E178 (8.69%) (e178-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 50,000 Max Cl/Cd: 36.66 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e178-il-50000.txt Download as CSV file: xf-e178-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4615 0.11958 0.11305 -0.0010 1.0000 0.1796
-9.250 -0.4489 0.11495 0.10841 -0.0008 1.0000 0.1884
-9.000 -0.4587 0.11377 0.10734 -0.0038 1.0000 0.1945
-8.750 -0.4435 0.10901 0.10259 -0.0031 1.0000 0.2065
-8.500 -0.4346 0.10508 0.09871 -0.0033 1.0000 0.2161
-8.250 -0.4530 0.10465 0.09845 -0.0068 1.0000 0.2230
-8.000 -0.4365 0.09995 0.09376 -0.0059 1.0000 0.2360
-7.750 -0.4238 0.09573 0.08957 -0.0055 1.0000 0.2477
-7.500 -0.4172 0.09225 0.08616 -0.0056 1.0000 0.2592
-7.250 -0.4133 0.08912 0.08311 -0.0059 1.0000 0.2718
-7.000 -0.4097 0.08607 0.08015 -0.0059 1.0000 0.2856
-6.750 -0.4063 0.08310 0.07726 -0.0056 1.0000 0.3013
-6.500 -0.4085 0.08068 0.07497 -0.0058 1.0000 0.3193
-6.000 -0.4076 0.07557 0.07007 -0.0055 1.0000 0.3636
-5.750 -0.3824 0.07139 0.06590 -0.0004 1.0000 0.3987
-5.500 -0.3861 0.06954 0.06419 0.0018 1.0000 0.4333
-4.500 -0.3726 0.04611 0.03930 -0.0360 1.0000 0.1523
-4.250 -0.3588 0.04218 0.03497 -0.0360 1.0000 0.1413
-4.000 -0.3428 0.03916 0.03160 -0.0355 1.0000 0.1343
-3.750 -0.3211 0.03585 0.02732 -0.0354 1.0000 0.1251
-3.500 -0.3017 0.03333 0.02446 -0.0348 1.0000 0.1236
-3.250 -0.2802 0.03114 0.02176 -0.0342 1.0000 0.1234
-3.000 -0.2574 0.02941 0.01945 -0.0334 1.0000 0.1255
-2.750 -0.2369 0.02799 0.01801 -0.0329 1.0000 0.1356
-2.500 -0.2145 0.02664 0.01646 -0.0322 1.0000 0.1458
-2.250 -0.1909 0.02540 0.01504 -0.0315 1.0000 0.1580
-2.000 -0.1675 0.02423 0.01388 -0.0307 1.0000 0.1916
-1.750 -0.1418 0.02229 0.01280 -0.0306 1.0000 0.3280
-1.500 -0.1081 0.01927 0.01177 -0.0296 1.0000 1.0000
-1.250 -0.0826 0.01974 0.01166 -0.0304 0.9974 1.0000
-1.000 -0.0409 0.02046 0.01183 -0.0343 0.9877 1.0000
-0.750 -0.0007 0.02121 0.01214 -0.0379 0.9784 1.0000
-0.500 0.0418 0.02203 0.01256 -0.0418 0.9693 1.0000
-0.250 0.0750 0.02269 0.01293 -0.0440 0.9595 1.0000
0.000 0.1094 0.02343 0.01343 -0.0464 0.9504 1.0000
0.250 0.1495 0.02426 0.01401 -0.0498 0.9414 1.0000
0.500 0.1769 0.02496 0.01455 -0.0509 0.9319 1.0000
0.750 0.2076 0.02574 0.01519 -0.0525 0.9229 1.0000
1.000 0.2459 0.02662 0.01594 -0.0555 0.9144 1.0000
1.250 0.2680 0.02737 0.01660 -0.0556 0.9047 1.0000
1.500 0.2960 0.02823 0.01738 -0.0567 0.8958 1.0000
1.750 0.3323 0.02914 0.01825 -0.0591 0.8868 1.0000
2.000 0.3509 0.03001 0.01908 -0.0587 0.8771 1.0000
2.250 0.3768 0.03095 0.02002 -0.0594 0.8677 1.0000
2.500 0.4122 0.03192 0.02100 -0.0616 0.8582 1.0000
2.750 0.4318 0.03289 0.02197 -0.0613 0.8477 1.0000
3.000 0.4538 0.03391 0.02301 -0.0613 0.8368 1.0000
3.250 0.4800 0.03494 0.02414 -0.0620 0.8258 1.0000
3.500 0.5090 0.03596 0.02523 -0.0629 0.8139 1.0000
3.750 0.5392 0.03697 0.02634 -0.0638 0.8015 1.0000
4.000 0.5684 0.03796 0.02744 -0.0645 0.7883 1.0000
4.250 0.5944 0.03897 0.02863 -0.0646 0.7741 1.0000
4.500 0.6172 0.04001 0.02980 -0.0643 0.7589 1.0000
4.750 0.6399 0.04103 0.03097 -0.0639 0.7424 1.0000
5.000 0.6702 0.04182 0.03195 -0.0640 0.7245 1.0000
5.250 0.7198 0.04179 0.03230 -0.0651 0.7060 1.0000
5.500 0.7343 0.04282 0.03348 -0.0632 0.6848 1.0000
5.750 0.7871 0.04164 0.03269 -0.0626 0.6641 1.0000
6.000 0.8102 0.04174 0.03303 -0.0602 0.6396 1.0000
6.250 0.8455 0.04053 0.03221 -0.0574 0.6142 1.0000
6.500 0.8871 0.03799 0.03005 -0.0534 0.5865 1.0000
6.750 0.9334 0.03387 0.02629 -0.0482 0.5543 1.0000
7.000 0.9677 0.03031 0.02296 -0.0427 0.5101 1.0000
7.250 0.9913 0.02751 0.02022 -0.0369 0.4397 1.0000
7.500 1.0000 0.02728 0.01924 -0.0315 0.3359 1.0000
7.750 1.0025 0.02972 0.02065 -0.0276 0.2504 1.0000
8.000 1.0084 0.03270 0.02311 -0.0247 0.1883 1.0000
8.250 1.0223 0.03590 0.02569 -0.0227 0.1419 1.0000
8.500 1.0425 0.03911 0.02884 -0.0211 0.1135 1.0000
8.750 1.0646 0.04246 0.03239 -0.0199 0.0978 1.0000
9.000 1.0880 0.04631 0.03628 -0.0191 0.0886 1.0000
9.250 1.0990 0.04960 0.04019 -0.0173 0.0830 1.0000
9.500 1.1158 0.05334 0.04415 -0.0164 0.0785 1.0000
9.750 1.1278 0.05827 0.04937 -0.0154 0.0772 1.0000
10.000 1.1317 0.06294 0.05448 -0.0139 0.0771 1.0000
10.250 1.1269 0.06691 0.05895 -0.0121 0.0778 1.0000
10.500 1.1013 0.07089 0.06354 -0.0100 0.0795 1.0000
10.750 1.0748 0.07505 0.06803 -0.0086 0.0810 1.0000
11.000 1.0482 0.07973 0.07292 -0.0087 0.0824 1.0000
11.250 1.0201 0.08531 0.07860 -0.0106 0.0837 1.0000
11.500 0.9933 0.09181 0.08520 -0.0139 0.0852 1.0000
11.750 0.9707 0.09896 0.09241 -0.0179 0.0868 1.0000
12.000 0.9566 0.10605 0.09952 -0.0213 0.0883 1.0000
12.250 0.9554 0.11237 0.10584 -0.0228 0.0895 1.0000
12.500 0.7451 0.13189 0.12566 -0.0356 0.1265 1.0000
12.750 0.7459 0.13722 0.13101 -0.0368 0.1282 1.0000
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Polar data table (+)
Polar graphs
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