E182 (8.47%) (e182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.15 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e182-il-1000000-n5.txt Download as CSV file: xf-e182-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E182 (8.47%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6313 0.08522 0.08348 0.0129 0.8521 0.0049
-8.750 -0.6399 0.08015 0.07834 0.0101 0.8252 0.0049
-8.250 -0.7667 0.03482 0.03204 -0.0085 0.7924 0.0044
-8.000 -0.7548 0.03123 0.02811 -0.0081 0.7804 0.0045
-7.750 -0.7408 0.02789 0.02439 -0.0074 0.7693 0.0045
-7.500 -0.7226 0.02553 0.02172 -0.0068 0.7591 0.0046
-7.250 -0.7058 0.02228 0.01800 -0.0058 0.7495 0.0046
-7.000 -0.6853 0.02005 0.01541 -0.0050 0.7409 0.0046
-6.750 -0.6628 0.01838 0.01344 -0.0044 0.7324 0.0047
-6.500 -0.6391 0.01706 0.01188 -0.0038 0.7246 0.0047
-6.000 -0.5895 0.01501 0.00946 -0.0029 0.7095 0.0049
-5.500 -0.5382 0.01346 0.00763 -0.0022 0.6958 0.0053
-5.250 -0.5122 0.01282 0.00685 -0.0018 0.6892 0.0055
-5.000 -0.4860 0.01222 0.00615 -0.0015 0.6832 0.0057
-4.750 -0.4595 0.01173 0.00556 -0.0012 0.6768 0.0060
-4.500 -0.4329 0.01127 0.00501 -0.0009 0.6713 0.0062
-4.250 -0.4060 0.01086 0.00453 -0.0007 0.6655 0.0064
-4.000 -0.3791 0.01052 0.00410 -0.0005 0.6598 0.0065
-3.750 -0.3519 0.01019 0.00373 -0.0003 0.6547 0.0066
-3.500 -0.3253 0.00970 0.00316 0.0000 0.6494 0.0069
-3.250 -0.2985 0.00932 0.00270 0.0002 0.6442 0.0076
-3.000 -0.2711 0.00904 0.00238 0.0004 0.6391 0.0080
-2.750 -0.2435 0.00882 0.00210 0.0005 0.6339 0.0084
-2.500 -0.2159 0.00863 0.00187 0.0006 0.6291 0.0090
-2.250 -0.1881 0.00847 0.00167 0.0007 0.6240 0.0097
-2.000 -0.1602 0.00835 0.00149 0.0007 0.6187 0.0102
-1.750 -0.1323 0.00822 0.00134 0.0008 0.6141 0.0121
-1.500 -0.1049 0.00795 0.00118 0.0009 0.6091 0.0391
-1.250 -0.0777 0.00769 0.00105 0.0010 0.6039 0.0801
-1.000 -0.0505 0.00745 0.00095 0.0011 0.5991 0.1295
-0.750 -0.0235 0.00715 0.00087 0.0012 0.5940 0.1955
-0.500 0.0037 0.00692 0.00081 0.0012 0.5885 0.2545
-0.250 0.0294 0.00644 0.00075 0.0014 0.5836 0.3850
0.000 0.0548 0.00598 0.00071 0.0017 0.5780 0.5171
0.250 0.0812 0.00574 0.00068 0.0020 0.5722 0.5950
0.500 0.1064 0.00542 0.00066 0.0025 0.5650 0.6919
0.750 0.1300 0.00508 0.00065 0.0035 0.5571 0.7991
1.000 0.1543 0.00478 0.00068 0.0046 0.5487 0.8975
1.250 0.2010 0.00480 0.00077 0.0006 0.5386 0.9591
1.500 0.2383 0.00488 0.00081 -0.0014 0.5277 0.9742
1.750 0.2694 0.00497 0.00085 -0.0021 0.5163 0.9841
2.000 0.3066 0.00504 0.00088 -0.0041 0.5036 0.9888
2.250 0.3420 0.00513 0.00093 -0.0058 0.4897 0.9934
2.500 0.3782 0.00523 0.00097 -0.0077 0.4728 0.9965
2.750 0.4151 0.00538 0.00102 -0.0098 0.4421 0.9993
3.000 0.4447 0.00569 0.00112 -0.0105 0.3876 1.0000
3.250 0.4706 0.00621 0.00131 -0.0105 0.3069 1.0000
3.500 0.4958 0.00699 0.00162 -0.0105 0.1987 1.0000
3.750 0.5210 0.00762 0.00191 -0.0105 0.1222 1.0000
4.000 0.5465 0.00805 0.00216 -0.0103 0.0803 1.0000
4.250 0.5716 0.00858 0.00247 -0.0101 0.0344 1.0000
4.500 0.5968 0.00901 0.00279 -0.0098 0.0098 1.0000
4.750 0.6225 0.00923 0.00303 -0.0094 0.0086 1.0000
5.000 0.6481 0.00949 0.00330 -0.0091 0.0076 1.0000
5.250 0.6736 0.00978 0.00362 -0.0087 0.0068 1.0000
5.500 0.6988 0.01012 0.00401 -0.0083 0.0064 1.0000
5.750 0.7239 0.01042 0.00435 -0.0079 0.0062 1.0000
6.000 0.7489 0.01074 0.00469 -0.0075 0.0060 1.0000
6.250 0.7737 0.01110 0.00510 -0.0071 0.0058 1.0000
6.500 0.7982 0.01151 0.00555 -0.0066 0.0055 1.0000
6.750 0.8223 0.01197 0.00606 -0.0061 0.0052 1.0000
7.000 0.8460 0.01247 0.00662 -0.0056 0.0051 1.0000
7.250 0.8693 0.01303 0.00724 -0.0050 0.0049 1.0000
7.500 0.8924 0.01358 0.00783 -0.0044 0.0047 1.0000
7.750 0.9151 0.01415 0.00845 -0.0038 0.0045 1.0000
8.000 0.9373 0.01478 0.00912 -0.0032 0.0043 1.0000
8.250 0.9585 0.01552 0.00992 -0.0024 0.0042 1.0000
8.500 0.9785 0.01640 0.01089 -0.0016 0.0041 1.0000
8.750 0.9963 0.01760 0.01219 -0.0004 0.0040 1.0000
9.000 1.0120 0.01908 0.01379 0.0009 0.0039 1.0000
9.250 1.0306 0.02009 0.01489 0.0018 0.0038 1.0000
9.500 1.0508 0.02079 0.01567 0.0026 0.0038 1.0000
9.750 1.0676 0.02198 0.01698 0.0037 0.0038 1.0000
10.000 1.0857 0.02285 0.01795 0.0046 0.0037 1.0000
10.250 1.1021 0.02389 0.01912 0.0057 0.0036 1.0000
10.500 1.1157 0.02523 0.02060 0.0069 0.0036 1.0000
10.750 1.1292 0.02639 0.02189 0.0082 0.0035 1.0000
11.000 1.1383 0.02796 0.02361 0.0098 0.0034 1.0000
11.250 1.1412 0.02949 0.02528 0.0121 0.0034 1.0000
11.500 1.1428 0.03111 0.02704 0.0140 0.0033 1.0000
11.750 1.1418 0.03327 0.02937 0.0154 0.0033 1.0000
12.000 1.1401 0.03568 0.03195 0.0162 0.0032 1.0000
12.250 1.1383 0.03824 0.03466 0.0166 0.0032 1.0000
12.500 1.1326 0.04144 0.03804 0.0165 0.0031 1.0000
12.750 1.1231 0.04531 0.04209 0.0159 0.0031 1.0000
13.000 1.1161 0.04902 0.04597 0.0149 0.0031 1.0000
13.250 1.1034 0.05378 0.05090 0.0131 0.0030 1.0000
13.500 1.0920 0.05863 0.05591 0.0110 0.0030 1.0000
13.750 1.0750 0.06473 0.06216 0.0079 0.0030 1.0000
14.000 1.0567 0.07154 0.06914 0.0041 0.0030 1.0000
14.250 1.0364 0.07943 0.07717 -0.0006 0.0030 1.0000
14.500 1.0165 0.08819 0.08607 -0.0060 0.0030 1.0000
14.750 0.9925 0.09864 0.09666 -0.0122 0.0031 1.0000
15.000 0.9624 0.11160 0.10976 -0.0195 0.0031 1.0000
15.250 0.9286 0.12614 0.12441 -0.0269 0.0032 1.0000
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Polar data table (+)
Polar graphs
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