EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 200,000 Max Cl/Cd: 64.76 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e856-il-200000.txt Download as CSV file: xf-e856-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5332 0.07536 0.07140 -0.0772 1.0000 0.0264
-12.250 -0.5584 0.07013 0.06609 -0.0793 1.0000 0.0263
-12.000 -0.5680 0.06673 0.06270 -0.0791 1.0000 0.0260
-11.750 -0.5887 0.06295 0.05886 -0.0794 1.0000 0.0258
-11.500 -0.6158 0.05936 0.05520 -0.0790 1.0000 0.0257
-11.250 -0.6398 0.05680 0.05262 -0.0773 1.0000 0.0255
-11.000 -0.6613 0.05308 0.04870 -0.0797 0.9966 0.0256
-10.750 -0.6617 0.04824 0.04351 -0.0865 0.9865 0.0255
-10.500 -0.6555 0.04374 0.03852 -0.0911 0.9757 0.0258
-10.250 -0.6395 0.03988 0.03421 -0.0941 0.9659 0.0260
-10.000 -0.6187 0.03653 0.03038 -0.0964 0.9570 0.0263
-9.750 -0.5907 0.03363 0.02732 -0.0984 0.9507 0.0269
-9.500 -0.5636 0.03174 0.02536 -0.0996 0.9423 0.0278
-9.250 -0.5295 0.02986 0.02335 -0.1019 0.9370 0.0291
-9.000 -0.5026 0.02813 0.02135 -0.1026 0.9277 0.0308
-8.750 -0.4682 0.02631 0.01959 -0.1047 0.9229 0.0329
-8.500 -0.4390 0.02514 0.01826 -0.1057 0.9139 0.0362
-8.250 -0.4054 0.02353 0.01674 -0.1076 0.9082 0.0400
-8.000 -0.3749 0.02203 0.01521 -0.1089 0.8994 0.0446
-7.750 -0.3371 0.02065 0.01383 -0.1117 0.8923 0.0525
-7.500 -0.3001 0.01942 0.01260 -0.1143 0.8824 0.0628
-7.250 -0.2526 0.01828 0.01138 -0.1190 0.8747 0.0780
-7.000 -0.2170 0.01710 0.01029 -0.1216 0.8614 0.0948
-6.750 -0.1799 0.01618 0.00934 -0.1242 0.8474 0.1181
-6.500 -0.1478 0.01520 0.00846 -0.1260 0.8325 0.1503
-6.250 -0.1200 0.01423 0.00767 -0.1270 0.8173 0.2015
-6.000 -0.0948 0.01341 0.00717 -0.1274 0.8028 0.2914
-5.750 -0.0661 0.01329 0.00710 -0.1277 0.7891 0.3568
-5.500 -0.0400 0.01341 0.00712 -0.1272 0.7745 0.3893
-5.250 -0.0136 0.01360 0.00721 -0.1266 0.7609 0.4115
-5.000 0.0137 0.01383 0.00729 -0.1263 0.7482 0.4296
-4.750 0.0423 0.01407 0.00736 -0.1262 0.7369 0.4454
-4.500 0.0672 0.01426 0.00739 -0.1255 0.7248 0.4592
-4.250 0.0939 0.01444 0.00754 -0.1249 0.7141 0.4696
-4.000 0.1217 0.01457 0.00751 -0.1248 0.7043 0.4801
-3.750 0.1467 0.01470 0.00757 -0.1240 0.6935 0.4896
-3.500 0.1746 0.01481 0.00754 -0.1239 0.6847 0.4985
-3.250 0.1996 0.01492 0.00759 -0.1232 0.6749 0.5078
-3.000 0.2274 0.01504 0.00761 -0.1231 0.6671 0.5167
-2.750 0.2526 0.01517 0.00767 -0.1225 0.6583 0.5267
-2.500 0.2809 0.01526 0.00765 -0.1225 0.6512 0.5343
-2.250 0.3056 0.01529 0.00766 -0.1218 0.6428 0.5412
-2.000 0.3342 0.01532 0.00750 -0.1221 0.6360 0.5480
-1.750 0.3595 0.01532 0.00752 -0.1215 0.6287 0.5528
-1.500 0.3867 0.01535 0.00747 -0.1214 0.6222 0.5587
-1.250 0.4157 0.01542 0.00737 -0.1218 0.6166 0.5651
-1.000 0.4404 0.01540 0.00740 -0.1212 0.6097 0.5695
-0.750 0.4681 0.01545 0.00737 -0.1213 0.6040 0.5752
-0.500 0.4962 0.01555 0.00734 -0.1215 0.5986 0.5818
-0.250 0.5214 0.01555 0.00739 -0.1210 0.5927 0.5863
0.000 0.5492 0.01561 0.00741 -0.1211 0.5877 0.5920
0.250 0.5788 0.01576 0.00742 -0.1216 0.5832 0.5989
0.500 0.6027 0.01578 0.00752 -0.1209 0.5777 0.6040
0.750 0.6294 0.01585 0.00758 -0.1208 0.5726 0.6098
1.000 0.6590 0.01599 0.00759 -0.1213 0.5684 0.6171
1.250 0.6846 0.01609 0.00776 -0.1209 0.5640 0.6228
1.500 0.7098 0.01620 0.00791 -0.1205 0.5594 0.6297
1.750 0.7372 0.01630 0.00798 -0.1206 0.5551 0.6366
2.000 0.7663 0.01644 0.00809 -0.1209 0.5513 0.6437
2.250 0.7915 0.01661 0.00829 -0.1206 0.5470 0.6523
2.500 0.8156 0.01672 0.00850 -0.1200 0.5427 0.6595
2.750 0.8427 0.01687 0.00864 -0.1200 0.5389 0.6688
3.000 0.8710 0.01701 0.00880 -0.1202 0.5355 0.6773
3.250 0.8988 0.01724 0.00903 -0.1204 0.5321 0.6881
3.500 0.9202 0.01738 0.00932 -0.1193 0.5278 0.6984
3.750 0.9448 0.01753 0.00955 -0.1189 0.5238 0.7097
4.000 0.9719 0.01769 0.00974 -0.1189 0.5205 0.7232
4.250 1.0011 0.01790 0.00996 -0.1193 0.5176 0.7387
4.500 1.0240 0.01813 0.01033 -0.1185 0.5142 0.7555
4.750 1.0439 0.01829 0.01067 -0.1171 0.5102 0.7745
5.000 1.0659 0.01841 0.01093 -0.1161 0.5065 0.7979
5.250 1.0896 0.01851 0.01115 -0.1152 0.5035 0.8303
5.500 1.1151 0.01860 0.01134 -0.1146 0.5008 0.8843
5.750 1.1498 0.01886 0.01177 -0.1165 0.4972 1.0000
6.000 1.1720 0.01922 0.01219 -0.1159 0.4931 1.0000
6.250 1.1972 0.01955 0.01252 -0.1158 0.4896 1.0000
6.500 1.2257 0.01986 0.01281 -0.1163 0.4866 1.0000
6.750 1.2582 0.02023 0.01310 -0.1175 0.4837 1.0000
7.000 1.2756 0.02069 0.01368 -0.1159 0.4799 1.0000
7.250 1.2945 0.02110 0.01420 -0.1146 0.4759 1.0000
7.500 1.3183 0.02141 0.01454 -0.1141 0.4722 1.0000
7.750 1.3480 0.02165 0.01476 -0.1147 0.4689 1.0000
8.000 1.3753 0.02206 0.01518 -0.1149 0.4654 1.0000
8.250 1.3866 0.02250 0.01578 -0.1123 0.4606 1.0000
8.500 1.4075 0.02273 0.01607 -0.1112 0.4560 1.0000
8.750 1.4387 0.02281 0.01611 -0.1120 0.4519 1.0000
9.000 1.4563 0.02317 0.01655 -0.1104 0.4470 1.0000
9.250 1.4682 0.02344 0.01694 -0.1077 0.4415 1.0000
9.500 1.4953 0.02340 0.01687 -0.1077 0.4363 1.0000
9.750 1.5161 0.02365 0.01716 -0.1066 0.4314 1.0000
10.000 1.5223 0.02399 0.01766 -0.1030 0.4259 1.0000
10.250 1.5448 0.02403 0.01770 -0.1022 0.4207 1.0000
10.500 1.5673 0.02420 0.01789 -0.1015 0.4157 1.0000
10.750 1.5642 0.02461 0.01849 -0.0962 0.4103 1.0000
11.000 1.5800 0.02469 0.01859 -0.0943 0.4049 1.0000
11.250 1.5964 0.02486 0.01878 -0.0925 0.3994 1.0000
11.500 1.5915 0.02538 0.01947 -0.0873 0.3935 1.0000
11.750 1.6067 0.02545 0.01955 -0.0854 0.3874 1.0000
12.000 1.6074 0.02599 0.02021 -0.0814 0.3812 1.0000
12.250 1.6078 0.02654 0.02086 -0.0776 0.3744 1.0000
12.500 1.6167 0.02691 0.02125 -0.0751 0.3676 1.0000
12.750 1.6083 0.02796 0.02246 -0.0707 0.3600 1.0000
13.000 1.6140 0.02858 0.02310 -0.0681 0.3522 1.0000
13.250 1.6042 0.03005 0.02472 -0.0643 0.3436 1.0000
13.500 1.6024 0.03131 0.02604 -0.0616 0.3346 1.0000
13.750 1.5979 0.03287 0.02765 -0.0589 0.3246 1.0000
14.000 1.5880 0.03505 0.02995 -0.0563 0.3137 1.0000
14.250 1.5796 0.03734 0.03229 -0.0541 0.3020 1.0000
14.500 1.5695 0.03998 0.03494 -0.0522 0.2893 1.0000
14.750 1.5568 0.04308 0.03805 -0.0505 0.2754 1.0000
15.000 1.5419 0.04662 0.04160 -0.0492 0.2607 1.0000
15.250 1.5253 0.05058 0.04554 -0.0482 0.2453 1.0000
15.500 1.5079 0.05484 0.04976 -0.0474 0.2300 1.0000
15.750 1.4904 0.05931 0.05418 -0.0470 0.2153 1.0000
16.000 1.4734 0.06391 0.05873 -0.0468 0.2014 1.0000
16.250 1.4579 0.06850 0.06326 -0.0468 0.1885 1.0000
16.500 1.4436 0.07312 0.06784 -0.0471 0.1762 1.0000
16.750 1.4319 0.07757 0.07229 -0.0475 0.1648 1.0000
17.000 1.4219 0.08188 0.07659 -0.0481 0.1545 1.0000
17.250 1.4122 0.08619 0.08084 -0.0487 0.1452 1.0000
17.500 1.4041 0.09043 0.08510 -0.0494 0.1360 1.0000
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Polar data table (+)
Polar graphs
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