EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 100,000 Max Cl/Cd: 30.74 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e655-il-100000-n5.txt Download as CSV file: xf-e655-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 655 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2334 0.09821 0.09293 -0.0988 0.8934 0.0252
-12.500 -0.2658 0.08484 0.07952 -0.1062 0.8862 0.0251
-12.250 -0.2998 0.07228 0.06681 -0.1153 0.8781 0.0244
-12.000 -0.3330 0.06274 0.05701 -0.1229 0.8684 0.0238
-11.750 -0.3601 0.05615 0.05010 -0.1275 0.8596 0.0237
-11.500 -0.3791 0.05180 0.04549 -0.1292 0.8506 0.0236
-11.250 -0.3947 0.04807 0.04145 -0.1299 0.8436 0.0238
-11.000 -0.4072 0.04504 0.03814 -0.1293 0.8365 0.0240
-10.750 -0.4166 0.04235 0.03511 -0.1281 0.8302 0.0246
-10.500 -0.4219 0.03993 0.03230 -0.1265 0.8251 0.0251
-10.250 -0.4209 0.03859 0.03085 -0.1247 0.8192 0.0260
-10.000 -0.4156 0.03752 0.02967 -0.1230 0.8142 0.0270
-9.750 -0.4070 0.03611 0.02803 -0.1217 0.8103 0.0282
-9.500 -0.3976 0.03446 0.02606 -0.1202 0.8060 0.0295
-9.250 -0.3846 0.03302 0.02446 -0.1189 0.8019 0.0308
-9.000 -0.3695 0.03194 0.02328 -0.1179 0.7984 0.0321
-8.750 -0.3529 0.03088 0.02201 -0.1169 0.7953 0.0345
-8.500 -0.3353 0.02985 0.02086 -0.1161 0.7926 0.0370
-8.250 -0.3198 0.02908 0.02002 -0.1149 0.7888 0.0398
-8.000 -0.3029 0.02820 0.01904 -0.1137 0.7850 0.0430
-7.750 -0.2857 0.02752 0.01831 -0.1126 0.7817 0.0470
-7.500 -0.2673 0.02673 0.01744 -0.1116 0.7789 0.0514
-7.250 -0.2476 0.02608 0.01669 -0.1108 0.7767 0.0572
-7.000 -0.2301 0.02546 0.01607 -0.1097 0.7740 0.0630
-6.750 -0.2141 0.02495 0.01554 -0.1083 0.7705 0.0704
-6.500 -0.1960 0.02448 0.01503 -0.1071 0.7672 0.0796
-6.250 -0.1773 0.02395 0.01451 -0.1061 0.7642 0.0910
-6.000 -0.1571 0.02344 0.01401 -0.1053 0.7617 0.1058
-5.750 -0.1364 0.02291 0.01355 -0.1046 0.7598 0.1250
-5.500 -0.1164 0.02253 0.01323 -0.1038 0.7575 0.1496
-5.250 -0.1006 0.02228 0.01313 -0.1024 0.7539 0.1771
-5.000 -0.0825 0.02197 0.01296 -0.1013 0.7506 0.2126
-4.750 -0.0628 0.02160 0.01274 -0.1004 0.7477 0.2562
-4.500 -0.0419 0.02119 0.01253 -0.0997 0.7454 0.3100
-4.250 -0.0203 0.02078 0.01235 -0.0991 0.7436 0.3733
-4.000 0.0022 0.02040 0.01225 -0.0983 0.7419 0.4467
-3.750 0.0149 0.02056 0.01274 -0.0958 0.7378 0.5126
-3.500 0.0315 0.02087 0.01329 -0.0934 0.7342 0.5730
-3.250 0.0523 0.02122 0.01367 -0.0918 0.7315 0.6197
-3.000 0.0757 0.02153 0.01390 -0.0907 0.7293 0.6531
-2.750 0.1007 0.02182 0.01410 -0.0897 0.7273 0.6776
-2.500 0.1274 0.02206 0.01420 -0.0892 0.7256 0.6990
-2.250 0.1399 0.02269 0.01482 -0.0866 0.7213 0.7147
-2.000 0.1543 0.02325 0.01535 -0.0843 0.7173 0.7289
-1.750 0.1746 0.02360 0.01563 -0.0828 0.7143 0.7426
-1.500 0.1987 0.02382 0.01575 -0.0819 0.7119 0.7562
-1.250 0.2232 0.02402 0.01587 -0.0808 0.7101 0.7670
-1.000 0.2492 0.02417 0.01594 -0.0801 0.7086 0.7775
-0.750 0.2463 0.02514 0.01694 -0.0759 0.7013 0.7892
-0.500 0.2622 0.02549 0.01728 -0.0735 0.6978 0.7978
-0.250 0.2858 0.02564 0.01735 -0.0728 0.6954 0.8079
0.000 0.3112 0.02569 0.01733 -0.0720 0.6935 0.8161
0.250 0.3402 0.02567 0.01723 -0.0720 0.6920 0.8245
0.750 0.3465 0.02706 0.01867 -0.0651 0.6795 0.8413
1.000 0.3735 0.02701 0.01857 -0.0647 0.6776 0.8474
1.250 0.4055 0.02692 0.01840 -0.0655 0.6761 0.8538
1.750 0.4101 0.02831 0.01984 -0.0587 0.6626 0.8680
2.000 0.4420 0.02815 0.01964 -0.0593 0.6608 0.8728
2.250 0.4754 0.02793 0.01938 -0.0601 0.6594 0.8771
2.750 0.4817 0.02939 0.02089 -0.0539 0.6451 0.8917
3.000 0.5160 0.02907 0.02054 -0.0548 0.6437 0.8962
3.500 0.5306 0.03069 0.02222 -0.0505 0.6292 0.9114
3.750 0.5276 0.03223 0.02381 -0.0479 0.6185 0.9205
4.000 0.5548 0.03215 0.02374 -0.0479 0.6151 0.9271
4.250 0.5879 0.03176 0.02336 -0.0485 0.6132 0.9331
4.500 0.6237 0.03123 0.02285 -0.0494 0.6118 0.9386
5.000 0.6605 0.03254 0.02427 -0.0492 0.5973 0.9595
5.250 0.7019 0.03189 0.02366 -0.0511 0.5960 0.9682
5.750 0.7430 0.03301 0.02487 -0.0518 0.5812 1.0000
6.250 0.7828 0.03411 0.02604 -0.0520 0.5666 1.0000
6.750 0.8244 0.03502 0.02704 -0.0520 0.5520 1.0000
7.000 0.8622 0.03413 0.02619 -0.0530 0.5500 1.0000
8.000 0.9491 0.03529 0.02756 -0.0525 0.5190 1.0000
8.500 0.9732 0.03740 0.02979 -0.0511 0.4958 1.0000
8.750 1.0073 0.03656 0.02900 -0.0514 0.4900 1.0000
9.000 1.0215 0.03745 0.02996 -0.0507 0.4780 1.0000
9.250 1.0492 0.03715 0.02970 -0.0507 0.4691 1.0000
9.500 1.0764 0.03689 0.02947 -0.0505 0.4589 1.0000
9.750 1.0942 0.03745 0.03009 -0.0500 0.4461 1.0000
10.000 1.1163 0.03763 0.03029 -0.0496 0.4334 1.0000
10.250 1.1396 0.03770 0.03036 -0.0492 0.4203 1.0000
10.500 1.1614 0.03792 0.03057 -0.0487 0.4063 1.0000
10.750 1.1801 0.03839 0.03103 -0.0481 0.3913 1.0000
11.000 1.1959 0.03911 0.03173 -0.0473 0.3758 1.0000
11.250 1.2096 0.04004 0.03264 -0.0465 0.3602 1.0000
11.500 1.2214 0.04114 0.03372 -0.0456 0.3447 1.0000
11.750 1.2315 0.04241 0.03498 -0.0447 0.3293 1.0000
12.000 1.2407 0.04379 0.03634 -0.0438 0.3144 1.0000
12.500 1.2549 0.04706 0.03960 -0.0421 0.2850 1.0000
12.750 1.2609 0.04887 0.04142 -0.0413 0.2710 1.0000
13.000 1.2664 0.05078 0.04336 -0.0406 0.2574 1.0000
13.250 1.2718 0.05275 0.04534 -0.0400 0.2444 1.0000
13.500 1.2765 0.05482 0.04742 -0.0394 0.2319 1.0000
13.750 1.2808 0.05698 0.04957 -0.0389 0.2199 1.0000
14.000 1.2839 0.05932 0.05192 -0.0384 0.2081 1.0000
14.250 1.2872 0.06175 0.05441 -0.0381 0.1966 1.0000
14.500 1.2901 0.06425 0.05696 -0.0378 0.1861 1.0000
14.750 1.2920 0.06687 0.05958 -0.0376 0.1761 1.0000
15.000 1.2938 0.06963 0.06241 -0.0376 0.1661 1.0000
15.250 1.2954 0.07247 0.06531 -0.0376 0.1568 1.0000
15.500 1.2955 0.07549 0.06831 -0.0377 0.1485 1.0000
15.750 1.2968 0.07854 0.07148 -0.0380 0.1397 1.0000
16.000 1.2967 0.08174 0.07472 -0.0383 0.1321 1.0000
16.250 1.2962 0.08507 0.07814 -0.0388 0.1245 1.0000
16.500 1.2959 0.08844 0.08157 -0.0393 0.1177 1.0000
16.750 1.2945 0.09202 0.08524 -0.0400 0.1112 1.0000
17.000 1.2938 0.09555 0.08883 -0.0408 0.1051 1.0000
17.250 1.2921 0.09929 0.09267 -0.0418 0.0994 1.0000
17.500 1.2903 0.10304 0.09644 -0.0428 0.0943 1.0000
17.750 1.2888 0.10689 0.10045 -0.0440 0.0889 1.0000
18.000 1.2859 0.11084 0.10440 -0.0453 0.0846 1.0000
18.500 1.2821 0.11884 0.11266 -0.0483 0.0758 1.0000
18.750 1.2803 0.12273 0.11655 -0.0499 0.0723 1.0000
19.000 1.2781 0.12691 0.12091 -0.0517 0.0684 1.0000
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