E180 (8.59%) (e180-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 500,000 Max Cl/Cd: 82.27 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e180-il-500000-n5.txt Download as CSV file: xf-e180-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5208 0.09016 0.08810 0.0009 1.0000 0.0085
-8.500 -0.5206 0.08604 0.08401 -0.0013 1.0000 0.0080
-8.250 -0.5230 0.08143 0.07943 -0.0041 1.0000 0.0076
-7.750 -0.5478 0.06457 0.06238 -0.0176 0.8639 0.0058
-7.500 -0.5434 0.05951 0.05717 -0.0209 0.8400 0.0057
-7.250 -0.5389 0.05398 0.05144 -0.0238 0.8214 0.0055
-7.000 -0.5375 0.04608 0.04325 -0.0267 0.8066 0.0053
-6.750 -0.5335 0.03739 0.03413 -0.0280 0.7946 0.0051
-6.500 -0.5268 0.02922 0.02528 -0.0276 0.7842 0.0049
-6.250 -0.5116 0.02434 0.01976 -0.0268 0.7739 0.0049
-6.000 -0.4917 0.02112 0.01598 -0.0259 0.7639 0.0049
-5.750 -0.4690 0.01891 0.01334 -0.0251 0.7546 0.0050
-5.500 -0.4449 0.01723 0.01129 -0.0245 0.7460 0.0051
-5.250 -0.4198 0.01597 0.00975 -0.0240 0.7372 0.0053
-5.000 -0.3940 0.01501 0.00857 -0.0235 0.7293 0.0055
-4.750 -0.3689 0.01386 0.00718 -0.0230 0.7215 0.0057
-4.500 -0.3437 0.01278 0.00592 -0.0225 0.7142 0.0062
-4.250 -0.3176 0.01214 0.00516 -0.0221 0.7071 0.0066
-4.000 -0.2909 0.01173 0.00467 -0.0219 0.7003 0.0074
-3.750 -0.2640 0.01136 0.00421 -0.0217 0.6936 0.0083
-3.500 -0.2370 0.01093 0.00366 -0.0214 0.6873 0.0088
-3.250 -0.2099 0.01057 0.00320 -0.0212 0.6809 0.0094
-3.000 -0.1826 0.01022 0.00274 -0.0210 0.6751 0.0109
-2.750 -0.1552 0.00994 0.00242 -0.0208 0.6689 0.0152
-2.500 -0.1283 0.00960 0.00215 -0.0206 0.6635 0.0382
-2.250 -0.1012 0.00929 0.00195 -0.0205 0.6576 0.0704
-2.000 -0.0739 0.00906 0.00178 -0.0205 0.6520 0.1019
-1.750 -0.0471 0.00873 0.00164 -0.0204 0.6469 0.1602
-1.500 -0.0203 0.00838 0.00152 -0.0203 0.6412 0.2329
-1.250 0.0066 0.00814 0.00141 -0.0202 0.6360 0.2914
-1.000 0.0331 0.00778 0.00133 -0.0201 0.6307 0.3822
-0.750 0.0593 0.00745 0.00127 -0.0199 0.6252 0.4741
-0.500 0.0848 0.00710 0.00122 -0.0195 0.6203 0.5761
-0.250 0.1092 0.00670 0.00119 -0.0188 0.6149 0.6883
0.000 0.1319 0.00630 0.00118 -0.0174 0.6097 0.8091
0.250 0.1698 0.00607 0.00124 -0.0190 0.6044 0.9321
0.500 0.2168 0.00610 0.00123 -0.0231 0.5985 0.9729
0.750 0.2551 0.00615 0.00122 -0.0253 0.5929 0.9884
1.000 0.2936 0.00618 0.00121 -0.0277 0.5864 0.9977
1.500 0.3510 0.00626 0.00122 -0.0281 0.5722 1.0000
1.750 0.3774 0.00633 0.00124 -0.0277 0.5641 1.0000
2.000 0.4038 0.00638 0.00126 -0.0274 0.5545 1.0000
2.250 0.4303 0.00645 0.00131 -0.0271 0.5448 1.0000
2.500 0.4568 0.00653 0.00136 -0.0268 0.5353 1.0000
2.750 0.4832 0.00661 0.00141 -0.0265 0.5246 1.0000
3.000 0.5097 0.00670 0.00148 -0.0263 0.5127 1.0000
3.250 0.5362 0.00680 0.00157 -0.0260 0.4990 1.0000
3.500 0.5625 0.00693 0.00166 -0.0257 0.4814 1.0000
3.750 0.5882 0.00715 0.00175 -0.0254 0.4446 1.0000
4.000 0.6131 0.00755 0.00191 -0.0250 0.3873 1.0000
4.250 0.6369 0.00817 0.00221 -0.0247 0.3097 1.0000
4.500 0.6609 0.00878 0.00255 -0.0244 0.2476 1.0000
4.750 0.6852 0.00930 0.00288 -0.0240 0.2002 1.0000
5.000 0.7086 0.00998 0.00328 -0.0237 0.1419 1.0000
5.250 0.7316 0.01071 0.00373 -0.0233 0.0865 1.0000
5.500 0.7553 0.01129 0.00416 -0.0229 0.0527 1.0000
5.750 0.7789 0.01188 0.00462 -0.0224 0.0265 1.0000
6.000 0.8030 0.01237 0.00507 -0.0220 0.0167 1.0000
6.250 0.8275 0.01279 0.00551 -0.0215 0.0142 1.0000
6.500 0.8520 0.01320 0.00599 -0.0211 0.0132 1.0000
6.750 0.8762 0.01364 0.00650 -0.0206 0.0127 1.0000
7.000 0.9000 0.01412 0.00709 -0.0201 0.0123 1.0000
7.250 0.9233 0.01468 0.00773 -0.0196 0.0118 1.0000
7.500 0.9461 0.01526 0.00838 -0.0190 0.0111 1.0000
7.750 0.9683 0.01588 0.00907 -0.0184 0.0106 1.0000
8.000 0.9898 0.01657 0.00985 -0.0176 0.0102 1.0000
8.250 1.0103 0.01737 0.01073 -0.0168 0.0099 1.0000
8.500 1.0299 0.01823 0.01167 -0.0159 0.0096 1.0000
8.750 1.0477 0.01924 0.01280 -0.0148 0.0092 1.0000
9.000 1.0634 0.02050 0.01416 -0.0135 0.0088 1.0000
9.250 1.0747 0.02232 0.01614 -0.0117 0.0084 1.0000
9.500 1.0922 0.02326 0.01718 -0.0107 0.0081 1.0000
9.750 1.1096 0.02413 0.01817 -0.0096 0.0079 1.0000
10.000 1.1254 0.02514 0.01929 -0.0085 0.0076 1.0000
10.250 1.1393 0.02632 0.02061 -0.0071 0.0073 1.0000
10.500 1.1504 0.02761 0.02207 -0.0054 0.0071 1.0000
10.750 1.1584 0.02890 0.02349 -0.0034 0.0068 1.0000
11.000 1.1655 0.03021 0.02492 -0.0017 0.0065 1.0000
11.250 1.1724 0.03159 0.02642 -0.0002 0.0062 1.0000
11.500 1.1781 0.03315 0.02811 0.0010 0.0060 1.0000
11.750 1.1858 0.03440 0.02944 0.0017 0.0057 1.0000
12.000 1.1897 0.03630 0.03145 0.0024 0.0055 1.0000
12.250 1.1940 0.03814 0.03338 0.0028 0.0053 1.0000
12.500 1.1945 0.04057 0.03592 0.0031 0.0052 1.0000
12.750 1.1886 0.04392 0.03945 0.0033 0.0050 1.0000
13.000 1.1828 0.04740 0.04311 0.0030 0.0048 1.0000
13.250 1.1798 0.05066 0.04655 0.0024 0.0048 1.0000
13.500 1.1740 0.05441 0.05048 0.0015 0.0047 1.0000
13.750 1.1614 0.05932 0.05558 0.0001 0.0047 1.0000
14.000 1.1549 0.06359 0.06003 -0.0017 0.0046 1.0000
14.250 1.1428 0.06892 0.06554 -0.0040 0.0045 1.0000
14.500 1.1274 0.07516 0.07195 -0.0071 0.0045 1.0000
14.750 1.1142 0.08162 0.07859 -0.0106 0.0044 1.0000
15.000 1.0925 0.09011 0.08724 -0.0154 0.0045 1.0000
15.250 1.0770 0.09812 0.09541 -0.0202 0.0044 1.0000
15.500 1.0567 0.10767 0.10511 -0.0258 0.0045 1.0000
15.750 1.0320 0.11906 0.11665 -0.0325 0.0045 1.0000
16.000 1.0083 0.13055 0.12824 -0.0389 0.0047 1.0000
16.250 0.9763 0.14531 0.14309 -0.0469 0.0048 1.0000
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Polar data table (+)
Polar graphs
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