E178 (8.69%) (e178-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 500,000 Max Cl/Cd: 95.14 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e178-il-500000-n5.txt Download as CSV file: xf-e178-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
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 -0.4765 0.08488 0.08281 -0.0125 1.0000 0.0059
-8.500 -0.4789 0.08031 0.07828 -0.0151 1.0000 0.0059
-8.250 -0.4843 0.07548 0.07350 -0.0179 1.0000 0.0060
-8.000 -0.4816 0.06813 0.06610 -0.0273 0.9067 0.0061
-7.750 -0.4870 0.06201 0.05981 -0.0325 0.8632 0.0061
-7.500 -0.4914 0.05345 0.05105 -0.0387 0.8371 0.0061
-7.250 -0.5182 0.03112 0.02778 -0.0454 0.8208 0.0061
-7.000 -0.5105 0.02353 0.01921 -0.0451 0.8069 0.0066
-6.750 -0.4894 0.02119 0.01641 -0.0446 0.7940 0.0069
-6.500 -0.4688 0.01856 0.01330 -0.0441 0.7823 0.0076
-6.250 -0.4438 0.01782 0.01239 -0.0439 0.7710 0.0080
-6.000 -0.4180 0.01734 0.01174 -0.0437 0.7604 0.0086
-5.750 -0.3921 0.01672 0.01095 -0.0435 0.7505 0.0095
-5.500 -0.3659 0.01612 0.01017 -0.0433 0.7411 0.0107
-5.250 -0.3395 0.01546 0.00932 -0.0431 0.7324 0.0117
-5.000 -0.3131 0.01476 0.00843 -0.0428 0.7241 0.0122
-4.750 -0.2863 0.01419 0.00770 -0.0426 0.7164 0.0126
-4.250 -0.2346 0.01225 0.00544 -0.0420 0.7016 0.0147
-3.750 -0.1809 0.01126 0.00423 -0.0415 0.6881 0.0165
-3.500 -0.1538 0.01089 0.00376 -0.0414 0.6817 0.0173
-3.250 -0.1264 0.01056 0.00334 -0.0412 0.6754 0.0181
-3.000 -0.0990 0.01028 0.00297 -0.0411 0.6693 0.0187
-2.750 -0.0714 0.01005 0.00266 -0.0410 0.6634 0.0194
-2.500 -0.0437 0.00987 0.00239 -0.0409 0.6574 0.0202
-2.250 -0.0159 0.00967 0.00210 -0.0408 0.6521 0.0209
-2.000 0.0120 0.00949 0.00186 -0.0407 0.6462 0.0227
-1.750 0.0397 0.00933 0.00168 -0.0406 0.6409 0.0285
-1.500 0.0672 0.00906 0.00153 -0.0406 0.6356 0.0656
-1.250 0.0947 0.00882 0.00141 -0.0406 0.6301 0.1112
-1.000 0.1219 0.00856 0.00132 -0.0406 0.6253 0.1723
-0.750 0.1495 0.00834 0.00126 -0.0406 0.6199 0.2264
-0.500 0.1766 0.00808 0.00121 -0.0406 0.6146 0.3034
-0.250 0.2021 0.00752 0.00120 -0.0405 0.6098 0.4778
0.000 0.2240 0.00673 0.00123 -0.0394 0.6046 0.7176
0.250 0.2452 0.00627 0.00127 -0.0375 0.5997 0.8794
0.500 0.2944 0.00619 0.00126 -0.0418 0.5943 0.9759
0.750 0.3348 0.00622 0.00123 -0.0446 0.5886 0.9978
1.000 0.3635 0.00628 0.00123 -0.0448 0.5834 1.0000
1.250 0.3902 0.00632 0.00125 -0.0445 0.5776 1.0000
1.500 0.4169 0.00640 0.00127 -0.0442 0.5716 1.0000
1.750 0.4437 0.00645 0.00130 -0.0440 0.5635 1.0000
2.000 0.4705 0.00652 0.00133 -0.0438 0.5553 1.0000
2.250 0.4974 0.00659 0.00139 -0.0435 0.5470 1.0000
2.500 0.5244 0.00667 0.00144 -0.0433 0.5380 1.0000
2.750 0.5513 0.00676 0.00150 -0.0431 0.5282 1.0000
3.000 0.5782 0.00686 0.00157 -0.0430 0.5175 1.0000
3.250 0.6051 0.00696 0.00167 -0.0428 0.5055 1.0000
3.500 0.6320 0.00707 0.00176 -0.0426 0.4928 1.0000
3.750 0.6589 0.00720 0.00187 -0.0424 0.4796 1.0000
4.000 0.6855 0.00735 0.00199 -0.0422 0.4633 1.0000
4.250 0.7121 0.00753 0.00212 -0.0420 0.4421 1.0000
4.500 0.7383 0.00776 0.00231 -0.0418 0.4165 1.0000
4.750 0.7639 0.00807 0.00251 -0.0416 0.3820 1.0000
5.000 0.7886 0.00852 0.00278 -0.0412 0.3343 1.0000
5.250 0.8127 0.00907 0.00312 -0.0409 0.2844 1.0000
5.500 0.8356 0.00980 0.00357 -0.0405 0.2232 1.0000
5.750 0.8571 0.01072 0.00412 -0.0399 0.1522 1.0000
6.000 0.8801 0.01139 0.00462 -0.0395 0.1103 1.0000
6.250 0.9026 0.01210 0.00512 -0.0390 0.0726 1.0000
6.500 0.9251 0.01278 0.00565 -0.0385 0.0433 1.0000
6.750 0.9477 0.01342 0.00619 -0.0379 0.0240 1.0000
7.000 0.9696 0.01414 0.00683 -0.0373 0.0100 1.0000
7.250 0.9921 0.01478 0.00750 -0.0366 0.0065 1.0000
7.500 1.0151 0.01532 0.00813 -0.0360 0.0060 1.0000
7.750 1.0374 0.01591 0.00881 -0.0353 0.0054 1.0000
8.000 1.0591 0.01653 0.00954 -0.0346 0.0048 1.0000
8.250 1.0799 0.01722 0.01031 -0.0338 0.0042 1.0000
8.500 1.0988 0.01812 0.01130 -0.0327 0.0038 1.0000
8.750 1.1154 0.01919 0.01251 -0.0314 0.0035 1.0000
9.000 1.1274 0.02068 0.01415 -0.0295 0.0033 1.0000
9.250 1.1436 0.02162 0.01519 -0.0282 0.0032 1.0000
9.500 1.1584 0.02264 0.01632 -0.0268 0.0031 1.0000
9.750 1.1705 0.02383 0.01763 -0.0250 0.0030 1.0000
10.000 1.1795 0.02505 0.01897 -0.0228 0.0029 1.0000
10.250 1.1850 0.02641 0.02049 -0.0203 0.0029 1.0000
10.500 1.1902 0.02791 0.02213 -0.0181 0.0028 1.0000
10.750 1.1952 0.02958 0.02394 -0.0162 0.0027 1.0000
11.000 1.1996 0.03140 0.02592 -0.0146 0.0027 1.0000
11.250 1.2024 0.03353 0.02822 -0.0131 0.0026 1.0000
11.500 1.2050 0.03573 0.03059 -0.0120 0.0026 1.0000
11.750 1.2060 0.03819 0.03323 -0.0110 0.0025 1.0000
12.000 1.2049 0.04098 0.03621 -0.0102 0.0025 1.0000
12.250 1.2021 0.04406 0.03949 -0.0098 0.0025 1.0000
12.500 1.1975 0.04744 0.04307 -0.0096 0.0025 1.0000
12.750 1.1909 0.05119 0.04702 -0.0099 0.0025 1.0000
13.000 1.1806 0.05561 0.05165 -0.0106 0.0024 1.0000
13.250 1.1706 0.06018 0.05641 -0.0118 0.0025 1.0000
13.500 1.1585 0.06528 0.06170 -0.0136 0.0025 1.0000
13.750 1.1440 0.07104 0.06765 -0.0159 0.0024 1.0000
14.000 1.1276 0.07761 0.07441 -0.0190 0.0024 1.0000
14.250 1.1120 0.08453 0.08150 -0.0227 0.0025 1.0000
14.500 1.0947 0.09240 0.08953 -0.0271 0.0025 1.0000
14.750 1.0781 0.10075 0.09804 -0.0321 0.0025 1.0000
15.000 1.0593 0.11031 0.10776 -0.0378 0.0025 1.0000
15.250 1.0400 0.12078 0.11836 -0.0440 0.0026 1.0000
15.500 1.0204 0.13200 0.12971 -0.0504 0.0026 1.0000
15.750 0.9951 0.14583 0.14365 -0.0579 0.0026 1.0000
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Polar data table (+)
Polar graphs
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