EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E854 AIRFOIL (e854-il) Reynolds number: 200,000 Max Cl/Cd: 82.37 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e854-il-200000.txt Download as CSV file: xf-e854-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E854 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3935 0.10398 0.10058 -0.0503 1.0000 0.0499
-10.000 -0.4021 0.09911 0.09578 -0.0529 1.0000 0.0501
-9.750 -0.4159 0.09339 0.09012 -0.0563 1.0000 0.0502
-9.500 -0.4081 0.09084 0.08762 -0.0510 1.0000 0.0517
-9.250 -0.4065 0.08853 0.08534 -0.0497 1.0000 0.0526
-9.000 -0.4115 0.08547 0.08234 -0.0494 1.0000 0.0532
-8.750 -0.4203 0.08223 0.07917 -0.0490 1.0000 0.0541
-8.500 -0.4352 0.07876 0.07578 -0.0487 1.0000 0.0547
-8.250 -0.4628 0.07469 0.07182 -0.0488 1.0000 0.0547
-7.500 -0.4934 0.04219 0.03780 -0.0792 0.9735 0.0311
-7.250 -0.4709 0.03517 0.03009 -0.0819 0.9663 0.0245
-7.000 -0.4416 0.02897 0.02286 -0.0842 0.9609 0.0219
-6.750 -0.4100 0.02621 0.01968 -0.0857 0.9549 0.0219
-6.500 -0.3762 0.02394 0.01719 -0.0874 0.9494 0.0226
-6.250 -0.3373 0.02213 0.01524 -0.0899 0.9462 0.0247
-6.000 -0.3064 0.02108 0.01403 -0.0907 0.9376 0.0280
-5.750 -0.2693 0.01917 0.01212 -0.0930 0.9339 0.0337
-5.500 -0.2376 0.01768 0.01059 -0.0941 0.9264 0.0434
-5.250 -0.1995 0.01640 0.00929 -0.0965 0.9216 0.0646
-5.000 -0.1582 0.01504 0.00806 -0.0998 0.9188 0.1001
-4.750 -0.1269 0.01366 0.00705 -0.1014 0.9099 0.1746
-4.500 -0.0865 0.01215 0.00649 -0.1052 0.9059 0.3966
-4.250 -0.0504 0.01206 0.00637 -0.1066 0.8973 0.4588
-4.000 -0.0079 0.01201 0.00622 -0.1092 0.8915 0.4945
-3.750 0.0273 0.01201 0.00612 -0.1105 0.8815 0.5173
-3.500 0.0658 0.01199 0.00597 -0.1123 0.8728 0.5369
-3.250 0.1020 0.01196 0.00584 -0.1138 0.8628 0.5523
-3.000 0.1338 0.01198 0.00575 -0.1144 0.8509 0.5660
-2.750 0.1649 0.01202 0.00569 -0.1148 0.8394 0.5801
-2.500 0.1955 0.01209 0.00568 -0.1151 0.8283 0.5944
-2.250 0.2262 0.01212 0.00564 -0.1154 0.8181 0.6057
-2.000 0.2536 0.01213 0.00558 -0.1152 0.8066 0.6141
-1.750 0.2819 0.01215 0.00547 -0.1154 0.7958 0.6229
-1.500 0.3103 0.01214 0.00541 -0.1154 0.7862 0.6293
-1.250 0.3393 0.01216 0.00531 -0.1157 0.7768 0.6375
-1.000 0.3657 0.01216 0.00529 -0.1154 0.7671 0.6436
-0.750 0.3947 0.01221 0.00523 -0.1156 0.7589 0.6518
-0.500 0.4214 0.01222 0.00523 -0.1154 0.7498 0.6582
-0.250 0.4492 0.01228 0.00522 -0.1155 0.7418 0.6665
0.000 0.4768 0.01230 0.00523 -0.1154 0.7342 0.6733
0.250 0.5039 0.01237 0.00527 -0.1154 0.7263 0.6820
0.500 0.5316 0.01241 0.00531 -0.1153 0.7193 0.6896
0.750 0.5582 0.01248 0.00539 -0.1152 0.7119 0.6984
1.000 0.5860 0.01255 0.00544 -0.1152 0.7054 0.7076
1.250 0.6122 0.01262 0.00556 -0.1149 0.6984 0.7168
1.500 0.6396 0.01270 0.00565 -0.1149 0.6919 0.7273
1.750 0.6666 0.01280 0.00578 -0.1148 0.6860 0.7387
2.000 0.6922 0.01287 0.00593 -0.1144 0.6793 0.7502
2.250 0.7206 0.01297 0.00604 -0.1145 0.6741 0.7630
2.500 0.7442 0.01305 0.00626 -0.1137 0.6672 0.7774
2.750 0.7710 0.01313 0.00639 -0.1135 0.6617 0.7939
3.000 0.7953 0.01324 0.00661 -0.1128 0.6558 0.8128
3.250 0.8185 0.01329 0.00680 -0.1118 0.6497 0.8340
3.500 0.8428 0.01334 0.00693 -0.1109 0.6447 0.8615
3.750 0.8613 0.01333 0.00711 -0.1088 0.6379 0.9022
4.000 0.8997 0.01329 0.00714 -0.1109 0.6318 1.0000
4.250 0.9272 0.01349 0.00739 -0.1113 0.6237 1.0000
4.500 0.9582 0.01365 0.00748 -0.1121 0.6168 1.0000
4.750 0.9823 0.01378 0.00768 -0.1115 0.6070 1.0000
5.000 1.0082 0.01388 0.00780 -0.1112 0.5969 1.0000
5.250 1.0351 0.01394 0.00783 -0.1109 0.5866 1.0000
5.500 1.0590 0.01403 0.00797 -0.1101 0.5758 1.0000
5.750 1.0827 0.01415 0.00816 -0.1093 0.5653 1.0000
6.000 1.1072 0.01426 0.00833 -0.1086 0.5548 1.0000
6.250 1.1317 0.01436 0.00845 -0.1079 0.5436 1.0000
6.500 1.1539 0.01444 0.00860 -0.1067 0.5308 1.0000
6.750 1.1750 0.01453 0.00876 -0.1053 0.5162 1.0000
7.000 1.1943 0.01463 0.00894 -0.1036 0.4991 1.0000
7.250 1.2124 0.01474 0.00916 -0.1016 0.4784 1.0000
7.500 1.2289 0.01492 0.00936 -0.0994 0.4534 1.0000
7.750 1.2426 0.01521 0.00963 -0.0967 0.4197 1.0000
8.000 1.2506 0.01576 0.01000 -0.0931 0.3699 1.0000
8.250 1.2483 0.01677 0.01064 -0.0879 0.3036 1.0000
8.500 1.2408 0.01814 0.01163 -0.0821 0.2438 1.0000
8.750 1.2345 0.01968 0.01284 -0.0770 0.1923 1.0000
9.000 1.2303 0.02125 0.01416 -0.0725 0.1527 1.0000
9.250 1.2277 0.02284 0.01557 -0.0686 0.1241 1.0000
9.500 1.2268 0.02444 0.01707 -0.0651 0.1032 1.0000
9.750 1.2260 0.02613 0.01870 -0.0619 0.0870 1.0000
10.000 1.2260 0.02791 0.02048 -0.0591 0.0747 1.0000
10.250 1.2258 0.02982 0.02239 -0.0566 0.0648 1.0000
10.500 1.2236 0.03201 0.02455 -0.0542 0.0568 1.0000
10.750 1.2275 0.03385 0.02644 -0.0525 0.0491 1.0000
11.000 1.2278 0.03611 0.02876 -0.0507 0.0430 1.0000
11.250 1.2294 0.03832 0.03099 -0.0492 0.0377 1.0000
11.500 1.2303 0.04074 0.03350 -0.0477 0.0329 1.0000
11.750 1.2332 0.04301 0.03583 -0.0466 0.0291 1.0000
12.000 1.2315 0.04596 0.03880 -0.0451 0.0259 1.0000
12.250 1.2375 0.04807 0.04105 -0.0443 0.0229 1.0000
12.500 1.2398 0.05057 0.04357 -0.0437 0.0205 1.0000
12.750 1.2444 0.05338 0.04646 -0.0423 0.0189 1.0000
13.000 1.2521 0.05571 0.04901 -0.0414 0.0177 1.0000
13.250 1.2594 0.05823 0.05168 -0.0406 0.0166 1.0000
13.500 1.2650 0.06095 0.05456 -0.0399 0.0158 1.0000
13.750 1.2682 0.06377 0.05749 -0.0396 0.0149 1.0000
14.000 1.2714 0.06687 0.06068 -0.0393 0.0142 1.0000
14.250 1.2706 0.07170 0.06575 -0.0387 0.0135 1.0000
14.500 1.2637 0.07544 0.06974 -0.0392 0.0132 1.0000
14.750 1.2568 0.07962 0.07418 -0.0399 0.0129 1.0000
15.000 1.2483 0.08430 0.07911 -0.0410 0.0126 1.0000
15.250 1.2387 0.08934 0.08439 -0.0424 0.0124 1.0000
15.500 1.2265 0.09494 0.09024 -0.0443 0.0121 1.0000
15.750 1.2126 0.10116 0.09670 -0.0466 0.0121 1.0000
16.000 1.1970 0.10787 0.10365 -0.0496 0.0121 1.0000
16.250 1.1802 0.11512 0.11113 -0.0533 0.0122 1.0000
16.500 1.1626 0.12288 0.11910 -0.0575 0.0123 1.0000
16.750 1.1443 0.13124 0.12766 -0.0625 0.0124 1.0000
17.000 1.1254 0.14027 0.13688 -0.0683 0.0126 1.0000
17.250 1.1061 0.15000 0.14677 -0.0746 0.0128 1.0000
17.500 1.0867 0.16034 0.15722 -0.0814 0.0132 1.0000
17.750 1.0678 0.17112 0.16808 -0.0882 0.0136 1.0000
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