E180 (8.59%) (e180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.71 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e180-il-1000000-n5.txt Download as CSV file: xf-e180-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E180 (8.59%)
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 -0.5267 0.09028 0.08852 0.0003 0.8712 0.0042
-7.000 -0.5917 0.02465 0.02091 -0.0253 0.7387 0.0030
-6.750 -0.5743 0.02119 0.01695 -0.0246 0.7305 0.0030
-6.500 -0.5533 0.01883 0.01417 -0.0239 0.7219 0.0030
-6.250 -0.5302 0.01710 0.01214 -0.0233 0.7143 0.0030
-6.000 -0.5058 0.01579 0.01056 -0.0229 0.7066 0.0031
-5.750 -0.4822 0.01410 0.00857 -0.0222 0.6997 0.0031
-5.500 -0.4584 0.01255 0.00673 -0.0216 0.6927 0.0034
-5.250 -0.4323 0.01186 0.00592 -0.0213 0.6863 0.0035
-5.000 -0.4057 0.01138 0.00535 -0.0210 0.6797 0.0038
-4.750 -0.3789 0.01096 0.00484 -0.0208 0.6736 0.0040
-4.500 -0.3520 0.01054 0.00433 -0.0206 0.6674 0.0043
-4.250 -0.3249 0.01017 0.00388 -0.0205 0.6619 0.0046
-4.000 -0.2977 0.00983 0.00346 -0.0203 0.6560 0.0049
-3.750 -0.2704 0.00953 0.00309 -0.0201 0.6504 0.0052
-3.500 -0.2428 0.00927 0.00278 -0.0200 0.6453 0.0054
-3.250 -0.2154 0.00900 0.00243 -0.0199 0.6397 0.0059
-3.000 -0.1879 0.00873 0.00207 -0.0197 0.6346 0.0069
-2.750 -0.1601 0.00852 0.00183 -0.0196 0.6296 0.0081
-2.500 -0.1323 0.00836 0.00163 -0.0196 0.6243 0.0096
-2.250 -0.1047 0.00814 0.00144 -0.0195 0.6195 0.0231
-2.000 -0.0772 0.00791 0.00129 -0.0194 0.6142 0.0461
-1.750 -0.0497 0.00769 0.00117 -0.0194 0.6092 0.0768
-1.500 -0.0220 0.00752 0.00107 -0.0194 0.6044 0.1043
-1.250 0.0054 0.00729 0.00097 -0.0193 0.5992 0.1510
-1.000 0.0325 0.00702 0.00089 -0.0193 0.5943 0.2184
-0.750 0.0601 0.00683 0.00083 -0.0193 0.5894 0.2671
-0.500 0.0871 0.00655 0.00078 -0.0192 0.5840 0.3457
-0.250 0.1145 0.00638 0.00074 -0.0192 0.5791 0.4035
0.000 0.1415 0.00613 0.00072 -0.0191 0.5738 0.4809
0.250 0.1682 0.00589 0.00070 -0.0190 0.5682 0.5612
0.500 0.1943 0.00561 0.00070 -0.0186 0.5624 0.6558
0.750 0.2194 0.00532 0.00070 -0.0180 0.5554 0.7553
1.000 0.2426 0.00501 0.00072 -0.0169 0.5484 0.8609
1.250 0.2796 0.00489 0.00079 -0.0186 0.5391 0.9552
1.500 0.3199 0.00495 0.00082 -0.0213 0.5282 0.9786
1.750 0.3551 0.00501 0.00084 -0.0229 0.5180 0.9879
2.250 0.4282 0.00516 0.00090 -0.0268 0.4947 0.9992
2.500 0.4575 0.00525 0.00094 -0.0272 0.4816 1.0000
2.750 0.4839 0.00535 0.00100 -0.0269 0.4666 1.0000
3.000 0.5099 0.00556 0.00107 -0.0266 0.4319 1.0000
3.250 0.5355 0.00588 0.00120 -0.0263 0.3847 1.0000
3.500 0.5605 0.00634 0.00139 -0.0261 0.3197 1.0000
3.750 0.5847 0.00696 0.00167 -0.0258 0.2426 1.0000
4.000 0.6094 0.00745 0.00193 -0.0254 0.1893 1.0000
4.250 0.6339 0.00796 0.00222 -0.0251 0.1365 1.0000
4.500 0.6583 0.00847 0.00251 -0.0248 0.0906 1.0000
4.750 0.6829 0.00891 0.00279 -0.0244 0.0573 1.0000
5.000 0.7075 0.00934 0.00310 -0.0240 0.0320 1.0000
5.250 0.7321 0.00976 0.00342 -0.0236 0.0144 1.0000
5.500 0.7577 0.01000 0.00369 -0.0232 0.0126 1.0000
5.750 0.7831 0.01026 0.00396 -0.0229 0.0116 1.0000
6.000 0.8084 0.01054 0.00426 -0.0225 0.0108 1.0000
6.250 0.8335 0.01086 0.00461 -0.0222 0.0100 1.0000
6.500 0.8584 0.01122 0.00501 -0.0217 0.0093 1.0000
6.750 0.8826 0.01168 0.00556 -0.0213 0.0086 1.0000
7.000 0.9067 0.01214 0.00608 -0.0208 0.0082 1.0000
7.250 0.9310 0.01255 0.00654 -0.0203 0.0081 1.0000
7.500 0.9550 0.01299 0.00703 -0.0199 0.0080 1.0000
7.750 0.9786 0.01346 0.00755 -0.0194 0.0079 1.0000
8.000 1.0020 0.01396 0.00810 -0.0189 0.0077 1.0000
8.250 1.0247 0.01453 0.00874 -0.0183 0.0075 1.0000
8.500 1.0470 0.01511 0.00940 -0.0177 0.0073 1.0000
8.750 1.0690 0.01571 0.01007 -0.0171 0.0071 1.0000
9.000 1.0909 0.01627 0.01069 -0.0164 0.0067 1.0000
9.250 1.1124 0.01686 0.01134 -0.0158 0.0064 1.0000
9.500 1.1334 0.01748 0.01202 -0.0151 0.0061 1.0000
9.750 1.1537 0.01814 0.01274 -0.0143 0.0059 1.0000
10.000 1.1740 0.01874 0.01338 -0.0136 0.0056 1.0000
10.250 1.1923 0.01951 0.01422 -0.0127 0.0053 1.0000
10.500 1.2019 0.02112 0.01596 -0.0108 0.0049 1.0000
10.750 1.2202 0.02174 0.01665 -0.0099 0.0048 1.0000
11.000 1.2366 0.02248 0.01747 -0.0088 0.0047 1.0000
11.250 1.2514 0.02326 0.01834 -0.0075 0.0046 1.0000
11.500 1.2609 0.02412 0.01929 -0.0054 0.0045 1.0000
11.750 1.2728 0.02479 0.02002 -0.0038 0.0043 1.0000
12.000 1.2800 0.02593 0.02126 -0.0021 0.0041 1.0000
12.250 1.2876 0.02717 0.02260 -0.0008 0.0040 1.0000
12.500 1.2998 0.02808 0.02358 0.0000 0.0037 1.0000
12.750 1.3118 0.02908 0.02463 0.0007 0.0035 1.0000
13.000 1.3267 0.02985 0.02543 0.0011 0.0033 1.0000
13.250 1.3375 0.03105 0.02668 0.0016 0.0032 1.0000
13.500 1.3478 0.03234 0.02803 0.0019 0.0031 1.0000
13.750 1.3538 0.03412 0.02988 0.0023 0.0030 1.0000
14.000 1.3587 0.03610 0.03194 0.0025 0.0028 1.0000
14.250 1.3598 0.03855 0.03449 0.0026 0.0027 1.0000
14.500 1.3616 0.04098 0.03704 0.0026 0.0027 1.0000
14.750 1.3642 0.04340 0.03956 0.0024 0.0025 1.0000
15.000 1.3578 0.04698 0.04329 0.0018 0.0026 1.0000
15.250 1.3562 0.05010 0.04652 0.0012 0.0025 1.0000
15.500 1.3532 0.05349 0.05003 0.0003 0.0024 1.0000
15.750 1.3435 0.05795 0.05463 -0.0011 0.0023 1.0000
16.000 1.3381 0.06199 0.05878 -0.0026 0.0023 1.0000
16.250 1.3260 0.06735 0.06430 -0.0048 0.0023 1.0000
16.500 1.3147 0.07281 0.06990 -0.0074 0.0023 1.0000
16.750 1.3076 0.07787 0.07506 -0.0098 0.0022 1.0000
17.000 1.2896 0.08510 0.08245 -0.0135 0.0022 1.0000
17.250 1.2776 0.09156 0.08901 -0.0169 0.0021 1.0000
17.500 1.2489 0.10173 0.09937 -0.0225 0.0022 1.0000
17.750 1.2199 0.11249 0.11027 -0.0285 0.0022 1.0000
18.000 1.1939 0.12306 0.12099 -0.0344 0.0022 1.0000
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Polar data table (+)
Polar graphs
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