EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 656 AIRFOIL (e656-il) Reynolds number: 100,000 Max Cl/Cd: 29.8 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e656-il-100000-n5.txt Download as CSV file: xf-e656-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0931 0.10368 0.09786 -0.1082 0.8380 0.0220
-11.500 -0.0899 0.09975 0.09390 -0.1102 0.8339 0.0219
-11.250 -0.0880 0.09589 0.09006 -0.1119 0.8293 0.0219
-11.000 -0.0899 0.09117 0.08537 -0.1142 0.8250 0.0220
-10.750 -0.0847 0.08817 0.08235 -0.1156 0.8211 0.0216
-10.500 -0.0890 0.08291 0.07710 -0.1184 0.8179 0.0217
-10.250 -0.0938 0.07792 0.07214 -0.1210 0.8144 0.0216
-10.000 -0.0989 0.07301 0.06728 -0.1236 0.8106 0.0213
-9.500 -0.1922 0.05127 0.04511 -0.1368 0.8017 0.0186
-9.250 -0.2108 0.04832 0.04197 -0.1358 0.7978 0.0186
-9.000 -0.2051 0.04809 0.04182 -0.1345 0.7937 0.0195
-8.750 -0.2356 0.04370 0.03689 -0.1314 0.7890 0.0188
-8.500 -0.2310 0.04215 0.03519 -0.1301 0.7857 0.0191
-8.250 -0.2234 0.04079 0.03365 -0.1289 0.7831 0.0202
-8.000 -0.2194 0.03841 0.03084 -0.1273 0.7807 0.0209
-7.750 -0.2142 0.03617 0.02818 -0.1254 0.7774 0.0215
-7.500 -0.2036 0.03422 0.02584 -0.1238 0.7743 0.0221
-7.250 -0.1875 0.03295 0.02443 -0.1228 0.7713 0.0229
-7.000 -0.1695 0.03153 0.02277 -0.1218 0.7686 0.0236
-6.750 -0.1495 0.03007 0.02101 -0.1209 0.7662 0.0246
-6.500 -0.1278 0.02870 0.01937 -0.1200 0.7643 0.0258
-6.250 -0.1061 0.02787 0.01846 -0.1195 0.7625 0.0274
-6.000 -0.0890 0.02726 0.01776 -0.1182 0.7595 0.0302
-5.750 -0.0708 0.02673 0.01718 -0.1170 0.7565 0.0331
-5.500 -0.0517 0.02607 0.01647 -0.1159 0.7535 0.0363
-5.250 -0.0311 0.02545 0.01580 -0.1150 0.7509 0.0411
-5.000 -0.0092 0.02485 0.01514 -0.1143 0.7488 0.0492
-4.750 0.0134 0.02425 0.01455 -0.1138 0.7470 0.0605
-4.500 0.0368 0.02369 0.01402 -0.1134 0.7454 0.0779
-4.250 0.0547 0.02340 0.01385 -0.1122 0.7427 0.1005
-4.000 0.0697 0.02323 0.01384 -0.1106 0.7388 0.1307
-3.750 0.0884 0.02298 0.01383 -0.1097 0.7357 0.1773
-3.500 0.1104 0.02281 0.01369 -0.1090 0.7333 0.2297
-3.250 0.1317 0.02236 0.01356 -0.1085 0.7312 0.2883
-3.000 0.1543 0.02188 0.01345 -0.1080 0.7294 0.3929
-2.750 0.1762 0.02142 0.01347 -0.1068 0.7277 0.5185
-2.500 0.1868 0.02169 0.01411 -0.1035 0.7242 0.6129
-2.250 0.1929 0.02237 0.01499 -0.0993 0.7198 0.6750
-2.000 0.2075 0.02286 0.01549 -0.0965 0.7165 0.7240
-1.750 0.2274 0.02320 0.01574 -0.0946 0.7140 0.7610
-1.500 0.2482 0.02349 0.01593 -0.0926 0.7119 0.7906
-1.250 0.2710 0.02371 0.01603 -0.0912 0.7103 0.8152
-1.000 0.2744 0.02452 0.01682 -0.0872 0.7055 0.8321
-0.750 0.2756 0.02530 0.01760 -0.0829 0.6996 0.8469
-0.500 0.2939 0.02554 0.01775 -0.0811 0.6968 0.8594
-0.250 0.3166 0.02565 0.01775 -0.0800 0.6947 0.8714
0.000 0.3425 0.02566 0.01764 -0.0794 0.6930 0.8835
0.250 0.3691 0.02562 0.01749 -0.0787 0.6917 0.8956
0.750 0.3618 0.02731 0.01923 -0.0695 0.6779 0.9286
1.000 0.3948 0.02726 0.01910 -0.0702 0.6763 0.9417
1.250 0.4349 0.02721 0.01895 -0.0723 0.6751 0.9518
1.500 0.4778 0.02710 0.01875 -0.0751 0.6741 0.9601
2.000 0.5144 0.02915 0.02082 -0.0758 0.6603 0.9848
2.250 0.5565 0.02903 0.02064 -0.0785 0.6589 0.9925
2.500 0.5947 0.02888 0.02042 -0.0805 0.6577 1.0000
3.000 0.5808 0.03089 0.02241 -0.0722 0.6419 1.0000
3.250 0.6035 0.03119 0.02267 -0.0720 0.6383 1.0000
3.750 0.6327 0.03273 0.02419 -0.0704 0.6254 1.0000
4.000 0.6558 0.03309 0.02454 -0.0703 0.6213 1.0000
5.500 0.7913 0.03505 0.02653 -0.0694 0.5914 1.0000
6.500 0.8551 0.03781 0.02943 -0.0664 0.5616 1.0000
6.750 0.8895 0.03709 0.02876 -0.0669 0.5598 1.0000
7.250 0.9232 0.03821 0.02998 -0.0655 0.5447 1.0000
8.250 0.9985 0.03974 0.03176 -0.0630 0.5140 1.0000
8.750 1.0404 0.04012 0.03228 -0.0620 0.4980 1.0000
9.000 1.0515 0.04119 0.03343 -0.0610 0.4863 1.0000
9.250 1.0861 0.04014 0.03244 -0.0611 0.4811 1.0000
9.500 1.0979 0.04116 0.03354 -0.0601 0.4687 1.0000
9.750 1.1244 0.04085 0.03329 -0.0598 0.4598 1.0000
10.250 1.1673 0.04115 0.03369 -0.0587 0.4364 1.0000
10.500 1.1892 0.04126 0.03384 -0.0582 0.4239 1.0000
10.750 1.2129 0.04121 0.03381 -0.0577 0.4108 1.0000
11.000 1.2338 0.04141 0.03400 -0.0571 0.3965 1.0000
11.250 1.2509 0.04197 0.03456 -0.0563 0.3811 1.0000
11.500 1.2645 0.04286 0.03545 -0.0554 0.3652 1.0000
11.750 1.2752 0.04405 0.03664 -0.0544 0.3493 1.0000
12.000 1.2846 0.04538 0.03797 -0.0534 0.3335 1.0000
12.250 1.2927 0.04687 0.03947 -0.0525 0.3177 1.0000
12.500 1.3000 0.04850 0.04111 -0.0515 0.3024 1.0000
12.750 1.3066 0.05022 0.04284 -0.0507 0.2875 1.0000
13.000 1.3123 0.05207 0.04470 -0.0498 0.2730 1.0000
13.250 1.3178 0.05401 0.04665 -0.0491 0.2590 1.0000
13.500 1.3226 0.05605 0.04872 -0.0484 0.2455 1.0000
13.750 1.3264 0.05823 0.05089 -0.0477 0.2324 1.0000
14.000 1.3296 0.06053 0.05319 -0.0471 0.2196 1.0000
14.250 1.3320 0.06304 0.05576 -0.0467 0.2072 1.0000
14.500 1.3344 0.06559 0.05836 -0.0463 0.1954 1.0000
14.750 1.3362 0.06825 0.06106 -0.0460 0.1842 1.0000
15.000 1.3368 0.07106 0.06385 -0.0458 0.1737 1.0000
15.250 1.3378 0.07399 0.06689 -0.0458 0.1631 1.0000
15.500 1.3384 0.07701 0.06996 -0.0458 0.1534 1.0000
15.750 1.3376 0.08020 0.07316 -0.0459 0.1446 1.0000
16.000 1.3377 0.08345 0.07652 -0.0462 0.1355 1.0000
16.250 1.3371 0.08679 0.07993 -0.0466 0.1275 1.0000
16.500 1.3351 0.09036 0.08355 -0.0471 0.1200 1.0000
16.750 1.3344 0.09387 0.08717 -0.0477 0.1125 1.0000
17.000 1.3312 0.09770 0.09099 -0.0485 0.1063 1.0000
17.250 1.3303 0.10137 0.09483 -0.0494 0.0994 1.0000
17.500 1.3270 0.10534 0.09882 -0.0504 0.0940 1.0000
17.750 1.3252 0.10924 0.10288 -0.0516 0.0880 1.0000
18.000 1.3219 0.11330 0.10696 -0.0529 0.0833 1.0000
18.250 1.3199 0.11730 0.11111 -0.0543 0.0781 1.0000
18.500 1.3165 0.12145 0.11526 -0.0559 0.0741 1.0000
18.750 1.3145 0.12553 0.11952 -0.0575 0.0695 1.0000
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Polar data table (+)
Polar graphs
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