EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 593 AIRFOIL (e593-il) Reynolds number: 500,000 Max Cl/Cd: 115.24 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e593-il-500000.txt Download as CSV file: xf-e593-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3766 0.10315 0.09932 0.0042 0.5097 0.0196
-8.750 -0.3763 0.09866 0.09486 0.0012 0.5085 0.0197
-8.500 -0.3729 0.09469 0.09091 -0.0001 0.5070 0.0198
-8.250 -0.3659 0.09183 0.08804 -0.0009 0.5051 0.0200
-8.000 -0.3577 0.08931 0.08552 -0.0014 0.5035 0.0203
-7.750 -0.3514 0.08654 0.08275 -0.0026 0.5019 0.0205
-7.500 -0.3473 0.08356 0.07977 -0.0039 0.5005 0.0208
-7.250 -0.3453 0.08056 0.07678 -0.0053 0.4990 0.0212
-7.000 -0.3461 0.07747 0.07370 -0.0072 0.4975 0.0215
-6.750 -0.3410 0.07356 0.06981 -0.0110 0.4965 0.0220
-6.500 -0.3863 0.03615 0.03178 -0.0365 0.4997 0.0134
-6.250 -0.3766 0.02752 0.02232 -0.0382 0.4985 0.0118
-6.000 -0.3613 0.02064 0.01416 -0.0377 0.4971 0.0106
-5.750 -0.3362 0.01903 0.01224 -0.0373 0.4955 0.0106
-5.500 -0.3103 0.01776 0.01076 -0.0369 0.4935 0.0107
-5.250 -0.2839 0.01674 0.00957 -0.0365 0.4913 0.0108
-5.000 -0.2571 0.01593 0.00863 -0.0362 0.4891 0.0111
-4.750 -0.2300 0.01523 0.00781 -0.0358 0.4871 0.0115
-4.500 -0.2027 0.01462 0.00708 -0.0355 0.4853 0.0121
-4.250 -0.1751 0.01414 0.00646 -0.0352 0.4835 0.0129
-4.000 -0.1480 0.01361 0.00585 -0.0349 0.4814 0.0143
-3.750 -0.1202 0.01310 0.00531 -0.0346 0.4801 0.0175
-3.500 -0.0924 0.01259 0.00482 -0.0343 0.4785 0.0259
-3.250 -0.0643 0.01230 0.00456 -0.0341 0.4766 0.0370
-3.000 -0.0361 0.01215 0.00443 -0.0340 0.4746 0.0467
-2.750 -0.0079 0.01206 0.00434 -0.0339 0.4727 0.0565
-2.500 0.0204 0.01197 0.00427 -0.0338 0.4710 0.0669
-2.250 0.0486 0.01184 0.00413 -0.0337 0.4694 0.0767
-2.000 0.0767 0.01174 0.00399 -0.0335 0.4678 0.0863
-1.750 0.1050 0.01179 0.00398 -0.0334 0.4660 0.0950
-1.500 0.1332 0.01167 0.00390 -0.0333 0.4646 0.1068
-1.250 0.1615 0.01152 0.00380 -0.0332 0.4632 0.1189
-1.000 0.1899 0.01141 0.00372 -0.0331 0.4614 0.1321
-0.750 0.2182 0.01131 0.00366 -0.0330 0.4596 0.1473
-0.500 0.2464 0.01121 0.00361 -0.0330 0.4579 0.1658
-0.250 0.2746 0.01112 0.00357 -0.0329 0.4563 0.1917
0.000 0.3026 0.01098 0.00356 -0.0328 0.4548 0.2347
0.250 0.3302 0.01077 0.00356 -0.0327 0.4534 0.3102
0.500 0.3528 0.00982 0.00360 -0.0321 0.4520 0.6372
0.750 0.4104 0.00918 0.00374 -0.0377 0.4498 1.0000
1.000 0.4375 0.00924 0.00376 -0.0374 0.4484 1.0000
1.250 0.4646 0.00931 0.00380 -0.0370 0.4469 1.0000
1.500 0.4918 0.00941 0.00387 -0.0368 0.4454 1.0000
1.750 0.5189 0.00951 0.00394 -0.0365 0.4438 1.0000
2.000 0.5462 0.00961 0.00401 -0.0362 0.4421 1.0000
2.250 0.5735 0.00971 0.00406 -0.0360 0.4404 1.0000
2.500 0.6009 0.00980 0.00411 -0.0357 0.4388 1.0000
2.750 0.6283 0.00992 0.00418 -0.0355 0.4373 1.0000
3.000 0.6557 0.01008 0.00429 -0.0353 0.4359 1.0000
3.250 0.6829 0.01036 0.00453 -0.0351 0.4340 1.0000
3.500 0.7104 0.01043 0.00463 -0.0350 0.4326 1.0000
3.750 0.7380 0.01052 0.00475 -0.0349 0.4307 1.0000
4.000 0.7655 0.01062 0.00488 -0.0347 0.4287 1.0000
4.250 0.7931 0.01071 0.00497 -0.0346 0.4266 1.0000
4.500 0.8208 0.01077 0.00503 -0.0345 0.4246 1.0000
4.750 0.8485 0.01083 0.00506 -0.0344 0.4225 1.0000
5.000 0.8761 0.01095 0.00514 -0.0343 0.4205 1.0000
5.250 0.9035 0.01113 0.00534 -0.0342 0.4182 1.0000
5.500 0.9310 0.01118 0.00546 -0.0341 0.4157 1.0000
5.750 0.9586 0.01123 0.00556 -0.0340 0.4129 1.0000
6.000 0.9863 0.01126 0.00561 -0.0339 0.4103 1.0000
6.250 1.0140 0.01127 0.00561 -0.0339 0.4076 1.0000
6.500 1.0415 0.01136 0.00568 -0.0338 0.4049 1.0000
6.750 1.0688 0.01143 0.00584 -0.0337 0.4019 1.0000
7.000 1.0963 0.01147 0.00595 -0.0337 0.3985 1.0000
7.250 1.1238 0.01147 0.00600 -0.0336 0.3952 1.0000
7.500 1.1514 0.01148 0.00602 -0.0335 0.3920 1.0000
7.750 1.1786 0.01156 0.00613 -0.0335 0.3881 1.0000
8.000 1.2058 0.01155 0.00624 -0.0334 0.3832 1.0000
8.250 1.2332 0.01154 0.00627 -0.0333 0.3786 1.0000
8.500 1.2602 0.01161 0.00637 -0.0333 0.3739 1.0000
8.750 1.2873 0.01164 0.00652 -0.0332 0.3675 1.0000
9.000 1.3140 0.01170 0.00658 -0.0331 0.3614 1.0000
9.250 1.3410 0.01178 0.00679 -0.0331 0.3530 1.0000
9.500 1.3673 0.01191 0.00697 -0.0330 0.3434 1.0000
9.750 1.3932 0.01209 0.00718 -0.0329 0.3314 1.0000
10.000 1.4184 0.01237 0.00748 -0.0328 0.3154 1.0000
10.250 1.4418 0.01285 0.00792 -0.0326 0.2928 1.0000
10.500 1.4625 0.01364 0.00860 -0.0322 0.2644 1.0000
11.000 1.4975 0.01584 0.01059 -0.0310 0.2099 1.0000
11.250 1.5122 0.01709 0.01177 -0.0303 0.1860 1.0000
11.500 1.5240 0.01850 0.01310 -0.0294 0.1656 1.0000
11.750 1.5343 0.01990 0.01447 -0.0284 0.1484 1.0000
12.000 1.5390 0.02158 0.01614 -0.0272 0.1338 1.0000
12.250 1.5301 0.02400 0.01862 -0.0255 0.1257 1.0000
12.500 1.5181 0.02811 0.02282 -0.0268 0.1188 1.0000
12.750 1.5037 0.03242 0.02717 -0.0274 0.1130 1.0000
13.000 1.4931 0.03610 0.03090 -0.0276 0.1064 1.0000
13.500 1.4692 0.04357 0.03843 -0.0279 0.0951 1.0000
13.750 1.4568 0.04741 0.04227 -0.0281 0.0897 1.0000
14.000 1.4496 0.05074 0.04565 -0.0284 0.0844 1.0000
14.250 1.4395 0.05445 0.04937 -0.0287 0.0793 1.0000
14.500 1.4352 0.05772 0.05267 -0.0292 0.0741 1.0000
14.750 1.4288 0.06138 0.05634 -0.0298 0.0691 1.0000
15.000 1.4254 0.06475 0.05975 -0.0304 0.0645 1.0000
15.250 1.4209 0.06837 0.06338 -0.0312 0.0596 1.0000
15.500 1.4173 0.07194 0.06698 -0.0320 0.0553 1.0000
15.750 1.4147 0.07544 0.07052 -0.0329 0.0513 1.0000
16.000 1.4085 0.07951 0.07459 -0.0339 0.0476 1.0000
16.250 1.4085 0.08278 0.07793 -0.0348 0.0439 1.0000
16.500 1.4028 0.08696 0.08213 -0.0361 0.0408 1.0000
16.750 1.4013 0.09059 0.08583 -0.0372 0.0379 1.0000
17.000 1.3977 0.09454 0.08982 -0.0384 0.0352 1.0000
17.250 1.3911 0.09908 0.09438 -0.0400 0.0326 1.0000
17.500 1.3914 0.10259 0.09797 -0.0412 0.0300 1.0000
17.750 1.3857 0.10712 0.10253 -0.0430 0.0280 1.0000
18.000 1.3819 0.11141 0.10688 -0.0446 0.0261 1.0000
18.250 1.3797 0.11548 0.11103 -0.0462 0.0244 1.0000
18.500 1.3744 0.12015 0.11574 -0.0482 0.0228 1.0000
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Polar data table (+)
Polar graphs
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