E186 (10.27%) (e186-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E186 (10.27%) (e186-il) Reynolds number: 50,000 Max Cl/Cd: 29.86 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e186-il-50000.txt Download as CSV file: xf-e186-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E186 (10.27%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.6442 0.05172 0.04459 0.0001 1.0000 0.1229
-6.250 -0.6287 0.04751 0.04012 0.0006 1.0000 0.1205
-6.000 -0.6131 0.04333 0.03548 0.0014 1.0000 0.1167
-5.750 -0.5959 0.03937 0.03081 0.0026 1.0000 0.1128
-5.500 -0.5745 0.03616 0.02698 0.0036 1.0000 0.1117
-5.250 -0.5493 0.03325 0.02378 0.0039 1.0000 0.1133
-5.000 -0.5241 0.03091 0.02124 0.0041 1.0000 0.1181
-4.750 -0.5031 0.02901 0.01903 0.0050 1.0000 0.1259
-4.500 -0.4884 0.02755 0.01756 0.0066 1.0000 0.1346
-4.250 -0.4726 0.02603 0.01602 0.0083 1.0000 0.1451
-4.000 -0.4535 0.02451 0.01452 0.0096 1.0000 0.1683
-3.750 -0.4350 0.02253 0.01312 0.0107 1.0000 0.2436
-3.500 -0.1268 0.02044 0.01271 -0.0215 1.0000 0.9937
-3.250 -0.0940 0.01959 0.01158 -0.0265 1.0000 1.0000
-3.000 -0.0796 0.01935 0.01114 -0.0280 1.0000 1.0000
-2.750 -0.0884 0.01962 0.01131 -0.0255 1.0000 1.0000
-2.500 -0.1069 0.02005 0.01163 -0.0208 1.0000 1.0000
-2.250 -0.0682 0.02017 0.01145 -0.0254 0.9852 1.0000
-2.000 -0.0070 0.02020 0.01117 -0.0334 0.9699 1.0000
-1.750 0.0508 0.02024 0.01093 -0.0405 0.9551 1.0000
-1.500 0.0990 0.02035 0.01085 -0.0455 0.9400 1.0000
-1.250 0.1382 0.02058 0.01090 -0.0488 0.9250 1.0000
-1.000 0.1703 0.02091 0.01110 -0.0505 0.9106 1.0000
-0.750 0.1976 0.02132 0.01140 -0.0514 0.8972 1.0000
-0.500 0.2221 0.02179 0.01178 -0.0516 0.8845 1.0000
-0.250 0.2458 0.02230 0.01220 -0.0515 0.8726 1.0000
0.000 0.2656 0.02289 0.01274 -0.0509 0.8606 1.0000
0.250 0.2856 0.02354 0.01334 -0.0504 0.8492 1.0000
0.500 0.3058 0.02421 0.01398 -0.0499 0.8386 1.0000
0.750 0.3272 0.02487 0.01462 -0.0493 0.8286 1.0000
1.000 0.3459 0.02563 0.01538 -0.0486 0.8183 1.0000
1.250 0.3631 0.02649 0.01623 -0.0478 0.8081 1.0000
1.500 0.3828 0.02730 0.01705 -0.0470 0.7987 1.0000
1.750 0.4017 0.02814 0.01793 -0.0461 0.7889 1.0000
2.000 0.4165 0.02920 0.01901 -0.0451 0.7788 1.0000
2.250 0.4344 0.03015 0.01999 -0.0441 0.7692 1.0000
2.500 0.4541 0.03103 0.02093 -0.0431 0.7595 1.0000
2.750 0.4666 0.03224 0.02218 -0.0419 0.7485 1.0000
3.000 0.4812 0.03339 0.02342 -0.0407 0.7379 1.0000
3.250 0.4999 0.03437 0.02448 -0.0394 0.7272 1.0000
3.500 0.5201 0.03527 0.02546 -0.0381 0.7159 1.0000
3.750 0.5321 0.03655 0.02682 -0.0366 0.7032 1.0000
4.000 0.5455 0.03776 0.02813 -0.0350 0.6901 1.0000
4.250 0.5604 0.03891 0.02941 -0.0334 0.6764 1.0000
4.500 0.5770 0.03994 0.03056 -0.0316 0.6618 1.0000
4.750 0.5955 0.04081 0.03157 -0.0297 0.6464 1.0000
5.000 0.6172 0.04137 0.03229 -0.0274 0.6302 1.0000
5.250 0.6319 0.04233 0.03339 -0.0252 0.6122 1.0000
5.500 0.6463 0.04322 0.03447 -0.0228 0.5924 1.0000
5.750 0.6749 0.04261 0.03408 -0.0193 0.5729 1.0000
6.000 0.6898 0.04313 0.03477 -0.0164 0.5500 1.0000
6.250 0.7239 0.04090 0.03278 -0.0111 0.5289 1.0000
6.500 0.7459 0.03976 0.03191 -0.0068 0.5024 1.0000
6.750 0.7742 0.03706 0.02942 -0.0011 0.4741 1.0000
7.000 0.8027 0.03365 0.02615 0.0049 0.4387 1.0000
7.250 0.8301 0.02970 0.02211 0.0114 0.3875 1.0000
7.500 0.8457 0.02832 0.02026 0.0161 0.3068 1.0000
7.750 0.8533 0.02990 0.02098 0.0194 0.2321 1.0000
8.000 0.8599 0.03260 0.02320 0.0219 0.1784 1.0000
8.250 0.8688 0.03534 0.02569 0.0240 0.1408 1.0000
8.500 0.8832 0.03812 0.02833 0.0259 0.1167 1.0000
8.750 0.9017 0.04114 0.03143 0.0275 0.1035 1.0000
9.000 0.9200 0.04431 0.03459 0.0288 0.0941 1.0000
9.250 0.9287 0.04744 0.03825 0.0304 0.0893 1.0000
9.500 0.9406 0.05075 0.04179 0.0317 0.0852 1.0000
9.750 0.9502 0.05466 0.04592 0.0329 0.0835 1.0000
10.000 0.9528 0.05879 0.05036 0.0341 0.0831 1.0000
10.250 0.9465 0.06287 0.05487 0.0353 0.0833 1.0000
10.500 0.9184 0.06683 0.05924 0.0364 0.0849 1.0000
10.750 0.8846 0.07106 0.06370 0.0367 0.0865 1.0000
11.000 0.8520 0.07646 0.06924 0.0346 0.0884 1.0000
11.250 0.8214 0.08316 0.07602 0.0308 0.0903 1.0000
11.500 0.7959 0.09048 0.08336 0.0266 0.0923 1.0000
11.750 0.7798 0.09753 0.09039 0.0232 0.0939 1.0000
12.000 0.7669 0.10480 0.09766 0.0198 0.0957 1.0000
12.250 0.7272 0.12014 0.11289 0.0095 0.1091 1.0000
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Polar data table (+)
Polar graphs
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