EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 656 AIRFOIL (e656-il) Reynolds number: 200,000 Max Cl/Cd: 70.63 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e656-il-200000-n5.txt Download as CSV file: xf-e656-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1918 0.05927 0.05435 -0.1261 0.7624 0.0102
-10.500 -0.2235 0.05005 0.04498 -0.1335 0.7593 0.0101
-10.250 -0.2439 0.04544 0.04021 -0.1359 0.7560 0.0100
-10.000 -0.2617 0.04201 0.03660 -0.1360 0.7528 0.0099
-9.750 -0.2807 0.03894 0.03328 -0.1343 0.7497 0.0099
-9.500 -0.2966 0.03667 0.03074 -0.1312 0.7468 0.0099
-9.250 -0.3035 0.03414 0.02786 -0.1288 0.7444 0.0099
-9.000 -0.3041 0.03165 0.02499 -0.1266 0.7416 0.0100
-8.750 -0.2957 0.02981 0.02287 -0.1251 0.7391 0.0100
-8.500 -0.2840 0.02804 0.02078 -0.1237 0.7368 0.0101
-8.250 -0.2695 0.02637 0.01881 -0.1224 0.7346 0.0104
-8.000 -0.2518 0.02526 0.01756 -0.1216 0.7326 0.0106
-7.750 -0.2323 0.02425 0.01641 -0.1209 0.7307 0.0109
-7.500 -0.2118 0.02332 0.01531 -0.1202 0.7290 0.0112
-7.250 -0.1905 0.02241 0.01423 -0.1196 0.7273 0.0118
-7.000 -0.1692 0.02157 0.01325 -0.1189 0.7252 0.0123
-6.750 -0.1478 0.02078 0.01233 -0.1182 0.7229 0.0129
-6.500 -0.1258 0.02015 0.01167 -0.1177 0.7209 0.0136
-6.250 -0.1024 0.01967 0.01112 -0.1173 0.7189 0.0151
-6.000 -0.0789 0.01918 0.01058 -0.1169 0.7171 0.0168
-5.750 -0.0550 0.01870 0.01000 -0.1165 0.7153 0.0187
-5.500 -0.0310 0.01819 0.00945 -0.1162 0.7136 0.0209
-5.250 -0.0064 0.01772 0.00892 -0.1159 0.7119 0.0239
-5.000 0.0187 0.01730 0.00845 -0.1157 0.7103 0.0304
-4.750 0.0440 0.01689 0.00804 -0.1156 0.7088 0.0399
-4.500 0.0681 0.01654 0.00777 -0.1153 0.7069 0.0533
-4.250 0.0926 0.01622 0.00753 -0.1150 0.7050 0.0730
-4.000 0.1171 0.01588 0.00733 -0.1149 0.7031 0.1012
-3.750 0.1419 0.01554 0.00714 -0.1148 0.7010 0.1391
-3.500 0.1674 0.01525 0.00704 -0.1148 0.6990 0.1928
-3.250 0.1943 0.01512 0.00687 -0.1148 0.6972 0.2257
-3.000 0.2204 0.01481 0.00668 -0.1149 0.6956 0.2556
-2.500 0.2720 0.01399 0.00647 -0.1152 0.6928 0.4350
-2.250 0.2978 0.01366 0.00647 -0.1151 0.6914 0.5370
-2.000 0.3201 0.01356 0.00669 -0.1141 0.6891 0.6189
-1.750 0.3421 0.01364 0.00699 -0.1127 0.6869 0.6820
-1.500 0.3657 0.01382 0.00723 -0.1116 0.6849 0.7214
-1.250 0.3906 0.01399 0.00739 -0.1109 0.6827 0.7466
-1.000 0.4162 0.01415 0.00751 -0.1104 0.6807 0.7665
-0.750 0.4427 0.01429 0.00759 -0.1100 0.6788 0.7827
-0.500 0.4701 0.01441 0.00763 -0.1100 0.6773 0.7943
-0.250 0.4976 0.01450 0.00766 -0.1099 0.6757 0.8017
0.000 0.5260 0.01459 0.00767 -0.1100 0.6743 0.8094
0.250 0.5499 0.01479 0.00787 -0.1095 0.6717 0.8170
0.500 0.5721 0.01499 0.00809 -0.1086 0.6688 0.8242
0.750 0.5968 0.01515 0.00824 -0.1081 0.6661 0.8336
1.000 0.6195 0.01527 0.00837 -0.1070 0.6637 0.8422
1.250 0.6454 0.01535 0.00843 -0.1067 0.6614 0.8514
1.500 0.6704 0.01539 0.00844 -0.1060 0.6594 0.8585
1.750 0.6994 0.01543 0.00843 -0.1063 0.6577 0.8662
2.000 0.7202 0.01557 0.00860 -0.1050 0.6549 0.8721
2.250 0.7396 0.01577 0.00886 -0.1036 0.6510 0.8787
2.500 0.7634 0.01588 0.00899 -0.1031 0.6478 0.8845
2.750 0.7873 0.01589 0.00900 -0.1024 0.6450 0.8893
3.000 0.8150 0.01586 0.00895 -0.1024 0.6426 0.8940
3.250 0.8456 0.01581 0.00887 -0.1031 0.6405 0.8986
3.500 0.8622 0.01600 0.00915 -0.1013 0.6361 0.9035
3.750 0.8816 0.01612 0.00933 -0.0999 0.6317 0.9089
4.000 0.9073 0.01612 0.00934 -0.0998 0.6282 0.9138
4.250 0.9337 0.01599 0.00921 -0.0994 0.6253 0.9187
4.500 0.9573 0.01596 0.00922 -0.0987 0.6219 0.9252
4.750 0.9694 0.01617 0.00954 -0.0961 0.6159 0.9332
5.000 0.9919 0.01612 0.00952 -0.0952 0.6116 0.9406
5.250 1.0203 0.01594 0.00936 -0.0954 0.6081 0.9469
5.500 1.0357 0.01614 0.00966 -0.0935 0.6022 0.9562
5.750 1.0590 0.01620 0.00980 -0.0931 0.5964 0.9646
6.000 1.0916 0.01606 0.00967 -0.0942 0.5920 0.9711
6.250 1.1122 0.01632 0.01005 -0.0938 0.5842 1.0000
6.500 1.1358 0.01633 0.01008 -0.0934 0.5777 1.0000
6.750 1.1521 0.01657 0.01039 -0.0920 0.5697 1.0000
7.000 1.1738 0.01665 0.01050 -0.0913 0.5615 1.0000
7.250 1.1879 0.01702 0.01093 -0.0896 0.5517 1.0000
7.500 1.2099 0.01713 0.01104 -0.0891 0.5422 1.0000
7.750 1.2250 0.01751 0.01145 -0.0876 0.5304 1.0000
8.000 1.2400 0.01794 0.01189 -0.0862 0.5176 1.0000
8.250 1.2557 0.01837 0.01231 -0.0848 0.5036 1.0000
8.500 1.2702 0.01889 0.01279 -0.0834 0.4879 1.0000
8.750 1.2829 0.01953 0.01338 -0.0818 0.4711 1.0000
9.000 1.2934 0.02032 0.01411 -0.0800 0.4532 1.0000
9.250 1.3018 0.02127 0.01498 -0.0780 0.4348 1.0000
9.500 1.3084 0.02237 0.01602 -0.0760 0.4166 1.0000
9.750 1.3135 0.02362 0.01720 -0.0739 0.3985 1.0000
10.000 1.3178 0.02498 0.01850 -0.0719 0.3805 1.0000
10.250 1.3219 0.02641 0.01988 -0.0699 0.3632 1.0000
10.500 1.3254 0.02793 0.02136 -0.0681 0.3460 1.0000
10.750 1.3288 0.02951 0.02289 -0.0663 0.3294 1.0000
11.000 1.3321 0.03114 0.02448 -0.0646 0.3134 1.0000
11.250 1.3355 0.03283 0.02613 -0.0630 0.2982 1.0000
11.500 1.3392 0.03455 0.02782 -0.0616 0.2833 1.0000
11.750 1.3435 0.03629 0.02955 -0.0602 0.2687 1.0000
12.000 1.3476 0.03810 0.03135 -0.0590 0.2541 1.0000
12.250 1.3521 0.03994 0.03317 -0.0579 0.2403 1.0000
12.500 1.3564 0.04185 0.03507 -0.0568 0.2270 1.0000
12.750 1.3602 0.04384 0.03705 -0.0558 0.2139 1.0000
13.000 1.3637 0.04593 0.03913 -0.0549 0.2014 1.0000
13.500 1.3714 0.05021 0.04340 -0.0534 0.1766 1.0000
13.750 1.3758 0.05237 0.04558 -0.0528 0.1655 1.0000
14.000 1.3792 0.05468 0.04789 -0.0522 0.1549 1.0000
14.250 1.3815 0.05717 0.05037 -0.0517 0.1450 1.0000
14.500 1.3861 0.05946 0.05271 -0.0513 0.1349 1.0000
14.750 1.3895 0.06193 0.05520 -0.0510 0.1259 1.0000
15.000 1.3913 0.06463 0.05791 -0.0507 0.1174 1.0000
15.250 1.3944 0.06725 0.06058 -0.0506 0.1088 1.0000
15.500 1.3972 0.06994 0.06332 -0.0505 0.1013 1.0000
15.750 1.3978 0.07296 0.06636 -0.0505 0.0943 1.0000
16.000 1.4005 0.07577 0.06924 -0.0506 0.0874 1.0000
16.250 1.4018 0.07881 0.07233 -0.0508 0.0815 1.0000
16.500 1.4021 0.08205 0.07562 -0.0511 0.0758 1.0000
16.750 1.4034 0.08518 0.07883 -0.0515 0.0706 1.0000
17.000 1.4019 0.08875 0.08245 -0.0520 0.0659 1.0000
17.250 1.4028 0.09204 0.08584 -0.0526 0.0613 1.0000
17.500 1.4004 0.09588 0.08972 -0.0534 0.0573 1.0000
17.750 1.4008 0.09934 0.09329 -0.0542 0.0532 1.0000
18.000 1.3976 0.10336 0.09738 -0.0552 0.0500 1.0000
18.250 1.3972 0.10702 0.10115 -0.0563 0.0464 1.0000
18.500 1.3932 0.11126 0.10545 -0.0576 0.0437 1.0000
18.750 1.3922 0.11509 0.10940 -0.0589 0.0408 1.0000
19.000 1.3879 0.11949 0.11388 -0.0605 0.0385 1.0000
19.250 1.3864 0.12345 0.11795 -0.0621 0.0360 1.0000
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Polar data table (+)
Polar graphs
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