E423 (e423-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E423 (e423-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.23 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e423-il-1000000-n5.txt Download as CSV file: xf-e423-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E423
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
------ -------- --------- --------- -------- -------- --------
-8.250 0.2314 0.05498 0.05122 -0.1709 0.6286 0.0065
-8.000 0.2166 0.04963 0.04582 -0.1745 0.6250 0.0064
-7.750 0.2157 0.04478 0.04090 -0.1796 0.6210 0.0062
-7.500 0.2236 0.03686 0.03282 -0.1919 0.6171 0.0063
-7.250 0.2848 0.01694 0.01196 -0.2294 0.6140 0.0065
-7.000 0.3159 0.01471 0.00950 -0.2322 0.6111 0.0066
-6.750 0.3451 0.01374 0.00838 -0.2333 0.6079 0.0068
-6.500 0.3734 0.01311 0.00763 -0.2339 0.6043 0.0071
-6.250 0.4012 0.01262 0.00702 -0.2343 0.6006 0.0072
-6.000 0.4288 0.01221 0.00649 -0.2345 0.5969 0.0075
-5.750 0.4573 0.01184 0.00604 -0.2348 0.5944 0.0077
-5.500 0.4857 0.01151 0.00562 -0.2350 0.5918 0.0080
-5.250 0.5137 0.01123 0.00527 -0.2351 0.5889 0.0082
-5.000 0.5415 0.01097 0.00493 -0.2352 0.5858 0.0085
-4.750 0.5688 0.01073 0.00460 -0.2351 0.5825 0.0090
-4.250 0.6237 0.01036 0.00412 -0.2350 0.5772 0.0101
-4.000 0.6515 0.01021 0.00391 -0.2349 0.5749 0.0108
-3.750 0.6792 0.01004 0.00371 -0.2349 0.5723 0.0120
-3.500 0.7064 0.00992 0.00355 -0.2347 0.5694 0.0135
-3.250 0.7334 0.00981 0.00341 -0.2345 0.5665 0.0162
-3.000 0.7600 0.00973 0.00330 -0.2342 0.5636 0.0194
-2.750 0.7868 0.00966 0.00321 -0.2340 0.5611 0.0234
-2.500 0.8144 0.00957 0.00313 -0.2339 0.5592 0.0282
-2.250 0.8417 0.00950 0.00306 -0.2338 0.5567 0.0330
-2.000 0.8687 0.00944 0.00300 -0.2336 0.5541 0.0390
-1.750 0.8954 0.00940 0.00296 -0.2333 0.5515 0.0458
-1.500 0.9218 0.00938 0.00294 -0.2330 0.5489 0.0528
-1.250 0.9478 0.00937 0.00293 -0.2326 0.5460 0.0607
-1.000 0.9741 0.00938 0.00293 -0.2323 0.5435 0.0681
-0.750 1.0012 0.00936 0.00293 -0.2321 0.5414 0.0755
-0.500 1.0280 0.00936 0.00294 -0.2319 0.5392 0.0828
-0.250 1.0545 0.00937 0.00296 -0.2316 0.5366 0.0901
0.000 1.0806 0.00941 0.00300 -0.2312 0.5337 0.0971
0.250 1.1064 0.00946 0.00305 -0.2308 0.5309 0.1047
0.500 1.1317 0.00953 0.00311 -0.2303 0.5282 0.1117
0.750 1.1579 0.00957 0.00317 -0.2300 0.5259 0.1214
1.000 1.1843 0.00961 0.00323 -0.2297 0.5235 0.1279
1.250 1.2103 0.00966 0.00330 -0.2294 0.5208 0.1361
1.500 1.2358 0.00973 0.00337 -0.2289 0.5181 0.1422
1.750 1.2609 0.00981 0.00345 -0.2284 0.5151 0.1493
2.000 1.2852 0.00991 0.00355 -0.2278 0.5120 0.1567
2.250 1.3099 0.01001 0.00365 -0.2272 0.5092 0.1619
2.500 1.3358 0.01007 0.00374 -0.2269 0.5068 0.1706
2.750 1.3610 0.01015 0.00383 -0.2264 0.5039 0.1768
3.000 1.3858 0.01024 0.00394 -0.2259 0.5006 0.1846
3.250 1.4098 0.01035 0.00406 -0.2253 0.4972 0.1926
3.500 1.4331 0.01050 0.00420 -0.2245 0.4939 0.1998
3.750 1.4578 0.01058 0.00433 -0.2240 0.4911 0.2107
4.000 1.4822 0.01068 0.00446 -0.2234 0.4876 0.2200
4.250 1.5056 0.01081 0.00461 -0.2227 0.4837 0.2324
4.500 1.5277 0.01097 0.00478 -0.2217 0.4793 0.2470
4.750 1.5505 0.01112 0.00496 -0.2209 0.4753 0.2623
5.000 1.5741 0.01124 0.00513 -0.2203 0.4707 0.2836
5.250 1.5963 0.01141 0.00534 -0.2194 0.4655 0.3113
5.500 1.6170 0.01162 0.00558 -0.2182 0.4604 0.3450
5.750 1.6403 0.01173 0.00579 -0.2176 0.4559 0.3993
6.250 1.6803 0.01157 0.00647 -0.2153 0.4450 1.0000
6.500 1.7020 0.01179 0.00669 -0.2143 0.4401 1.0000
6.750 1.7225 0.01205 0.00694 -0.2132 0.4342 1.0000
7.000 1.7402 0.01241 0.00727 -0.2116 0.4276 1.0000
7.250 1.7604 0.01269 0.00755 -0.2104 0.4217 1.0000
7.500 1.7773 0.01308 0.00791 -0.2087 0.4142 1.0000
7.750 1.7959 0.01343 0.00826 -0.2074 0.4084 1.0000
8.000 1.8128 0.01384 0.00866 -0.2057 0.4005 1.0000
8.250 1.8282 0.01431 0.00912 -0.2038 0.3933 1.0000
8.500 1.8447 0.01476 0.00956 -0.2022 0.3855 1.0000
8.750 1.8578 0.01536 0.01013 -0.2000 0.3771 1.0000
9.000 1.8716 0.01595 0.01071 -0.1980 0.3680 1.0000
9.250 1.8838 0.01662 0.01137 -0.1958 0.3593 1.0000
9.500 1.8934 0.01745 0.01216 -0.1932 0.3486 1.0000
9.750 1.9048 0.01821 0.01292 -0.1911 0.3395 1.0000
10.000 1.9132 0.01916 0.01385 -0.1885 0.3301 1.0000
10.250 1.9202 0.02024 0.01490 -0.1859 0.3185 1.0000
10.500 1.9266 0.02139 0.01604 -0.1833 0.3076 1.0000
10.750 1.9300 0.02280 0.01741 -0.1804 0.2959 1.0000
11.000 1.9316 0.02440 0.01898 -0.1775 0.2837 1.0000
11.250 1.9353 0.02595 0.02052 -0.1750 0.2728 1.0000
11.500 1.9366 0.02774 0.02229 -0.1724 0.2616 1.0000
11.750 1.9365 0.02973 0.02426 -0.1698 0.2512 1.0000
12.000 1.9376 0.03173 0.02626 -0.1675 0.2414 1.0000
12.250 1.9368 0.03395 0.02847 -0.1652 0.2309 1.0000
12.500 1.9347 0.03639 0.03090 -0.1630 0.2215 1.0000
12.750 1.9339 0.03881 0.03332 -0.1610 0.2122 1.0000
13.000 1.9329 0.04132 0.03585 -0.1592 0.2042 1.0000
13.250 1.9287 0.04422 0.03874 -0.1573 0.1948 1.0000
13.500 1.9292 0.04673 0.04128 -0.1558 0.1878 1.0000
13.750 1.9252 0.04978 0.04432 -0.1542 0.1795 1.0000
14.000 1.9252 0.05247 0.04704 -0.1529 0.1721 1.0000
14.250 1.9201 0.05579 0.05036 -0.1516 0.1643 1.0000
14.500 1.9196 0.05865 0.05325 -0.1505 0.1576 1.0000
14.750 1.9164 0.06188 0.05649 -0.1494 0.1507 1.0000
15.000 1.9160 0.06485 0.05949 -0.1485 0.1448 1.0000
15.250 1.9120 0.06830 0.06295 -0.1476 0.1383 1.0000
15.500 1.9124 0.07123 0.06592 -0.1470 0.1328 1.0000
15.750 1.9091 0.07471 0.06941 -0.1463 0.1269 1.0000
16.000 1.9090 0.07779 0.07253 -0.1458 0.1215 1.0000
16.250 1.9057 0.08135 0.07611 -0.1453 0.1157 1.0000
16.500 1.9051 0.08456 0.07934 -0.1449 0.1109 1.0000
16.750 1.9030 0.08804 0.08286 -0.1446 0.1057 1.0000
17.000 1.9008 0.09152 0.08635 -0.1444 0.1006 1.0000
17.250 1.9002 0.09485 0.08974 -0.1443 0.0965 1.0000
17.500 1.8984 0.09833 0.09323 -0.1442 0.0917 1.0000
17.750 1.8969 0.10180 0.09675 -0.1443 0.0879 1.0000
18.000 1.8965 0.10511 0.10009 -0.1443 0.0837 1.0000
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Polar data table (+)
Polar graphs
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