EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 593 AIRFOIL (e593-il) Reynolds number: 200,000 Max Cl/Cd: 71.35 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e593-il-200000.txt Download as CSV file: xf-e593-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3602 0.11000 0.10535 0.0060 0.5772 0.0402
-8.750 -0.3673 0.10702 0.10244 0.0008 0.5758 0.0409
-8.500 -0.3697 0.10362 0.09910 -0.0032 0.5739 0.0411
-8.250 -0.3568 0.09911 0.09459 -0.0022 0.5707 0.0416
-8.000 -0.3419 0.09600 0.09146 -0.0012 0.5677 0.0425
-7.750 -0.3334 0.09315 0.08859 -0.0020 0.5654 0.0433
-7.500 -0.3274 0.09016 0.08560 -0.0032 0.5635 0.0442
-7.250 -0.3236 0.08709 0.08252 -0.0049 0.5618 0.0456
-7.000 -0.3242 0.08398 0.07946 -0.0073 0.5602 0.0469
-6.750 -0.3278 0.07940 0.07492 -0.0173 0.5591 0.0487
-6.500 -0.3209 0.07327 0.06872 -0.0259 0.5577 0.0492
-6.250 -0.3101 0.07013 0.06563 -0.0237 0.5552 0.0499
-6.000 -0.2964 0.06741 0.06290 -0.0237 0.5528 0.0508
-5.750 -0.2816 0.06437 0.05982 -0.0251 0.5504 0.0521
-5.500 -0.2768 0.04158 0.03621 -0.0387 0.5513 0.0292
-5.250 -0.2543 0.04156 0.03619 -0.0386 0.5486 0.0302
-5.000 -0.2418 0.02784 0.02087 -0.0403 0.5478 0.0252
-4.750 -0.2175 0.02522 0.01767 -0.0399 0.5457 0.0258
-4.500 -0.1911 0.02326 0.01527 -0.0396 0.5434 0.0273
-4.250 -0.1642 0.02212 0.01393 -0.0394 0.5409 0.0304
-4.000 -0.1362 0.02131 0.01283 -0.0390 0.5384 0.0345
-3.750 -0.1091 0.02031 0.01178 -0.0388 0.5360 0.0398
-3.500 -0.0813 0.01983 0.01116 -0.0385 0.5338 0.0493
-3.250 -0.0541 0.01937 0.01069 -0.0383 0.5316 0.0608
-3.000 -0.0267 0.01923 0.01048 -0.0380 0.5295 0.0725
-2.750 0.0015 0.01894 0.01017 -0.0380 0.5270 0.0841
-2.500 0.0299 0.01888 0.01003 -0.0379 0.5246 0.0949
-2.250 0.0575 0.01848 0.00970 -0.0378 0.5223 0.1069
-2.000 0.0852 0.01818 0.00941 -0.0376 0.5201 0.1191
-1.750 0.1128 0.01794 0.00916 -0.0375 0.5181 0.1323
-1.500 0.1403 0.01773 0.00893 -0.0372 0.5162 0.1467
-1.250 0.1676 0.01760 0.00877 -0.0370 0.5143 0.1627
-1.000 0.1951 0.01752 0.00877 -0.0369 0.5121 0.1814
-0.750 0.2228 0.01745 0.00880 -0.0369 0.5097 0.2050
-0.500 0.2500 0.01733 0.00886 -0.0369 0.5074 0.2373
-0.250 0.2765 0.01709 0.00893 -0.0368 0.5053 0.2989
0.000 0.3319 0.01516 0.00895 -0.0419 0.5030 1.0000
0.250 0.3584 0.01539 0.00900 -0.0414 0.5010 1.0000
0.500 0.3847 0.01564 0.00908 -0.0410 0.4992 1.0000
0.750 0.4108 0.01603 0.00931 -0.0406 0.4975 1.0000
1.000 0.4376 0.01644 0.00973 -0.0406 0.4951 1.0000
1.250 0.4641 0.01688 0.01016 -0.0406 0.4926 1.0000
1.500 0.4906 0.01727 0.01052 -0.0405 0.4901 1.0000
1.750 0.5171 0.01757 0.01077 -0.0402 0.4877 1.0000
2.000 0.5437 0.01784 0.01096 -0.0399 0.4857 1.0000
2.250 0.5703 0.01815 0.01119 -0.0397 0.4841 1.0000
2.500 0.5968 0.01852 0.01148 -0.0394 0.4825 1.0000
2.750 0.6227 0.01908 0.01206 -0.0393 0.4802 1.0000
3.000 0.6483 0.01977 0.01287 -0.0396 0.4765 1.0000
3.250 0.6742 0.02033 0.01346 -0.0396 0.4737 1.0000
3.500 0.7005 0.02068 0.01380 -0.0394 0.4712 1.0000
3.750 0.7271 0.02090 0.01398 -0.0391 0.4692 1.0000
4.000 0.7539 0.02113 0.01414 -0.0387 0.4675 1.0000
4.250 0.7804 0.02146 0.01442 -0.0383 0.4659 1.0000
4.500 0.8032 0.02264 0.01583 -0.0388 0.4606 1.0000
4.750 0.8283 0.02321 0.01647 -0.0388 0.4570 1.0000
5.000 0.8548 0.02337 0.01663 -0.0385 0.4545 1.0000
5.250 0.8822 0.02338 0.01660 -0.0381 0.4526 1.0000
5.500 0.9096 0.02341 0.01657 -0.0376 0.4508 1.0000
5.750 0.9308 0.02465 0.01802 -0.0379 0.4453 1.0000
6.000 0.9553 0.02515 0.01862 -0.0378 0.4410 1.0000
6.250 0.9828 0.02503 0.01849 -0.0373 0.4385 1.0000
6.500 1.0113 0.02475 0.01817 -0.0368 0.4365 1.0000
6.750 1.0400 0.02450 0.01787 -0.0363 0.4347 1.0000
7.000 1.0582 0.02589 0.01955 -0.0365 0.4270 1.0000
7.250 1.0863 0.02558 0.01925 -0.0361 0.4239 1.0000
7.500 1.1161 0.02498 0.01862 -0.0355 0.4215 1.0000
7.750 1.1464 0.02438 0.01796 -0.0351 0.4195 1.0000
8.000 1.1653 0.02537 0.01923 -0.0349 0.4119 1.0000
8.250 1.1943 0.02483 0.01871 -0.0345 0.4084 1.0000
8.500 1.2254 0.02398 0.01781 -0.0341 0.4058 1.0000
8.750 1.2487 0.02418 0.01818 -0.0337 0.3995 1.0000
9.000 1.2767 0.02362 0.01769 -0.0333 0.3942 1.0000
9.250 1.3086 0.02258 0.01658 -0.0329 0.3907 1.0000
9.500 1.3309 0.02273 0.01697 -0.0325 0.3828 1.0000
9.750 1.3608 0.02186 0.01610 -0.0321 0.3774 1.0000
10.000 1.3846 0.02175 0.01617 -0.0316 0.3689 1.0000
10.250 1.4140 0.02092 0.01532 -0.0312 0.3617 1.0000
10.500 1.4367 0.02088 0.01550 -0.0307 0.3500 1.0000
10.750 1.4602 0.02078 0.01552 -0.0302 0.3367 1.0000
11.000 1.4827 0.02078 0.01556 -0.0296 0.3207 1.0000
11.250 1.5014 0.02120 0.01605 -0.0289 0.2998 1.0000
11.500 1.5155 0.02196 0.01675 -0.0278 0.2757 1.0000
11.750 1.5219 0.02335 0.01803 -0.0265 0.2512 1.0000
12.000 1.5199 0.02528 0.01992 -0.0248 0.2308 1.0000
12.250 1.5045 0.02803 0.02266 -0.0231 0.2178 1.0000
12.500 1.4870 0.03213 0.02674 -0.0236 0.2056 1.0000
12.750 1.4708 0.03632 0.03088 -0.0242 0.1939 1.0000
13.000 1.4568 0.04032 0.03488 -0.0246 0.1824 1.0000
13.250 1.4437 0.04420 0.03875 -0.0250 0.1716 1.0000
13.500 1.4314 0.04801 0.04253 -0.0253 0.1617 1.0000
13.750 1.4190 0.05185 0.04628 -0.0257 0.1526 1.0000
14.000 1.4094 0.05555 0.05002 -0.0262 0.1427 1.0000
14.250 1.4007 0.05920 0.05367 -0.0267 0.1339 1.0000
14.500 1.3923 0.06296 0.05735 -0.0273 0.1257 1.0000
14.750 1.3865 0.06672 0.06116 -0.0282 0.1169 1.0000
15.000 1.3811 0.07042 0.06486 -0.0290 0.1091 1.0000
15.250 1.3750 0.07427 0.06866 -0.0299 0.1017 1.0000
15.500 1.3714 0.07801 0.07248 -0.0309 0.0945 1.0000
15.750 1.3673 0.08165 0.07603 -0.0317 0.0882 1.0000
16.000 1.3640 0.08555 0.08005 -0.0329 0.0821 1.0000
16.250 1.3605 0.08923 0.08366 -0.0339 0.0764 1.0000
16.500 1.3574 0.09322 0.08777 -0.0352 0.0711 1.0000
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