EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 604 AIRFOIL (e604-il) Reynolds number: 200,000 Max Cl/Cd: 65.12 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e604-il-200000.txt Download as CSV file: xf-e604-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 604 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2413 0.09531 0.09198 -0.1015 0.9633 0.0604
-11.500 -0.4686 0.04997 0.04499 -0.1269 0.9474 0.0244
-11.250 -0.4573 0.04555 0.04034 -0.1303 0.9434 0.0241
-11.000 -0.4567 0.04192 0.03636 -0.1314 0.9334 0.0240
-10.750 -0.4465 0.03814 0.03213 -0.1333 0.9276 0.0241
-10.500 -0.4394 0.03574 0.02942 -0.1324 0.9170 0.0241
-10.250 -0.4198 0.03306 0.02633 -0.1334 0.9115 0.0242
-10.000 -0.4099 0.03123 0.02419 -0.1316 0.9013 0.0248
-9.750 -0.3774 0.02967 0.02266 -0.1335 0.8967 0.0263
-9.500 -0.3614 0.02867 0.02151 -0.1323 0.8882 0.0275
-9.250 -0.3438 0.02759 0.02009 -0.1313 0.8815 0.0291
-9.000 -0.2972 0.02568 0.01820 -0.1342 0.8792 0.0312
-8.750 -0.2766 0.02489 0.01734 -0.1331 0.8719 0.0332
-8.500 -0.2505 0.02388 0.01629 -0.1329 0.8664 0.0365
-8.250 -0.2308 0.02326 0.01559 -0.1321 0.8607 0.0408
-8.000 -0.2174 0.02252 0.01492 -0.1302 0.8534 0.0453
-7.750 -0.2009 0.02171 0.01408 -0.1289 0.8482 0.0513
-7.500 -0.1884 0.02128 0.01361 -0.1269 0.8424 0.0577
-7.250 -0.1844 0.02069 0.01309 -0.1238 0.8356 0.0648
-7.000 -0.1753 0.02004 0.01244 -0.1215 0.8307 0.0746
-6.750 -0.1703 0.01955 0.01200 -0.1185 0.8245 0.0865
-6.500 -0.1625 0.01899 0.01150 -0.1159 0.8189 0.1043
-6.250 -0.1518 0.01818 0.01084 -0.1141 0.8147 0.1346
-6.000 -0.1452 0.01737 0.01033 -0.1117 0.8100 0.1871
-5.750 -0.1426 0.01632 0.00982 -0.1090 0.8040 0.2865
-5.500 -0.1343 0.01505 0.00957 -0.1070 0.7997 0.4826
-5.250 -0.1060 0.01546 0.01012 -0.1064 0.7971 0.5770
-5.000 -0.0832 0.01606 0.01065 -0.1053 0.7929 0.6081
-4.750 -0.0600 0.01683 0.01137 -0.1037 0.7884 0.6268
-4.500 -0.0326 0.01749 0.01194 -0.1028 0.7848 0.6422
-4.250 -0.0030 0.01835 0.01276 -0.1017 0.7821 0.6519
-4.000 0.0273 0.01896 0.01325 -0.1013 0.7799 0.6617
-3.750 0.0445 0.01971 0.01401 -0.0987 0.7749 0.6693
-3.500 0.0673 0.02018 0.01443 -0.0972 0.7708 0.6777
-3.250 0.0946 0.02097 0.01517 -0.0956 0.7678 0.6844
-3.000 0.1228 0.02155 0.01568 -0.0946 0.7654 0.6945
-2.750 0.1540 0.02232 0.01638 -0.0935 0.7633 0.7013
-2.500 0.1635 0.02251 0.01657 -0.0909 0.7576 0.7101
-2.250 0.1859 0.02292 0.01696 -0.0890 0.7539 0.7139
-2.000 0.2125 0.02295 0.01691 -0.0889 0.7510 0.7200
-1.750 0.2419 0.02266 0.01650 -0.0900 0.7486 0.7264
-1.500 0.2651 0.02285 0.01665 -0.0888 0.7454 0.7291
-1.250 0.2765 0.02309 0.01692 -0.0861 0.7402 0.7331
-1.000 0.3008 0.02289 0.01666 -0.0865 0.7365 0.7384
-0.750 0.3315 0.02255 0.01622 -0.0881 0.7338 0.7425
-0.500 0.3623 0.02245 0.01605 -0.0885 0.7317 0.7443
-0.250 0.3755 0.02268 0.01632 -0.0862 0.7270 0.7470
0.000 0.3936 0.02273 0.01637 -0.0851 0.7222 0.7500
0.250 0.4225 0.02256 0.01614 -0.0861 0.7191 0.7534
0.500 0.4589 0.02223 0.01572 -0.0889 0.7167 0.7567
0.750 0.4944 0.02200 0.01541 -0.0908 0.7147 0.7589
1.000 0.4965 0.02246 0.01597 -0.0866 0.7080 0.7612
1.250 0.5211 0.02243 0.01595 -0.0864 0.7042 0.7631
1.500 0.5532 0.02225 0.01573 -0.0876 0.7015 0.7651
1.750 0.5897 0.02203 0.01545 -0.0896 0.6993 0.7674
2.000 0.6056 0.02232 0.01578 -0.0885 0.6940 0.7709
2.250 0.6315 0.02237 0.01582 -0.0893 0.6891 0.7740
2.500 0.6623 0.02218 0.01563 -0.0901 0.6860 0.7756
2.750 0.6971 0.02194 0.01537 -0.0915 0.6836 0.7772
3.000 0.7205 0.02204 0.01550 -0.0911 0.6797 0.7791
3.250 0.7314 0.02240 0.01593 -0.0887 0.6732 0.7820
3.500 0.7647 0.02221 0.01574 -0.0900 0.6699 0.7846
3.750 0.8055 0.02188 0.01538 -0.0927 0.6674 0.7870
4.000 0.8289 0.02205 0.01558 -0.0928 0.6621 0.7899
4.250 0.8481 0.02213 0.01572 -0.0918 0.6562 0.7920
4.500 0.8831 0.02180 0.01539 -0.0931 0.6528 0.7939
4.750 0.9236 0.02142 0.01501 -0.0953 0.6502 0.7961
5.000 0.9275 0.02188 0.01560 -0.0917 0.6422 0.7994
5.250 0.9619 0.02160 0.01533 -0.0931 0.6378 0.8022
5.500 1.0067 0.02113 0.01483 -0.0964 0.6345 0.8047
5.750 1.0175 0.02142 0.01523 -0.0940 0.6268 0.8077
6.000 1.0476 0.02111 0.01496 -0.0944 0.6216 0.8098
6.250 1.0898 0.02065 0.01448 -0.0970 0.6179 0.8120
6.500 1.0941 0.02095 0.01493 -0.0932 0.6093 0.8156
6.750 1.1305 0.02056 0.01454 -0.0948 0.6039 0.8190
7.000 1.1531 0.02055 0.01460 -0.0944 0.5967 0.8227
7.250 1.1753 0.02032 0.01443 -0.0934 0.5895 0.8253
7.500 1.2006 0.02011 0.01429 -0.0930 0.5826 0.8282
7.750 1.2158 0.02005 0.01431 -0.0909 0.5740 0.8318
8.000 1.2367 0.01992 0.01423 -0.0899 0.5657 0.8356
8.250 1.2558 0.01976 0.01411 -0.0885 0.5566 0.8395
8.500 1.2594 0.01985 0.01431 -0.0843 0.5469 0.8436
8.750 1.2815 0.01968 0.01415 -0.0834 0.5372 0.8478
9.000 1.2885 0.01995 0.01449 -0.0803 0.5255 0.8530
9.250 1.2947 0.02024 0.01486 -0.0770 0.5134 0.8573
9.500 1.3036 0.02050 0.01516 -0.0742 0.5006 0.8621
9.750 1.3141 0.02087 0.01556 -0.0719 0.4867 0.8675
10.000 1.3212 0.02135 0.01606 -0.0692 0.4716 0.8728
10.250 1.3254 0.02196 0.01669 -0.0661 0.4559 0.8791
10.500 1.3296 0.02278 0.01751 -0.0634 0.4386 0.8861
10.750 1.3300 0.02367 0.01841 -0.0600 0.4210 0.8931
11.250 1.3308 0.02593 0.02061 -0.0542 0.3832 0.9099
11.500 1.3290 0.02727 0.02192 -0.0514 0.3642 0.9207
11.750 1.3258 0.02873 0.02338 -0.0485 0.3450 0.9365
12.000 1.3237 0.03025 0.02491 -0.0464 0.3255 1.0000
12.250 1.3261 0.03232 0.02689 -0.0456 0.3054 1.0000
12.500 1.3276 0.03452 0.02899 -0.0447 0.2864 1.0000
12.750 1.3292 0.03679 0.03123 -0.0440 0.2674 1.0000
13.000 1.3304 0.03913 0.03351 -0.0433 0.2498 1.0000
13.250 1.3312 0.04155 0.03588 -0.0426 0.2331 1.0000
13.500 1.3318 0.04404 0.03832 -0.0420 0.2173 1.0000
13.750 1.3322 0.04660 0.04083 -0.0414 0.2025 1.0000
14.000 1.3327 0.04919 0.04339 -0.0409 0.1886 1.0000
14.250 1.3329 0.05188 0.04603 -0.0404 0.1755 1.0000
14.500 1.3322 0.05468 0.04880 -0.0400 0.1635 1.0000
14.750 1.3321 0.05752 0.05161 -0.0397 0.1520 1.0000
15.000 1.3335 0.06028 0.05439 -0.0395 0.1407 1.0000
15.250 1.3339 0.06319 0.05731 -0.0394 0.1306 1.0000
15.500 1.3324 0.06632 0.06038 -0.0393 0.1219 1.0000
15.750 1.3334 0.06929 0.06340 -0.0394 0.1128 1.0000
16.000 1.3337 0.07237 0.06651 -0.0396 0.1048 1.0000
16.250 1.3317 0.07576 0.06985 -0.0398 0.0977 1.0000
16.500 1.3334 0.07883 0.07304 -0.0402 0.0905 1.0000
16.750 1.3308 0.08233 0.07644 -0.0405 0.0845 1.0000
17.000 1.3324 0.08555 0.07982 -0.0411 0.0785 1.0000
17.250 1.3302 0.08908 0.08325 -0.0416 0.0732 1.0000
17.500 1.3313 0.09246 0.08681 -0.0424 0.0684 1.0000
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Polar data table (+)
Polar graphs
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