475 0.01248 0.00381 -0.0406 0.5034 0.3609
0.500 0.4124 0.01087 0.00379 -0.0476 0.4989 0.9995
0.750 0.4395 0.01096 0.00380 -0.0473 0.4945 1.0000
1.000 0.4660 0.01105 0.00380 -0.0469 0.4903 1.0000
1.250 0.4924 0.01116 0.00379 -0.0465 0.4866 1.0000
1.500 0.5189 0.01129 0.00381 -0.0461 0.4830 1.0000
1.750 0.5455 0.01140 0.00389 -0.0458 0.4784 1.0000
2.000 0.5721 0.01151 0.00394 -0.0455 0.4742 1.0000
2.250 0.5987 0.01163 0.00398 -0.0451 0.4704 1.0000
2.500 0.6252 0.01177 0.00406 -0.0448 0.4666 1.0000
2.750 0.6520 0.01190 0.00418 -0.0446 0.4619 1.0000
3.000 0.6786 0.01203 0.00428 -0.0443 0.4575 1.0000
3.250 0.7051 0.01217 0.00435 -0.0440 0.4537 1.0000
3.500 0.7318 0.01232 0.00450 -0.0437 0.4493 1.0000
3.750 0.7584 0.01246 0.00465 -0.0435 0.4444 1.0000
4.000 0.7850 0.01260 0.00478 -0.0432 0.4400 1.0000
4.250 0.8115 0.01276 0.00489 -0.0429 0.4360 1.0000
4.500 0.8381 0.01292 0.00511 -0.0427 0.4307 1.0000
4.750 0.8646 0.01308 0.00528 -0.0425 0.4258 1.0000
5.000 0.8909 0.01324 0.00540 -0.0422 0.4216 1.0000
5.250 0.9173 0.01343 0.00565 -0.0420 0.4160 1.0000
5.500 0.9436 0.01360 0.00585 -0.0418 0.4107 1.0000
5.750 0.9697 0.01378 0.00601 -0.0415 0.4061 1.0000
6.000 0.9958 0.01398 0.00630 -0.0413 0.4000 1.0000
6.250 1.0218 0.01418 0.00652 -0.0410 0.3944 1.0000
6.500 1.0476 0.01439 0.00676 -0.0408 0.3891 1.0000
6.750 1.0733 0.01461 0.00706 -0.0405 0.3824 1.0000
7.000 1.0987 0.01483 0.00729 -0.0402 0.3765 1.0000
7.250 1.1241 0.01508 0.00763 -0.0399 0.3694 1.0000
7.500 1.1491 0.01532 0.00789 -0.0396 0.3623 1.0000
7.750 1.1739 0.01559 0.00825 -0.0393 0.3546 1.0000
8.000 1.1982 0.01587 0.00855 -0.0389 0.3467 1.0000
8.250 1.2225 0.01618 0.00894 -0.0385 0.3381 1.0000
8.500 1.2460 0.01651 0.00930 -0.0381 0.3298 1.0000
8.750 1.2694 0.01686 0.00974 -0.0377 0.3203 1.0000
9.000 1.2921 0.01725 0.01019 -0.0371 0.3109 1.0000
9.500 1.3351 0.01815 0.01119 -0.0359 0.2895 1.0000
9.750 1.3553 0.01867 0.01177 -0.0352 0.2778 1.0000
10.000 1.3743 0.01925 0.01239 -0.0344 0.2660 1.0000
10.250 1.3915 0.01992 0.01310 -0.0334 0.2534 1.0000
10.500 1.4067 0.02068 0.01388 -0.0322 0.2403 1.0000
10.750 1.4193 0.02156 0.01478 -0.0308 0.2266 1.0000
11.000 1.4286 0.02256 0.01580 -0.0292 0.2130 1.0000
11.250 1.4322 0.02369 0.01696 -0.0269 0.2004 1.0000
11.500 1.4323 0.02513 0.01843 -0.0248 0.1886 1.0000
11.750 1.4313 0.02697 0.02030 -0.0234 0.1771 1.0000
12.000 1.4290 0.02919 0.02253 -0.0225 0.1657 1.0000
12.250 1.4256 0.03171 0.02507 -0.0220 0.1552 1.0000
12.500 1.4214 0.03446 0.02783 -0.0217 0.1450 1.0000
12.750 1.4181 0.03723 0.03064 -0.0215 0.1354 1.0000
13.000 1.4131 0.04024 0.03368 -0.0214 0.1270 1.0000
13.250 1.4068 0.04347 0.03694 -0.0214 0.1192 1.0000
13.500 1.4025 0.04654 0.04007 -0.0216 0.1116 1.0000
13.750 1.3948 0.05006 0.04361 -0.0218 0.1051 1.0000
14.000 1.3904 0.05329 0.04690 -0.0221 0.0984 1.0000
14.250 1.3831 0.05692 0.05057 -0.0226 0.0927 1.0000
14.500 1.3787 0.06039 0.05410 -0.0232 0.0867 1.0000
14.750 1.3719 0.06428 0.05804 -0.0240 0.0815 1.0000
15.000 1.3680 0.06792 0.06174 -0.0248 0.0759 1.0000
15.250 1.3610 0.07207 0.06593 -0.0259 0.0715 1.0000
15.500 1.3575 0.07583 0.06979 -0.0269 0.0667 1.0000
15.750 1.3497 0.08029 0.07428 -0.0283 0.0626 1.0000
16.000 1.3468 0.08412 0.07821 -0.0294 0.0586 1.0000
16.250 1.3405 0.08854 0.08269 -0.0308 0.0550 1.0000
16.500 1.3353 0.09288 0.08711 -0.0323 0.0518 1.0000
16.750 1.3306 0.09722 0.09153 -0.0338 0.0486 1.0000
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Polar data table (+)
Polar graphs
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