GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 482 AIRFOIL (goe482-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.59 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe482-il-1000000.txt Download as CSV file: xf-goe482-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 482 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 0.0800 0.12521 0.12237 -0.1184 0.8005 0.0192
-14.250 0.0823 0.12103 0.11815 -0.1200 0.7960 0.0197
-14.000 0.0801 0.11579 0.11292 -0.1220 0.7931 0.0210
-13.750 0.0953 0.11478 0.11189 -0.1229 0.7887 0.0213
-13.500 0.1071 0.11299 0.11009 -0.1239 0.7845 0.0218
-13.250 0.0935 0.10557 0.10264 -0.1266 0.7814 0.0241
-13.000 0.1068 0.10418 0.10123 -0.1274 0.7773 0.0244
-12.750 0.1205 0.10279 0.09984 -0.1283 0.7737 0.0246
-12.500 0.1336 0.10132 0.09836 -0.1291 0.7693 0.0250
-12.250 0.1225 0.09498 0.09200 -0.1318 0.7659 0.0279
-12.000 0.1392 0.09441 0.09139 -0.1322 0.7607 0.0281
-11.750 0.1522 0.09291 0.08990 -0.1329 0.7569 0.0284
-11.500 0.1678 0.09198 0.08897 -0.1335 0.7526 0.0288
-11.250 0.1550 0.08589 0.08287 -0.1363 0.7489 0.0320
-11.000 0.1718 0.08528 0.08223 -0.1364 0.7440 0.0323
-10.750 0.1942 0.08559 0.08253 -0.1363 0.7394 0.0328
-10.500 0.2084 0.08442 0.08136 -0.1369 0.7344 0.0337
-8.250 0.0665 0.02166 0.01768 -0.1890 0.6864 0.0449
-8.000 0.0916 0.01970 0.01543 -0.1910 0.6794 0.0454
-7.750 0.1181 0.01863 0.01413 -0.1920 0.6719 0.0460
-7.500 0.1457 0.01778 0.01310 -0.1928 0.6637 0.0463
-7.250 0.1730 0.01719 0.01232 -0.1932 0.6547 0.0466
-7.000 0.2007 0.01627 0.01121 -0.1939 0.6454 0.0469
-6.750 0.2270 0.01464 0.00936 -0.1948 0.6362 0.0475
-6.500 0.2547 0.01410 0.00873 -0.1951 0.6256 0.0479
-6.250 0.2825 0.01374 0.00828 -0.1952 0.6153 0.0483
-6.000 0.3100 0.01345 0.00788 -0.1953 0.6043 0.0487
-5.750 0.3382 0.01317 0.00752 -0.1954 0.5943 0.0491
-5.500 0.3660 0.01297 0.00724 -0.1955 0.5847 0.0497
-5.250 0.3940 0.01270 0.00687 -0.1956 0.5752 0.0501
-5.000 0.4220 0.01243 0.00650 -0.1957 0.5669 0.0505
-4.750 0.4501 0.01216 0.00615 -0.1958 0.5591 0.0510
-4.500 0.4780 0.01195 0.00585 -0.1958 0.5518 0.0514
-4.250 0.5066 0.01173 0.00557 -0.1959 0.5458 0.0519
-4.000 0.5346 0.01159 0.00535 -0.1959 0.5396 0.0523
-3.750 0.5627 0.01148 0.00517 -0.1959 0.5341 0.0527
-3.500 0.5914 0.01137 0.00503 -0.1960 0.5294 0.0530
-3.250 0.6196 0.01092 0.00451 -0.1963 0.5245 0.0538
-3.000 0.6474 0.01074 0.00429 -0.1963 0.5195 0.0547
-2.750 0.6761 0.01062 0.00416 -0.1965 0.5160 0.0555
-2.500 0.7048 0.01052 0.00405 -0.1966 0.5119 0.0563
-2.250 0.7330 0.01045 0.00395 -0.1967 0.5078 0.0570
-2.000 0.7607 0.01042 0.00387 -0.1966 0.5035 0.0578
-1.750 0.7888 0.01038 0.00380 -0.1966 0.4999 0.0587
-1.500 0.8176 0.01032 0.00373 -0.1968 0.4971 0.0595
-1.250 0.8459 0.01029 0.00369 -0.1968 0.4935 0.0601
-1.000 0.8740 0.01020 0.00356 -0.1969 0.4896 0.0613
-0.750 0.9013 0.01019 0.00350 -0.1969 0.4854 0.0630
-0.500 0.9293 0.01018 0.00349 -0.1969 0.4823 0.0647
-0.250 0.9578 0.01015 0.00347 -0.1970 0.4796 0.0664
0.000 0.9858 0.01016 0.00346 -0.1970 0.4763 0.0679
0.250 1.0133 0.01017 0.00345 -0.1970 0.4728 0.0701
0.500 1.0401 0.01021 0.00347 -0.1968 0.4689 0.0739
0.750 1.0672 0.01026 0.00351 -0.1967 0.4654 0.0777
1.000 1.0955 0.01020 0.00352 -0.1968 0.4625 0.0936
1.250 1.1233 0.01010 0.00360 -0.1970 0.4591 0.1661
1.500 1.1503 0.01007 0.00368 -0.1970 0.4555 0.2180
1.750 1.1764 0.01005 0.00384 -0.1969 0.4517 0.3136
2.000 1.2027 0.01013 0.00398 -0.1967 0.4484 0.3506
2.250 1.2299 0.01018 0.00407 -0.1966 0.4455 0.3692
2.500 1.2563 0.01027 0.00417 -0.1964 0.4420 0.3835
2.750 1.2817 0.01038 0.00429 -0.1960 0.4381 0.3989
3.000 1.3058 0.01055 0.00444 -0.1954 0.4337 0.4115
3.250 1.3318 0.01063 0.00454 -0.1952 0.4305 0.4218
3.500 1.3576 0.01070 0.00466 -0.1949 0.4269 0.4366
3.750 1.3822 0.01080 0.00480 -0.1944 0.4230 0.4589
4.000 1.4054 0.01090 0.00501 -0.1938 0.4188 0.5166
4.250 1.4288 0.01099 0.00524 -0.1931 0.4150 0.6001
4.500 1.4528 0.01099 0.00541 -0.1926 0.4117 0.6738
4.750 1.4722 0.01070 0.00563 -0.1910 0.4079 1.0000
5.000 1.4923 0.01092 0.00581 -0.1897 0.4037 1.0000
5.250 1.5109 0.01118 0.00603 -0.1882 0.3994 1.0000
5.500 1.5336 0.01134 0.00620 -0.1874 0.3961 1.0000
5.750 1.5543 0.01155 0.00640 -0.1862 0.3920 1.0000
6.000 1.5729 0.01184 0.00665 -0.1848 0.3876 1.0000
6.250 1.5901 0.01218 0.00696 -0.1831 0.3831 1.0000
6.500 1.6116 0.01239 0.00719 -0.1823 0.3800 1.0000
6.750 1.6314 0.01266 0.00746 -0.1811 0.3762 1.0000
7.000 1.6486 0.01303 0.00781 -0.1796 0.3720 1.0000
7.250 1.6637 0.01349 0.00824 -0.1777 0.3671 1.0000
7.500 1.6841 0.01376 0.00853 -0.1768 0.3635 1.0000
7.750 1.7015 0.01415 0.00892 -0.1754 0.3585 1.0000
8.000 1.7147 0.01473 0.00946 -0.1735 0.3530 1.0000
8.250 1.7325 0.01515 0.00989 -0.1723 0.3491 1.0000
8.500 1.7499 0.01559 0.01034 -0.1711 0.3451 1.0000
8.750 1.7643 0.01619 0.01093 -0.1695 0.3403 1.0000
9.000 1.7759 0.01694 0.01166 -0.1676 0.3351 1.0000
9.250 1.7940 0.01740 0.01216 -0.1666 0.3312 1.0000
9.500 1.8088 0.01805 0.01281 -0.1652 0.3269 1.0000
9.750 1.8199 0.01892 0.01367 -0.1635 0.3222 1.0000
10.000 1.8338 0.01968 0.01444 -0.1622 0.3179 1.0000
10.250 1.8494 0.02035 0.01514 -0.1611 0.3141 1.0000
10.500 1.8615 0.02125 0.01605 -0.1597 0.3097 1.0000
10.750 1.8708 0.02236 0.01715 -0.1580 0.3051 1.0000
11.000 1.8851 0.02317 0.01800 -0.1569 0.3010 1.0000
11.250 1.8973 0.02413 0.01898 -0.1557 0.2960 1.0000
11.500 1.9037 0.02551 0.02034 -0.1539 0.2900 1.0000
11.750 1.9154 0.02657 0.02143 -0.1527 0.2852 1.0000
12.000 1.9239 0.02786 0.02273 -0.1513 0.2784 1.0000
12.250 1.9284 0.02949 0.02436 -0.1496 0.2719 1.0000
12.500 1.9355 0.03098 0.02585 -0.1483 0.2640 1.0000
12.750 1.9372 0.03294 0.02780 -0.1466 0.2549 1.0000
13.000 1.9329 0.03548 0.03029 -0.1446 0.2425 1.0000
13.250 1.9253 0.03843 0.03319 -0.1425 0.2275 1.0000
13.500 1.9091 0.04233 0.03701 -0.1403 0.2073 1.0000
13.750 1.8868 0.04709 0.04169 -0.1381 0.1882 1.0000
14.000 1.8636 0.05224 0.04677 -0.1362 0.1702 1.0000
14.250 1.8432 0.05735 0.05186 -0.1349 0.1557 1.0000
14.500 1.8210 0.06296 0.05744 -0.1339 0.1413 1.0000
14.750 1.7990 0.06875 0.06321 -0.1333 0.1269 1.0000
15.000 1.7728 0.07537 0.06978 -0.1329 0.1114 1.0000
15.250 1.7398 0.08315 0.07752 -0.1330 0.0913 1.0000
15.500 1.7080 0.09109 0.08541 -0.1334 0.0717 1.0000
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