E186 (10.27%) (e186-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E186 (10.27%) (e186-il) Reynolds number: 200,000 Max Cl/Cd: 61.86 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e186-il-200000.txt Download as CSV file: xf-e186-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6684 0.08651 0.08366 0.0088 1.0000 0.0558
-8.750 -0.6936 0.08089 0.07798 0.0047 1.0000 0.0561
-8.500 -0.7149 0.07695 0.07384 0.0037 1.0000 0.0565
-7.000 -0.6919 0.05036 0.04661 0.0039 1.0000 0.0725
-6.750 -0.6747 0.04739 0.04361 0.0039 1.0000 0.0752
-6.500 -0.6665 0.04395 0.03960 0.0047 1.0000 0.0846
-6.250 -0.6491 0.02967 0.02385 0.0084 0.9392 0.0377
-6.000 -0.6337 0.02650 0.01982 0.0121 0.8980 0.0346
-5.750 -0.6174 0.02471 0.01777 0.0145 0.8709 0.0360
-5.500 -0.5974 0.02323 0.01601 0.0164 0.8493 0.0369
-5.250 -0.5749 0.02152 0.01397 0.0181 0.8322 0.0367
-5.000 -0.5511 0.02008 0.01229 0.0194 0.8171 0.0370
-4.750 -0.5267 0.01887 0.01089 0.0205 0.8031 0.0379
-4.500 -0.5023 0.01784 0.00974 0.0215 0.7902 0.0392
-4.250 -0.4782 0.01697 0.00875 0.0225 0.7783 0.0412
-4.000 -0.4535 0.01643 0.00807 0.0234 0.7674 0.0443
-3.750 -0.4322 0.01539 0.00698 0.0248 0.7580 0.0492
-3.500 -0.4077 0.01479 0.00626 0.0258 0.7478 0.0568
-3.250 -0.3890 0.01326 0.00534 0.0274 0.7390 0.1613
-3.000 -0.3694 0.01233 0.00497 0.0288 0.7309 0.2982
-2.750 -0.3524 0.01136 0.00473 0.0306 0.7222 0.4612
-2.500 -0.3379 0.01048 0.00453 0.0336 0.7155 0.6308
-2.250 -0.2543 0.01011 0.00497 0.0240 0.7059 0.8876
-2.000 -0.1987 0.01081 0.00546 0.0198 0.6983 0.9334
-1.750 -0.1501 0.01126 0.00571 0.0162 0.6900 0.9537
-1.500 -0.1031 0.01161 0.00587 0.0127 0.6824 0.9709
-1.250 -0.0491 0.01175 0.00580 0.0075 0.6746 0.9839
-1.000 0.0059 0.01166 0.00557 0.0018 0.6667 0.9949
-0.750 0.0449 0.01149 0.00525 -0.0008 0.6598 1.0000
-0.500 0.0683 0.01143 0.00512 -0.0003 0.6529 1.0000
-0.250 0.0916 0.01140 0.00499 0.0003 0.6464 1.0000
0.000 0.1155 0.01139 0.00491 0.0008 0.6402 1.0000
0.250 0.1397 0.01138 0.00485 0.0013 0.6335 1.0000
0.500 0.1638 0.01141 0.00478 0.0019 0.6280 1.0000
0.750 0.1889 0.01143 0.00479 0.0022 0.6210 1.0000
1.000 0.2132 0.01147 0.00475 0.0028 0.6157 1.0000
1.250 0.2387 0.01152 0.00482 0.0031 0.6088 1.0000
1.500 0.2636 0.01157 0.00482 0.0036 0.6030 1.0000
1.750 0.2889 0.01166 0.00489 0.0039 0.5971 1.0000
2.000 0.3144 0.01172 0.00495 0.0043 0.5904 1.0000
2.250 0.3394 0.01181 0.00500 0.0048 0.5852 1.0000
2.500 0.3655 0.01188 0.00513 0.0050 0.5775 1.0000
2.750 0.3905 0.01195 0.00515 0.0056 0.5718 1.0000
3.000 0.4165 0.01202 0.00529 0.0058 0.5634 1.0000
3.250 0.4414 0.01208 0.00531 0.0065 0.5571 1.0000
3.500 0.4674 0.01214 0.00546 0.0068 0.5480 1.0000
3.750 0.4926 0.01219 0.00550 0.0074 0.5405 1.0000
4.000 0.5182 0.01221 0.00559 0.0079 0.5312 1.0000
4.250 0.5437 0.01225 0.00569 0.0083 0.5217 1.0000
4.500 0.5688 0.01226 0.00569 0.0090 0.5128 1.0000
4.750 0.5944 0.01225 0.00576 0.0095 0.5017 1.0000
5.000 0.6200 0.01225 0.00587 0.0100 0.4899 1.0000
5.250 0.6454 0.01224 0.00593 0.0106 0.4772 1.0000
5.500 0.6708 0.01222 0.00597 0.0111 0.4625 1.0000
5.750 0.6962 0.01219 0.00601 0.0117 0.4455 1.0000
6.000 0.7216 0.01221 0.00610 0.0122 0.4248 1.0000
6.250 0.7468 0.01227 0.00624 0.0127 0.3979 1.0000
6.500 0.7714 0.01247 0.00637 0.0131 0.3475 1.0000
6.750 0.7933 0.01339 0.00681 0.0133 0.2479 1.0000
7.000 0.8137 0.01475 0.00773 0.0133 0.1658 1.0000
7.250 0.8328 0.01620 0.00882 0.0135 0.1000 1.0000
7.500 0.8461 0.01865 0.01083 0.0143 0.0389 1.0000
7.750 0.8620 0.02021 0.01246 0.0154 0.0310 1.0000
8.000 0.8771 0.02160 0.01391 0.0167 0.0275 1.0000
8.250 0.8861 0.02368 0.01602 0.0186 0.0255 1.0000
8.500 0.9010 0.02499 0.01744 0.0203 0.0246 1.0000
8.750 0.9154 0.02648 0.01903 0.0221 0.0237 1.0000
9.000 0.9304 0.02812 0.02077 0.0238 0.0230 1.0000
9.250 0.9456 0.02963 0.02243 0.0254 0.0220 1.0000
9.500 0.9592 0.03101 0.02390 0.0268 0.0206 1.0000
9.750 0.9717 0.03270 0.02565 0.0282 0.0196 1.0000
10.000 0.9844 0.03490 0.02803 0.0298 0.0194 1.0000
10.250 0.9947 0.03748 0.03081 0.0315 0.0192 1.0000
10.500 1.0014 0.03998 0.03358 0.0332 0.0193 1.0000
10.750 1.0033 0.04279 0.03667 0.0352 0.0193 1.0000
11.000 0.9972 0.04538 0.03955 0.0378 0.0196 1.0000
11.250 0.9844 0.04866 0.04314 0.0401 0.0201 1.0000
11.500 0.9640 0.05268 0.04752 0.0410 0.0207 1.0000
11.750 0.9448 0.05710 0.05221 0.0407 0.0210 1.0000
12.000 0.9231 0.06231 0.05768 0.0393 0.0216 1.0000
12.250 0.9026 0.06771 0.06328 0.0372 0.0221 1.0000
12.500 0.8818 0.07356 0.06930 0.0343 0.0225 1.0000
12.750 0.8584 0.08029 0.07619 0.0305 0.0227 1.0000
13.000 0.8342 0.08778 0.08383 0.0259 0.0228 1.0000
13.250 0.8120 0.09571 0.09187 0.0209 0.0232 1.0000
13.500 0.7850 0.10592 0.10217 0.0145 0.0236 1.0000
13.750 0.7588 0.11755 0.11384 0.0079 0.0243 1.0000
14.000 0.7432 0.12622 0.12249 0.0044 0.0253 1.0000
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Polar data table (+)
Polar graphs
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