EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 500,000 Max Cl/Cd: 85.19 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e857-il-500000-n5.txt Download as CSV file: xf-e857-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 857 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6607 0.11274 0.10907 -0.0585 1.0000 0.0085
-17.500 -0.6740 0.10692 0.10316 -0.0611 1.0000 0.0086
-17.250 -0.6868 0.10132 0.09747 -0.0635 1.0000 0.0086
-17.000 -0.6981 0.09613 0.09220 -0.0657 1.0000 0.0086
-16.750 -0.7098 0.09100 0.08698 -0.0679 1.0000 0.0085
-16.500 -0.7209 0.08603 0.08193 -0.0699 1.0000 0.0088
-16.250 -0.7325 0.08124 0.07706 -0.0717 1.0000 0.0088
-16.000 -0.7413 0.07699 0.07273 -0.0733 1.0000 0.0088
-15.750 -0.7513 0.07272 0.06838 -0.0747 1.0000 0.0088
-15.500 -0.7503 0.06828 0.06385 -0.0784 0.9990 0.0089
-15.250 -0.7473 0.06400 0.05947 -0.0823 0.9975 0.0090
-15.000 -0.7417 0.06023 0.05561 -0.0859 0.9960 0.0091
-14.750 -0.7365 0.05639 0.05167 -0.0897 0.9943 0.0092
-14.500 -0.7296 0.05294 0.04813 -0.0932 0.9928 0.0093
-14.250 -0.7245 0.04978 0.04489 -0.0958 0.9903 0.0094
-14.000 -0.7180 0.04657 0.04160 -0.0989 0.9876 0.0095
-13.750 -0.7109 0.04321 0.03817 -0.1025 0.9851 0.0098
-13.500 -0.6978 0.04032 0.03521 -0.1064 0.9832 0.0100
-13.250 -0.6935 0.03790 0.03274 -0.1073 0.9780 0.0100
-12.750 -0.6810 0.03320 0.02792 -0.1097 0.9647 0.0105
-12.500 -0.6844 0.03112 0.02578 -0.1087 0.9506 0.0107
-12.250 -0.6810 0.02910 0.02370 -0.1086 0.9353 0.0109
-12.000 -0.6655 0.02701 0.02153 -0.1108 0.9219 0.0111
-11.750 -0.6383 0.02503 0.01944 -0.1147 0.9091 0.0117
-11.500 -0.5932 0.02278 0.01707 -0.1225 0.8946 0.0123
-11.250 -0.5267 0.02092 0.01507 -0.1335 0.8776 0.0134
-11.000 -0.4506 0.01940 0.01336 -0.1460 0.8515 0.0152
-10.750 -0.4223 0.01849 0.01221 -0.1487 0.8153 0.0163
-10.500 -0.4159 0.01796 0.01150 -0.1462 0.7867 0.0173
-10.250 -0.4074 0.01748 0.01087 -0.1437 0.7630 0.0184
-10.000 -0.3960 0.01706 0.01033 -0.1415 0.7435 0.0198
-9.750 -0.3833 0.01664 0.00982 -0.1395 0.7268 0.0214
-9.500 -0.3685 0.01628 0.00935 -0.1376 0.7108 0.0233
-9.250 -0.3530 0.01591 0.00890 -0.1359 0.6961 0.0254
-9.000 -0.3361 0.01558 0.00848 -0.1343 0.6824 0.0278
-8.750 -0.3178 0.01525 0.00809 -0.1329 0.6694 0.0307
-8.500 -0.2987 0.01492 0.00771 -0.1316 0.6584 0.0343
-8.250 -0.2794 0.01461 0.00734 -0.1303 0.6472 0.0387
-8.000 -0.2586 0.01431 0.00700 -0.1293 0.6367 0.0430
-7.750 -0.2382 0.01404 0.00667 -0.1281 0.6260 0.0482
-7.500 -0.2166 0.01375 0.00636 -0.1272 0.6155 0.0544
-7.250 -0.1953 0.01349 0.00606 -0.1262 0.6057 0.0621
-7.000 -0.1729 0.01321 0.00578 -0.1254 0.5963 0.0717
-6.750 -0.1505 0.01297 0.00552 -0.1245 0.5879 0.0816
-6.500 -0.1270 0.01272 0.00527 -0.1239 0.5797 0.0926
-6.250 -0.1042 0.01249 0.00502 -0.1231 0.5716 0.1036
-6.000 -0.0804 0.01224 0.00477 -0.1225 0.5642 0.1167
-5.750 -0.0572 0.01197 0.00452 -0.1218 0.5559 0.1347
-5.500 -0.0341 0.01167 0.00427 -0.1211 0.5485 0.1600
-5.250 -0.0106 0.01136 0.00403 -0.1205 0.5408 0.1893
-5.000 0.0123 0.01105 0.00380 -0.1198 0.5339 0.2263
-4.750 0.0365 0.01073 0.00362 -0.1193 0.5279 0.2697
-4.500 0.0615 0.01057 0.00352 -0.1189 0.5214 0.3009
-4.250 0.0864 0.01051 0.00345 -0.1183 0.5153 0.3227
-4.000 0.1127 0.01045 0.00341 -0.1180 0.5098 0.3401
-3.750 0.1386 0.01044 0.00337 -0.1176 0.5037 0.3546
-3.500 0.1638 0.01046 0.00334 -0.1170 0.4977 0.3660
-3.250 0.1899 0.01046 0.00331 -0.1166 0.4922 0.3736
-3.000 0.2159 0.01048 0.00328 -0.1162 0.4868 0.3816
-2.750 0.2414 0.01051 0.00326 -0.1156 0.4815 0.3884
-2.500 0.2668 0.01055 0.00327 -0.1151 0.4769 0.3964
-2.250 0.2933 0.01058 0.00325 -0.1148 0.4726 0.4028
-2.000 0.3191 0.01060 0.00326 -0.1143 0.4680 0.4096
-1.750 0.3443 0.01066 0.00329 -0.1137 0.4633 0.4187
-1.500 0.3697 0.01073 0.00330 -0.1132 0.4590 0.4246
-1.250 0.3958 0.01075 0.00331 -0.1128 0.4548 0.4287
-1.000 0.4216 0.01079 0.00333 -0.1124 0.4506 0.4325
-0.750 0.4468 0.01085 0.00335 -0.1118 0.4466 0.4361
-0.500 0.4717 0.01093 0.00337 -0.1112 0.4430 0.4397
-0.250 0.4976 0.01099 0.00340 -0.1108 0.4399 0.4431
0.000 0.5234 0.01102 0.00344 -0.1104 0.4367 0.4467
0.250 0.5488 0.01108 0.00349 -0.1100 0.4331 0.4502
0.500 0.5738 0.01116 0.00355 -0.1094 0.4295 0.4538
0.750 0.5983 0.01127 0.00361 -0.1088 0.4261 0.4576
1.000 0.6235 0.01137 0.00368 -0.1083 0.4230 0.4613
1.250 0.6493 0.01142 0.00375 -0.1079 0.4204 0.4649
1.500 0.6747 0.01150 0.00384 -0.1074 0.4176 0.4687
1.750 0.6997 0.01159 0.00393 -0.1069 0.4147 0.4726
2.000 0.7244 0.01170 0.00402 -0.1064 0.4119 0.4766
2.250 0.7485 0.01183 0.00413 -0.1057 0.4090 0.4808
2.500 0.7724 0.01196 0.00425 -0.1050 0.4062 0.4847
2.750 0.7976 0.01203 0.00436 -0.1046 0.4038 0.4892
3.000 0.8224 0.01213 0.00448 -0.1041 0.4014 0.4936
3.250 0.8468 0.01224 0.00460 -0.1035 0.3989 0.4980
3.500 0.8709 0.01237 0.00473 -0.1029 0.3965 0.5024
3.750 0.8943 0.01250 0.00488 -0.1021 0.3940 0.5078
4.000 0.9174 0.01265 0.00503 -0.1014 0.3915 0.5133
4.250 0.9404 0.01281 0.00519 -0.1006 0.3890 0.5186
4.500 0.9650 0.01292 0.00534 -0.1001 0.3870 0.5235
4.750 0.9889 0.01303 0.00551 -0.0995 0.3848 0.5296
5.000 1.0124 0.01317 0.00568 -0.0988 0.3827 0.5365
5.250 1.0353 0.01332 0.00586 -0.0981 0.3805 0.5431
5.500 1.0577 0.01347 0.00605 -0.0972 0.3783 0.5507
5.750 1.0796 0.01365 0.00625 -0.0963 0.3759 0.5583
6.000 1.1009 0.01385 0.00647 -0.0953 0.3736 0.5658
6.250 1.1229 0.01403 0.00670 -0.0945 0.3715 0.5749
6.500 1.1457 0.01418 0.00692 -0.0937 0.3697 0.5845
6.750 1.1680 0.01434 0.00715 -0.0930 0.3678 0.5963
7.000 1.1897 0.01451 0.00740 -0.0921 0.3658 0.6084
7.500 1.2314 0.01490 0.00791 -0.0901 0.3614 0.6356
7.750 1.2509 0.01512 0.00820 -0.0889 0.3591 0.6517
8.000 1.2695 0.01537 0.00852 -0.0876 0.3569 0.6713
8.250 1.2887 0.01561 0.00885 -0.0864 0.3550 0.6960
8.500 1.3088 0.01577 0.00916 -0.0853 0.3534 0.7264
8.750 1.3272 0.01592 0.00950 -0.0839 0.3515 0.7717
9.000 1.3536 0.01589 0.00986 -0.0841 0.3491 0.9241
9.250 1.3755 0.01616 0.01017 -0.0836 0.3467 1.0000
9.500 1.3939 0.01651 0.01054 -0.0825 0.3444 1.0000
9.750 1.4113 0.01690 0.01094 -0.0812 0.3421 1.0000
10.000 1.4283 0.01733 0.01137 -0.0799 0.3399 1.0000
10.250 1.4461 0.01773 0.01182 -0.0788 0.3377 1.0000
10.500 1.4646 0.01810 0.01226 -0.0778 0.3353 1.0000
10.750 1.4812 0.01854 0.01274 -0.0765 0.3320 1.0000
11.000 1.4958 0.01906 0.01329 -0.0751 0.3282 1.0000
11.250 1.5080 0.01970 0.01393 -0.0734 0.3244 1.0000
11.500 1.5227 0.02028 0.01455 -0.0721 0.3212 1.0000
11.750 1.5378 0.02085 0.01519 -0.0708 0.3175 1.0000
12.000 1.5509 0.02153 0.01591 -0.0695 0.3135 1.0000
12.250 1.5615 0.02236 0.01675 -0.0679 0.3095 1.0000
12.500 1.5724 0.02321 0.01764 -0.0664 0.3062 1.0000
12.750 1.5861 0.02396 0.01847 -0.0653 0.3022 1.0000
13.000 1.5965 0.02491 0.01947 -0.0639 0.2978 1.0000
13.250 1.6038 0.02607 0.02065 -0.0624 0.2935 1.0000
13.500 1.6131 0.02717 0.02180 -0.0611 0.2897 1.0000
13.750 1.6229 0.02829 0.02298 -0.0600 0.2850 1.0000
14.000 1.6276 0.02978 0.02451 -0.0585 0.2796 1.0000
14.250 1.6316 0.03137 0.02614 -0.0572 0.2747 1.0000
14.500 1.6375 0.03290 0.02773 -0.0561 0.2689 1.0000
14.750 1.6376 0.03492 0.02978 -0.0548 0.2630 1.0000
15.000 1.6392 0.03691 0.03182 -0.0537 0.2567 1.0000
15.250 1.6367 0.03931 0.03426 -0.0526 0.2496 1.0000
15.500 1.6326 0.04193 0.03692 -0.0515 0.2425 1.0000
15.750 1.6257 0.04491 0.03993 -0.0506 0.2345 1.0000
16.000 1.6180 0.04807 0.04312 -0.0498 0.2267 1.0000
16.250 1.6041 0.05194 0.04702 -0.0490 0.2180 1.0000
16.500 1.5929 0.05566 0.05077 -0.0485 0.2088 1.0000
16.750 1.5763 0.06008 0.05522 -0.0482 0.2001 1.0000
17.000 1.5574 0.06488 0.06003 -0.0480 0.1904 1.0000
17.250 1.5409 0.06955 0.06472 -0.0480 0.1813 1.0000
17.500 1.5223 0.07461 0.06980 -0.0483 0.1736 1.0000
17.750 1.5070 0.07935 0.07457 -0.0487 0.1649 1.0000
18.000 1.4910 0.08430 0.07955 -0.0492 0.1575 1.0000
18.250 1.4756 0.08929 0.08456 -0.0500 0.1498 1.0000
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