EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 100,000 Max Cl/Cd: 28.59 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e856-il-100000.txt Download as CSV file: xf-e856-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 856 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2626 0.13196 0.12817 -0.0349 1.0000 0.1303
-11.000 -0.4619 0.08426 0.07971 -0.0706 1.0000 0.0580
-10.750 -0.4768 0.08051 0.07599 -0.0701 1.0000 0.0575
-10.500 -0.5030 0.07674 0.07227 -0.0696 1.0000 0.0572
-10.250 -0.5244 0.07410 0.06970 -0.0678 1.0000 0.0566
-10.000 -0.5579 0.07193 0.06760 -0.0655 1.0000 0.0562
-9.750 -0.5891 0.07043 0.06617 -0.0625 1.0000 0.0554
-9.500 -0.6087 0.06301 0.05837 -0.0725 0.9861 0.0537
-9.250 -0.6080 0.05667 0.05154 -0.0793 0.9733 0.0537
-9.000 -0.5970 0.05129 0.04561 -0.0838 0.9613 0.0545
-8.750 -0.5802 0.04666 0.04043 -0.0867 0.9498 0.0550
-8.500 -0.5597 0.04273 0.03593 -0.0886 0.9387 0.0560
-8.250 -0.5345 0.03956 0.03208 -0.0902 0.9283 0.0578
-8.000 -0.4954 0.03703 0.02962 -0.0935 0.9222 0.0627
-7.750 -0.4678 0.03487 0.02702 -0.0943 0.9111 0.0678
-7.500 -0.4248 0.03268 0.02482 -0.0976 0.9061 0.0762
-7.250 -0.3976 0.03100 0.02318 -0.0980 0.8949 0.0848
-7.000 -0.3536 0.02900 0.02113 -0.1012 0.8904 0.1002
-6.750 -0.3270 0.02764 0.01977 -0.1014 0.8790 0.1157
-6.500 -0.2841 0.02566 0.01801 -0.1045 0.8747 0.1413
-6.250 -0.2578 0.02429 0.01680 -0.1048 0.8637 0.1694
-6.000 -0.2158 0.02219 0.01514 -0.1083 0.8587 0.2315
-5.750 -0.1889 0.02123 0.01482 -0.1087 0.8477 0.3313
-5.500 -0.1391 0.02161 0.01516 -0.1118 0.8418 0.4096
-5.250 -0.1072 0.02222 0.01565 -0.1116 0.8303 0.4423
-5.000 -0.0573 0.02282 0.01619 -0.1140 0.8240 0.4689
-4.750 -0.0295 0.02331 0.01661 -0.1130 0.8118 0.4873
-4.500 0.0112 0.02362 0.01679 -0.1143 0.8036 0.5059
-4.250 0.0407 0.02391 0.01699 -0.1138 0.7925 0.5204
-4.000 0.0685 0.02408 0.01703 -0.1132 0.7817 0.5344
-3.750 0.1045 0.02411 0.01688 -0.1142 0.7731 0.5495
-3.500 0.1256 0.02440 0.01711 -0.1124 0.7619 0.5610
-3.250 0.1622 0.02446 0.01704 -0.1132 0.7548 0.5731
-3.000 0.1792 0.02446 0.01693 -0.1115 0.7435 0.5845
-2.750 0.2111 0.02448 0.01683 -0.1117 0.7361 0.5943
-2.500 0.2309 0.02441 0.01667 -0.1105 0.7261 0.6032
-2.250 0.2634 0.02431 0.01641 -0.1112 0.7195 0.6116
-2.000 0.2814 0.02426 0.01629 -0.1100 0.7101 0.6196
-1.750 0.3141 0.02415 0.01605 -0.1107 0.7041 0.6266
-1.500 0.3323 0.02414 0.01595 -0.1099 0.6952 0.6350
-1.250 0.3611 0.02407 0.01580 -0.1098 0.6888 0.6408
-1.000 0.3841 0.02413 0.01579 -0.1094 0.6819 0.6481
-0.750 0.4073 0.02416 0.01575 -0.1090 0.6750 0.6550
-0.500 0.4395 0.02410 0.01558 -0.1097 0.6700 0.6620
-0.250 0.4570 0.02432 0.01576 -0.1087 0.6626 0.6696
0.000 0.4817 0.02437 0.01580 -0.1081 0.6566 0.6757
0.250 0.5162 0.02433 0.01562 -0.1095 0.6523 0.6841
0.500 0.5276 0.02476 0.01613 -0.1072 0.6454 0.6903
0.750 0.5519 0.02491 0.01627 -0.1068 0.6399 0.6979
1.000 0.5857 0.02490 0.01614 -0.1080 0.6358 0.7065
1.250 0.5968 0.02543 0.01677 -0.1055 0.6294 0.7138
1.500 0.6196 0.02570 0.01702 -0.1052 0.6240 0.7226
1.750 0.6484 0.02579 0.01710 -0.1053 0.6201 0.7312
2.000 0.6696 0.02622 0.01754 -0.1047 0.6156 0.7409
2.250 0.6784 0.02690 0.01835 -0.1019 0.6094 0.7500
2.500 0.7051 0.02706 0.01850 -0.1019 0.6050 0.7604
2.750 0.7387 0.02712 0.01851 -0.1030 0.6017 0.7733
3.000 0.7360 0.02828 0.01987 -0.0986 0.5959 0.7843
3.250 0.7467 0.02901 0.02070 -0.0962 0.5908 0.7975
3.500 0.7759 0.02910 0.02080 -0.0965 0.5873 0.8135
3.750 0.8103 0.02902 0.02071 -0.0973 0.5844 0.8325
4.000 0.7765 0.03139 0.02339 -0.0889 0.5765 0.8536
4.250 0.7857 0.03209 0.02425 -0.0862 0.5723 0.8852
4.500 0.8387 0.03179 0.02404 -0.0905 0.5696 0.9479
4.750 0.9024 0.03156 0.02368 -0.0975 0.5671 1.0000
5.000 0.8096 0.03755 0.02987 -0.0840 0.5550 1.0000
5.250 0.8575 0.03739 0.02962 -0.0873 0.5529 1.0000
5.500 0.9153 0.03680 0.02895 -0.0917 0.5513 1.0000
5.750 0.7216 0.05188 0.04418 -0.0735 0.5321 1.0000
6.000 0.7921 0.04870 0.04095 -0.0757 0.5328 1.0000
6.250 0.8663 0.04580 0.03800 -0.0791 0.5332 1.0000
6.500 0.6251 0.06890 0.06125 -0.0687 0.5109 1.0000
6.750 0.6218 0.07218 0.06453 -0.0684 0.5065 1.0000
7.000 0.6533 0.07264 0.06498 -0.0686 0.5027 1.0000
7.250 0.7149 0.07064 0.06294 -0.0694 0.5001 1.0000
7.500 0.6399 0.07996 0.07234 -0.0680 0.4939 1.0000
7.750 0.6402 0.08304 0.07544 -0.0679 0.4901 1.0000
8.000 0.7101 0.08016 0.07254 -0.0682 0.4841 1.0000
8.250 0.6273 0.09268 0.08519 -0.0696 0.5025 1.0000
8.500 0.6438 0.09532 0.08786 -0.0702 0.5013 1.0000
8.750 0.7414 0.08654 0.07898 -0.0676 0.4673 1.0000
9.000 0.6714 0.10166 0.09427 -0.0715 0.4994 1.0000
9.250 0.6259 0.10586 0.09853 -0.0705 0.4946 1.0000
9.500 0.6723 0.10414 0.09679 -0.0695 0.4702 1.0000
9.750 0.6761 0.10763 0.10033 -0.0701 0.4696 1.0000
10.000 0.7959 0.09643 0.08907 -0.0665 0.4342 1.0000
10.250 0.7522 0.10333 0.09603 -0.0669 0.4236 1.0000
10.500 0.8081 0.10101 0.09375 -0.0662 0.4185 1.0000
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Polar data table (+)
Polar graphs
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