EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 656 AIRFOIL (e656-il) Reynolds number: 200,000 Max Cl/Cd: 69.12 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e656-il-200000.txt Download as CSV file: xf-e656-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 656 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0333 0.10057 0.09622 -0.1175 0.8370 0.0483
-11.000 -0.0551 0.09538 0.09108 -0.1230 0.8332 0.0505
-10.750 -0.0490 0.09200 0.08773 -0.1237 0.8295 0.0509
-10.500 -0.0318 0.09018 0.08589 -0.1226 0.8261 0.0519
-10.250 -0.0238 0.08773 0.08342 -0.1231 0.8228 0.0531
-10.000 -0.0209 0.08472 0.08040 -0.1244 0.8199 0.0545
-9.750 -0.0596 0.07680 0.07257 -0.1333 0.8164 0.0574
-9.500 -0.0502 0.07416 0.06996 -0.1324 0.8137 0.0581
-9.250 -0.0361 0.07275 0.06856 -0.1311 0.8110 0.0591
-9.000 -0.0317 0.07019 0.06602 -0.1316 0.8081 0.0606
-8.750 -0.0382 0.06612 0.06197 -0.1342 0.8049 0.0615
-8.500 -0.0580 0.06082 0.05666 -0.1384 0.8015 0.0624
-8.250 -0.0934 0.05717 0.05291 -0.1385 0.7980 0.0638
-7.750 -0.1840 0.03812 0.03248 -0.1322 0.7908 0.0290
-7.500 -0.1880 0.03339 0.02692 -0.1289 0.7881 0.0253
-7.250 -0.1731 0.03118 0.02444 -0.1277 0.7859 0.0250
-7.000 -0.1558 0.02918 0.02211 -0.1266 0.7837 0.0247
-6.750 -0.1359 0.02741 0.01996 -0.1256 0.7817 0.0247
-6.500 -0.1157 0.02603 0.01828 -0.1245 0.7795 0.0251
-6.250 -0.0952 0.02489 0.01695 -0.1235 0.7770 0.0259
-6.000 -0.0737 0.02406 0.01615 -0.1229 0.7746 0.0271
-5.750 -0.0513 0.02345 0.01542 -0.1222 0.7722 0.0291
-5.500 -0.0286 0.02290 0.01487 -0.1217 0.7698 0.0328
-5.250 -0.0057 0.02216 0.01412 -0.1210 0.7676 0.0359
-5.000 0.0173 0.02142 0.01338 -0.1203 0.7657 0.0407
-4.750 0.0409 0.02092 0.01286 -0.1198 0.7641 0.0509
-4.500 0.0621 0.02037 0.01243 -0.1191 0.7624 0.0674
-4.250 0.0779 0.02019 0.01243 -0.1177 0.7592 0.0912
-4.000 0.0959 0.01987 0.01234 -0.1167 0.7558 0.1292
-3.750 0.1169 0.01956 0.01237 -0.1162 0.7531 0.2040
-3.500 0.1393 0.01916 0.01222 -0.1160 0.7510 0.2659
-3.250 0.1632 0.01868 0.01215 -0.1160 0.7491 0.3719
-3.000 0.1870 0.01813 0.01213 -0.1156 0.7474 0.5125
-2.750 0.2095 0.01793 0.01238 -0.1142 0.7457 0.6397
-2.500 0.2229 0.01857 0.01322 -0.1114 0.7426 0.7058
-2.250 0.2301 0.01956 0.01430 -0.1081 0.7377 0.7437
-2.000 0.2474 0.02012 0.01484 -0.1058 0.7344 0.7737
-1.750 0.2697 0.02049 0.01513 -0.1043 0.7321 0.7979
-1.500 0.2910 0.02083 0.01540 -0.1023 0.7303 0.8171
-1.250 0.3137 0.02105 0.01556 -0.1004 0.7289 0.8347
-1.000 0.3374 0.02126 0.01567 -0.0988 0.7274 0.8502
-0.750 0.3054 0.02333 0.01792 -0.0902 0.7167 0.8629
-0.500 0.3217 0.02347 0.01801 -0.0874 0.7141 0.8769
-0.250 0.3424 0.02343 0.01790 -0.0851 0.7124 0.8908
0.000 0.3678 0.02328 0.01766 -0.0839 0.7111 0.9030
0.250 0.3979 0.02310 0.01739 -0.0837 0.7100 0.9123
0.500 0.3414 0.02553 0.01999 -0.0718 0.6959 0.9307
0.750 0.3747 0.02521 0.01959 -0.0721 0.6947 0.9390
1.000 0.4105 0.02490 0.01919 -0.0730 0.6937 0.9470
1.250 0.4483 0.02457 0.01879 -0.0742 0.6929 0.9568
1.500 0.4996 0.02427 0.01842 -0.0780 0.6924 0.9647
1.750 0.5523 0.02399 0.01806 -0.0822 0.6917 0.9714
2.000 0.5508 0.02657 0.02076 -0.0815 0.6781 0.9850
2.250 0.6097 0.02614 0.02026 -0.0869 0.6776 0.9875
2.500 0.6647 0.02565 0.01973 -0.0916 0.6770 0.9904
2.750 0.7168 0.02512 0.01915 -0.0957 0.6763 0.9930
3.000 0.7693 0.02456 0.01854 -0.1000 0.6755 0.9951
3.250 0.8185 0.02405 0.01799 -0.1038 0.6745 0.9971
3.500 0.6780 0.02797 0.02205 -0.0791 0.6527 1.0000
3.750 0.7334 0.02689 0.02093 -0.0828 0.6538 1.0000
4.000 0.7924 0.02580 0.01982 -0.0872 0.6549 1.0000
4.250 0.8547 0.02461 0.01858 -0.0922 0.6561 1.0000
4.500 0.7566 0.02969 0.02377 -0.0775 0.6299 1.0000
4.750 0.7994 0.02875 0.02283 -0.0791 0.6292 1.0000
5.000 0.8447 0.02772 0.02179 -0.0811 0.6288 1.0000
5.250 0.8924 0.02664 0.02073 -0.0835 0.6283 1.0000
5.500 0.9410 0.02561 0.01971 -0.0863 0.6276 1.0000
5.750 0.9907 0.02461 0.01874 -0.0893 0.6266 1.0000
6.000 1.0411 0.02359 0.01773 -0.0925 0.6255 1.0000
6.250 1.0915 0.02255 0.01670 -0.0958 0.6243 1.0000
6.500 1.0778 0.02381 0.01805 -0.0903 0.6127 1.0000
6.750 1.1297 0.02264 0.01691 -0.0937 0.6108 1.0000
7.000 1.1823 0.02144 0.01572 -0.0972 0.6087 1.0000
7.250 1.1795 0.02211 0.01648 -0.0929 0.5988 1.0000
7.500 1.2250 0.02112 0.01553 -0.0954 0.5948 1.0000
7.750 1.2786 0.01994 0.01436 -0.0992 0.5914 1.0000
8.000 1.2694 0.02062 0.01514 -0.0937 0.5804 1.0000
8.250 1.3219 0.01945 0.01398 -0.0972 0.5753 1.0000
8.500 1.3142 0.02011 0.01473 -0.0920 0.5636 1.0000
8.750 1.3284 0.02021 0.01488 -0.0900 0.5532 1.0000
9.000 1.3602 0.01968 0.01434 -0.0905 0.5430 1.0000
9.250 1.3694 0.02004 0.01473 -0.0880 0.5292 1.0000
9.500 1.3801 0.02046 0.01516 -0.0858 0.5140 1.0000
9.750 1.3930 0.02089 0.01557 -0.0840 0.4976 1.0000
10.000 1.4048 0.02145 0.01607 -0.0821 0.4796 1.0000
10.250 1.4092 0.02245 0.01704 -0.0796 0.4605 1.0000
10.500 1.4143 0.02353 0.01806 -0.0773 0.4410 1.0000
10.750 1.4186 0.02472 0.01918 -0.0750 0.4213 1.0000
11.000 1.4220 0.02605 0.02043 -0.0727 0.4021 1.0000
11.250 1.4242 0.02750 0.02180 -0.0705 0.3833 1.0000
11.500 1.4255 0.02908 0.02330 -0.0683 0.3649 1.0000
11.750 1.4253 0.03083 0.02501 -0.0662 0.3470 1.0000
12.000 1.4253 0.03266 0.02679 -0.0642 0.3295 1.0000
12.250 1.4251 0.03456 0.02864 -0.0623 0.3124 1.0000
12.500 1.4253 0.03652 0.03057 -0.0606 0.2957 1.0000
12.750 1.4254 0.03857 0.03258 -0.0590 0.2798 1.0000
13.000 1.4253 0.04071 0.03468 -0.0576 0.2641 1.0000
13.250 1.4257 0.04289 0.03682 -0.0563 0.2492 1.0000
13.500 1.4256 0.04520 0.03908 -0.0551 0.2348 1.0000
13.750 1.4263 0.04753 0.04142 -0.0541 0.2206 1.0000
14.000 1.4271 0.04992 0.04382 -0.0531 0.2069 1.0000
14.250 1.4280 0.05238 0.04628 -0.0523 0.1939 1.0000
14.500 1.4286 0.05493 0.04883 -0.0516 0.1815 1.0000
14.750 1.4285 0.05762 0.05150 -0.0510 0.1701 1.0000
15.000 1.4273 0.06047 0.05429 -0.0504 0.1591 1.0000
15.250 1.4281 0.06325 0.05714 -0.0501 0.1481 1.0000
15.500 1.4289 0.06607 0.06000 -0.0498 0.1380 1.0000
15.750 1.4276 0.06916 0.06308 -0.0496 0.1289 1.0000
16.000 1.4264 0.07233 0.06626 -0.0495 0.1202 1.0000
16.250 1.4269 0.07540 0.06940 -0.0495 0.1116 1.0000
16.500 1.4247 0.07880 0.07279 -0.0496 0.1042 1.0000
16.750 1.4234 0.08221 0.07625 -0.0499 0.0969 1.0000
17.000 1.4224 0.08562 0.07972 -0.0502 0.0901 1.0000
17.250 1.4190 0.08932 0.08337 -0.0507 0.0842 1.0000
17.500 1.4184 0.09287 0.08707 -0.0513 0.0781 1.0000
17.750 1.4156 0.09662 0.09080 -0.0519 0.0731 1.0000
18.000 1.4140 0.10037 0.09466 -0.0528 0.0681 1.0000
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Polar data table (+)
Polar graphs
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