EPPLER 625 AIRFOIL (e625-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 625 AIRFOIL (e625-il) Reynolds number: 200,000 Max Cl/Cd: 60.06 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e625-il-200000-n5.txt Download as CSV file: xf-e625-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 625 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4756 0.07987 0.07634 -0.0299 1.0000 0.0201
-9.750 -0.4887 0.07385 0.07033 -0.0342 1.0000 0.0200
-9.500 -0.5107 0.06772 0.06414 -0.0364 1.0000 0.0200
-9.250 -0.5369 0.06194 0.05824 -0.0356 1.0000 0.0200
-9.000 -0.5329 0.06205 0.05840 -0.0334 1.0000 0.0196
-8.750 -0.5648 0.05572 0.05186 -0.0295 1.0000 0.0198
-8.500 -0.5813 0.05099 0.04691 -0.0258 1.0000 0.0198
-8.250 -0.5965 0.04641 0.04205 -0.0214 1.0000 0.0199
-8.000 -0.6013 0.04242 0.03775 -0.0180 0.9918 0.0198
-7.750 -0.5860 0.03778 0.03264 -0.0184 0.9520 0.0197
-7.500 -0.5662 0.03354 0.02782 -0.0187 0.9235 0.0197
-7.250 -0.5458 0.03034 0.02404 -0.0181 0.8972 0.0198
-7.000 -0.5247 0.02798 0.02120 -0.0172 0.8738 0.0199
-6.750 -0.5040 0.02615 0.01892 -0.0158 0.8525 0.0201
-6.500 -0.4822 0.02458 0.01709 -0.0147 0.8333 0.0204
-6.250 -0.4597 0.02345 0.01575 -0.0137 0.8153 0.0207
-6.000 -0.4365 0.02240 0.01451 -0.0127 0.7985 0.0210
-5.750 -0.4130 0.02157 0.01351 -0.0118 0.7825 0.0216
-5.500 -0.3888 0.02079 0.01256 -0.0109 0.7673 0.0223
-5.250 -0.3640 0.02004 0.01161 -0.0101 0.7525 0.0233
-5.000 -0.3386 0.01925 0.01064 -0.0094 0.7384 0.0238
-4.750 -0.3131 0.01850 0.00974 -0.0086 0.7244 0.0242
-4.500 -0.2887 0.01774 0.00891 -0.0078 0.7109 0.0248
-4.250 -0.2647 0.01716 0.00828 -0.0070 0.6972 0.0254
-4.000 -0.2411 0.01665 0.00771 -0.0060 0.6840 0.0261
-3.750 -0.2176 0.01620 0.00718 -0.0050 0.6713 0.0271
-3.500 -0.1943 0.01581 0.00668 -0.0039 0.6590 0.0283
-3.250 -0.1710 0.01544 0.00624 -0.0028 0.6463 0.0298
-3.000 -0.1476 0.01511 0.00587 -0.0018 0.6339 0.0323
-2.750 -0.1241 0.01482 0.00550 -0.0008 0.6218 0.0354
-2.500 -0.1010 0.01452 0.00515 0.0003 0.6098 0.0396
-2.250 -0.0780 0.01421 0.00484 0.0015 0.5976 0.0495
-2.000 -0.0560 0.01385 0.00459 0.0027 0.5860 0.0797
-1.750 -0.0343 0.01353 0.00440 0.0040 0.5747 0.1221
-1.500 -0.0129 0.01324 0.00422 0.0052 0.5635 0.1701
-1.250 0.0017 0.01251 0.00401 0.0076 0.5530 0.3027
-1.000 0.0540 0.01162 0.00517 0.0046 0.5397 0.8711
-0.750 0.0802 0.01202 0.00543 0.0057 0.5289 0.8909
-0.500 0.1272 0.01255 0.00578 0.0027 0.5153 0.9012
-0.250 0.1632 0.01292 0.00601 0.0016 0.5033 0.9117
0.000 0.2024 0.01332 0.00626 -0.0001 0.4912 0.9226
0.250 0.2594 0.01384 0.00661 -0.0054 0.4770 0.9320
0.500 0.2857 0.01395 0.00659 -0.0050 0.4661 0.9376
0.750 0.3078 0.01395 0.00651 -0.0039 0.4559 0.9408
1.000 0.3385 0.01398 0.00643 -0.0046 0.4451 0.9422
1.250 0.3686 0.01402 0.00636 -0.0051 0.4342 0.9438
1.500 0.3975 0.01405 0.00632 -0.0054 0.4238 0.9456
1.750 0.4248 0.01411 0.00628 -0.0054 0.4142 0.9476
2.000 0.4509 0.01417 0.00627 -0.0052 0.4038 0.9503
2.250 0.4737 0.01424 0.00629 -0.0043 0.3952 0.9533
2.500 0.4958 0.01432 0.00630 -0.0032 0.3865 0.9559
2.750 0.5265 0.01439 0.00631 -0.0040 0.3769 0.9573
3.000 0.5560 0.01449 0.00634 -0.0045 0.3681 0.9588
3.250 0.5845 0.01457 0.00639 -0.0048 0.3594 0.9604
3.500 0.6115 0.01469 0.00645 -0.0049 0.3514 0.9622
3.750 0.6381 0.01480 0.00653 -0.0048 0.3430 0.9644
4.000 0.6626 0.01495 0.00664 -0.0043 0.3357 0.9671
4.250 0.6837 0.01509 0.00677 -0.0031 0.3282 0.9699
4.500 0.7125 0.01524 0.00687 -0.0036 0.3209 0.9711
4.750 0.7415 0.01535 0.00699 -0.0041 0.3132 0.9724
5.000 0.7695 0.01555 0.00713 -0.0045 0.3063 0.9740
5.250 0.7978 0.01569 0.00731 -0.0049 0.2994 0.9759
5.500 0.8239 0.01589 0.00749 -0.0049 0.2927 0.9781
5.750 0.8489 0.01608 0.00770 -0.0046 0.2867 0.9801
6.000 0.8722 0.01629 0.00792 -0.0040 0.2806 0.9823
6.250 0.8991 0.01652 0.00812 -0.0042 0.2744 0.9838
6.500 0.9281 0.01670 0.00837 -0.0049 0.2680 0.9854
6.750 0.9558 0.01696 0.00860 -0.0053 0.2620 0.9872
7.000 0.9827 0.01719 0.00888 -0.0055 0.2561 0.9891
7.250 1.0083 0.01745 0.00918 -0.0055 0.2500 0.9909
7.500 1.0326 0.01778 0.00949 -0.0054 0.2451 0.9928
7.750 1.0592 0.01803 0.00983 -0.0056 0.2391 0.9945
8.000 1.0864 0.01833 0.01016 -0.0061 0.2331 0.9963
8.250 1.1133 0.01866 0.01053 -0.0065 0.2278 0.9982
8.500 1.1400 0.01898 0.01093 -0.0069 0.2220 0.9998
8.750 1.1564 0.01935 0.01132 -0.0052 0.2173 1.0000
9.000 1.1718 0.01971 0.01174 -0.0033 0.2127 1.0000
9.250 1.1866 0.02007 0.01217 -0.0013 0.2079 1.0000
9.500 1.1994 0.02049 0.01261 0.0009 0.2035 1.0000
9.750 1.2115 0.02092 0.01309 0.0033 0.1994 1.0000
10.000 1.2235 0.02131 0.01357 0.0057 0.1946 1.0000
10.250 1.2329 0.02176 0.01407 0.0085 0.1905 1.0000
10.750 1.2479 0.02271 0.01514 0.0147 0.1831 1.0000
11.000 1.2527 0.02319 0.01569 0.0182 0.1791 1.0000
11.250 1.2507 0.02368 0.01620 0.0228 0.1759 1.0000
11.500 1.2468 0.02426 0.01678 0.0275 0.1730 1.0000
11.750 1.2502 0.02483 0.01747 0.0308 0.1696 1.0000
12.000 1.2528 0.02554 0.01826 0.0338 0.1658 1.0000
12.250 1.2548 0.02641 0.01917 0.0366 0.1625 1.0000
12.750 1.2622 0.02843 0.02132 0.0409 0.1557 1.0000
13.000 1.2663 0.02959 0.02258 0.0426 0.1519 1.0000
13.250 1.2690 0.03094 0.02397 0.0441 0.1486 1.0000
13.500 1.2710 0.03245 0.02550 0.0454 0.1456 1.0000
13.750 1.2759 0.03389 0.02710 0.0463 0.1419 1.0000
14.000 1.2786 0.03557 0.02888 0.0472 0.1384 1.0000
14.250 1.2790 0.03751 0.03086 0.0478 0.1351 1.0000
14.500 1.2788 0.03960 0.03300 0.0483 0.1319 1.0000
14.750 1.2807 0.04162 0.03517 0.0486 0.1285 1.0000
15.000 1.2804 0.04392 0.03757 0.0487 0.1253 1.0000
15.250 1.2773 0.04653 0.04023 0.0487 0.1223 1.0000
15.500 1.2741 0.04924 0.04299 0.0485 0.1194 1.0000
15.750 1.2720 0.05200 0.04592 0.0481 0.1161 1.0000
16.000 1.2674 0.05512 0.04914 0.0475 0.1129 1.0000
16.250 1.2617 0.05845 0.05253 0.0467 0.1101 1.0000
16.500 1.2551 0.06196 0.05608 0.0458 0.1073 1.0000
16.750 1.2491 0.06563 0.05992 0.0447 0.1041 1.0000
17.000 1.2411 0.06961 0.06401 0.0434 0.1011 1.0000
17.250 1.2311 0.07392 0.06836 0.0419 0.0981 1.0000
17.500 1.2238 0.07788 0.07236 0.0405 0.0959 1.0000
17.750 1.2114 0.08288 0.07753 0.0385 0.0923 1.0000
18.000 1.2009 0.08756 0.08232 0.0367 0.0898 1.0000
18.250 1.1879 0.09271 0.08751 0.0346 0.0868 1.0000
18.500 1.1802 0.09703 0.09187 0.0329 0.0848 1.0000
18.750 1.1652 0.10276 0.09776 0.0304 0.0820 1.0000
19.000 1.1522 0.10819 0.10331 0.0280 0.0795 1.0000
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