EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 593 AIRFOIL (e593-il) Reynolds number: 200,000 Max Cl/Cd: 74.23 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e593-il-200000-n5.txt Download as CSV file: xf-e593-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 593 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3917 0.11438 0.10941 0.0109 0.5237 0.0159
-9.500 -0.3828 0.11145 0.10647 0.0101 0.5214 0.0154
-9.000 -0.3829 0.10126 0.09630 0.0051 0.5187 0.0129
-8.750 -0.3777 0.09795 0.09299 0.0036 0.5170 0.0128
-8.500 -0.3731 0.09457 0.08960 0.0020 0.5154 0.0126
-8.250 -0.3689 0.09122 0.08624 0.0004 0.5139 0.0124
-8.000 -0.3674 0.08728 0.08232 -0.0016 0.5126 0.0123
-7.750 -0.3654 0.08368 0.07875 -0.0035 0.5110 0.0121
-7.500 -0.3668 0.07972 0.07484 -0.0057 0.5095 0.0119
-7.250 -0.3706 0.07550 0.07066 -0.0086 0.5081 0.0118
-7.000 -0.3697 0.07017 0.06534 -0.0134 0.5066 0.0116
-6.750 -0.4192 0.03292 0.02677 -0.0375 0.5105 0.0101
-6.500 -0.4015 0.02815 0.02124 -0.0382 0.5085 0.0102
-6.250 -0.3788 0.02609 0.01885 -0.0382 0.5060 0.0105
-6.000 -0.3546 0.02449 0.01695 -0.0381 0.5035 0.0108
-5.750 -0.3296 0.02307 0.01523 -0.0379 0.5011 0.0113
-5.500 -0.3041 0.02176 0.01359 -0.0376 0.4990 0.0119
-5.250 -0.2781 0.02060 0.01210 -0.0372 0.4971 0.0126
-5.000 -0.2516 0.01972 0.01108 -0.0370 0.4950 0.0135
-4.750 -0.2245 0.01909 0.01031 -0.0368 0.4928 0.0153
-4.500 -0.1974 0.01847 0.00959 -0.0366 0.4906 0.0175
-4.250 -0.1701 0.01781 0.00877 -0.0363 0.4885 0.0203
-4.000 -0.1428 0.01722 0.00806 -0.0361 0.4865 0.0240
-3.750 -0.1154 0.01679 0.00758 -0.0359 0.4845 0.0303
-3.500 -0.0878 0.01646 0.00717 -0.0357 0.4826 0.0382
-3.250 -0.0600 0.01622 0.00687 -0.0355 0.4808 0.0473
-3.000 -0.0320 0.01599 0.00663 -0.0354 0.4788 0.0564
-2.750 -0.0041 0.01576 0.00639 -0.0352 0.4769 0.0651
-2.500 0.0239 0.01554 0.00615 -0.0350 0.4750 0.0739
-2.250 0.0518 0.01537 0.00593 -0.0349 0.4731 0.0832
-2.000 0.0798 0.01523 0.00574 -0.0347 0.4712 0.0934
-1.750 0.1076 0.01507 0.00556 -0.0346 0.4694 0.1039
-1.500 0.1354 0.01493 0.00539 -0.0344 0.4677 0.1151
-1.250 0.1633 0.01484 0.00524 -0.0342 0.4661 0.1274
-1.000 0.1912 0.01476 0.00516 -0.0341 0.4645 0.1411
-0.750 0.2192 0.01467 0.00512 -0.0340 0.4627 0.1574
-0.500 0.2470 0.01457 0.00510 -0.0339 0.4609 0.1772
-0.250 0.2748 0.01448 0.00509 -0.0339 0.4591 0.2042
0.000 0.3024 0.01436 0.00509 -0.0338 0.4572 0.2423
0.500 0.3538 0.01354 0.00508 -0.0331 0.4537 0.4993
0.750 0.4083 0.01245 0.00507 -0.0377 0.4519 1.0000
1.000 0.4352 0.01260 0.00509 -0.0374 0.4506 1.0000
1.250 0.4622 0.01278 0.00517 -0.0371 0.4493 1.0000
1.500 0.4893 0.01295 0.00532 -0.0369 0.4475 1.0000
1.750 0.5164 0.01313 0.00546 -0.0367 0.4454 1.0000
2.000 0.5436 0.01330 0.00560 -0.0364 0.4433 1.0000
2.250 0.5707 0.01346 0.00572 -0.0362 0.4413 1.0000
2.500 0.5979 0.01364 0.00585 -0.0360 0.4397 1.0000
2.750 0.6251 0.01381 0.00599 -0.0358 0.4382 1.0000
3.000 0.6523 0.01398 0.00610 -0.0356 0.4367 1.0000
3.250 0.6795 0.01415 0.00622 -0.0354 0.4353 1.0000
3.500 0.7066 0.01435 0.00639 -0.0353 0.4337 1.0000
3.750 0.7336 0.01461 0.00672 -0.0352 0.4314 1.0000
4.000 0.7605 0.01485 0.00702 -0.0351 0.4291 1.0000
4.250 0.7875 0.01507 0.00727 -0.0350 0.4268 1.0000
4.500 0.8146 0.01525 0.00747 -0.0348 0.4247 1.0000
4.750 0.8417 0.01543 0.00764 -0.0347 0.4229 1.0000
5.000 0.8689 0.01557 0.00778 -0.0345 0.4211 1.0000
5.250 0.8961 0.01571 0.00790 -0.0343 0.4194 1.0000
5.500 0.9225 0.01600 0.00830 -0.0343 0.4164 1.0000
5.750 0.9490 0.01624 0.00865 -0.0342 0.4130 1.0000
6.000 0.9758 0.01639 0.00886 -0.0340 0.4100 1.0000
6.250 1.0029 0.01647 0.00896 -0.0339 0.4074 1.0000
6.500 1.0301 0.01652 0.00901 -0.0337 0.4051 1.0000
6.750 1.0562 0.01677 0.00938 -0.0336 0.4015 1.0000
7.000 1.0823 0.01698 0.00971 -0.0334 0.3972 1.0000
7.250 1.1091 0.01703 0.00983 -0.0333 0.3936 1.0000
7.500 1.1363 0.01699 0.00980 -0.0331 0.3904 1.0000
7.750 1.1617 0.01726 0.01023 -0.0329 0.3853 1.0000
8.000 1.1878 0.01738 0.01047 -0.0328 0.3803 1.0000
8.250 1.2146 0.01735 0.01047 -0.0325 0.3763 1.0000
8.500 1.2397 0.01762 0.01092 -0.0324 0.3699 1.0000
8.750 1.2658 0.01765 0.01103 -0.0322 0.3635 1.0000
9.000 1.2909 0.01784 0.01136 -0.0320 0.3556 1.0000
9.250 1.3166 0.01787 0.01144 -0.0317 0.3477 1.0000
9.500 1.3409 0.01815 0.01188 -0.0315 0.3371 1.0000
9.750 1.3649 0.01840 0.01221 -0.0312 0.3251 1.0000
10.000 1.3881 0.01870 0.01256 -0.0308 0.3100 1.0000
10.250 1.4093 0.01914 0.01298 -0.0303 0.2912 1.0000
10.500 1.4275 0.01987 0.01368 -0.0297 0.2679 1.0000
10.750 1.4414 0.02096 0.01470 -0.0289 0.2444 1.0000
11.000 1.4507 0.02240 0.01607 -0.0279 0.2232 1.0000
11.250 1.4553 0.02411 0.01776 -0.0267 0.2053 1.0000
11.500 1.4518 0.02622 0.01989 -0.0253 0.1914 1.0000
11.750 1.4374 0.02971 0.02343 -0.0253 0.1817 1.0000
12.000 1.4264 0.03353 0.02730 -0.0260 0.1721 1.0000
12.250 1.4141 0.03744 0.03122 -0.0266 0.1630 1.0000
12.500 1.4029 0.04117 0.03496 -0.0269 0.1543 1.0000
12.750 1.3934 0.04473 0.03854 -0.0272 0.1456 1.0000
13.000 1.3830 0.04839 0.04220 -0.0275 0.1378 1.0000
13.250 1.3756 0.05180 0.04562 -0.0279 0.1296 1.0000
13.500 1.3681 0.05526 0.04910 -0.0283 0.1222 1.0000
13.750 1.3613 0.05872 0.05257 -0.0287 0.1151 1.0000
14.000 1.3574 0.06205 0.05594 -0.0293 0.1078 1.0000
14.250 1.3516 0.06574 0.05962 -0.0301 0.1012 1.0000
14.500 1.3503 0.06896 0.06290 -0.0308 0.0943 1.0000
14.750 1.3453 0.07274 0.06668 -0.0317 0.0882 1.0000
15.000 1.3443 0.07606 0.07006 -0.0325 0.0820 1.0000
15.250 1.3398 0.07993 0.07395 -0.0335 0.0766 1.0000
15.500 1.3389 0.08336 0.07744 -0.0345 0.0710 1.0000
15.750 1.3339 0.08747 0.08156 -0.0357 0.0667 1.0000
16.000 1.3342 0.09082 0.08500 -0.0367 0.0619 1.0000
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Polar data table (+)
Polar graphs
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