GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 405 AIRFOIL (goe405-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.24 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe405-il-1000000-n5.txt Download as CSV file: xf-goe405-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 405 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2404 0.05846 0.05640 -0.1312 0.9314 0.0078
-11.000 -0.4029 0.02860 0.02562 -0.1524 0.8812 0.0068
-10.750 -0.4094 0.02058 0.01710 -0.1538 0.8714 0.0068
-10.500 -0.3937 0.01827 0.01453 -0.1535 0.8632 0.0072
-10.250 -0.3737 0.01700 0.01307 -0.1530 0.8558 0.0074
-10.000 -0.3524 0.01601 0.01192 -0.1525 0.8476 0.0077
-9.750 -0.3300 0.01520 0.01097 -0.1520 0.8401 0.0081
-9.500 -0.3070 0.01453 0.01015 -0.1514 0.8315 0.0084
-9.250 -0.2835 0.01392 0.00940 -0.1509 0.8225 0.0088
-9.000 -0.2597 0.01341 0.00874 -0.1504 0.8134 0.0091
-8.750 -0.2358 0.01285 0.00806 -0.1499 0.8039 0.0098
-8.500 -0.2116 0.01237 0.00748 -0.1494 0.7950 0.0106
-8.000 -0.1620 0.01165 0.00654 -0.1484 0.7763 0.0121
-7.750 -0.1369 0.01132 0.00611 -0.1479 0.7683 0.0131
-7.500 -0.1112 0.01106 0.00580 -0.1475 0.7603 0.0144
-7.250 -0.0855 0.01085 0.00551 -0.1472 0.7530 0.0156
-7.000 -0.0594 0.01065 0.00523 -0.1468 0.7454 0.0165
-6.750 -0.0336 0.01047 0.00499 -0.1464 0.7375 0.0178
-6.500 -0.0074 0.01038 0.00486 -0.1461 0.7285 0.0192
-6.250 0.0188 0.01029 0.00470 -0.1457 0.7198 0.0204
-6.000 0.0448 0.01019 0.00452 -0.1453 0.7111 0.0213
-5.750 0.0714 0.01010 0.00436 -0.1450 0.7035 0.0218
-5.500 0.0972 0.00984 0.00403 -0.1446 0.6971 0.0230
-5.250 0.1236 0.00966 0.00381 -0.1444 0.6921 0.0241
-5.000 0.1505 0.00951 0.00362 -0.1442 0.6869 0.0250
-4.750 0.1771 0.00941 0.00348 -0.1439 0.6816 0.0261
-4.500 0.2037 0.00929 0.00330 -0.1436 0.6767 0.0270
-4.250 0.2307 0.00917 0.00313 -0.1434 0.6716 0.0277
-4.000 0.2572 0.00905 0.00296 -0.1431 0.6663 0.0282
-3.750 0.2839 0.00896 0.00282 -0.1429 0.6612 0.0287
-3.500 0.3108 0.00885 0.00266 -0.1427 0.6559 0.0289
-3.250 0.3369 0.00868 0.00243 -0.1423 0.6504 0.0296
-3.000 0.3634 0.00852 0.00222 -0.1420 0.6455 0.0307
-2.750 0.3900 0.00840 0.00206 -0.1417 0.6396 0.0322
-2.500 0.4160 0.00833 0.00195 -0.1413 0.6332 0.0337
-2.250 0.4428 0.00825 0.00185 -0.1411 0.6275 0.0352
-2.000 0.4693 0.00820 0.00176 -0.1408 0.6212 0.0366
-1.750 0.4955 0.00817 0.00169 -0.1404 0.6148 0.0380
-1.500 0.5217 0.00812 0.00162 -0.1401 0.6071 0.0429
-1.250 0.5474 0.00806 0.00157 -0.1397 0.5999 0.0539
-1.000 0.5729 0.00794 0.00153 -0.1392 0.5920 0.0830
-0.750 0.5984 0.00793 0.00152 -0.1388 0.5839 0.1003
-0.500 0.6238 0.00793 0.00153 -0.1383 0.5740 0.1130
-0.250 0.6494 0.00795 0.00154 -0.1379 0.5644 0.1235
0.000 0.6744 0.00800 0.00156 -0.1373 0.5536 0.1349
0.250 0.6991 0.00807 0.00160 -0.1367 0.5419 0.1469
0.500 0.7240 0.00812 0.00165 -0.1362 0.5299 0.1566
0.750 0.7486 0.00822 0.00169 -0.1356 0.5168 0.1632
1.000 0.7724 0.00833 0.00176 -0.1348 0.5023 0.1725
1.250 0.7958 0.00847 0.00184 -0.1340 0.4860 0.1813
1.500 0.8188 0.00862 0.00194 -0.1331 0.4696 0.1900
1.750 0.8423 0.00876 0.00202 -0.1323 0.4562 0.1952
2.000 0.8660 0.00888 0.00212 -0.1316 0.4456 0.2033
2.500 0.9136 0.00910 0.00231 -0.1301 0.4278 0.2186
2.750 0.9372 0.00923 0.00241 -0.1294 0.4207 0.2261
3.000 0.9612 0.00931 0.00252 -0.1287 0.4139 0.2373
3.250 0.9845 0.00942 0.00263 -0.1279 0.4073 0.2504
3.500 1.0077 0.00952 0.00275 -0.1271 0.4010 0.2666
3.750 1.0308 0.00960 0.00287 -0.1263 0.3948 0.2890
4.000 1.0503 0.00950 0.00305 -0.1249 0.3892 0.4444
4.500 1.1221 0.00891 0.00359 -0.1293 0.3769 1.0000
4.750 1.1429 0.00907 0.00373 -0.1280 0.3720 1.0000
5.000 1.1639 0.00922 0.00386 -0.1267 0.3658 1.0000
5.250 1.1833 0.00942 0.00404 -0.1252 0.3589 1.0000
5.500 1.2038 0.00960 0.00420 -0.1238 0.3509 1.0000
5.750 1.2220 0.00986 0.00441 -0.1221 0.3387 1.0000
6.000 1.2409 0.01011 0.00462 -0.1206 0.3293 1.0000
6.250 1.2594 0.01038 0.00486 -0.1190 0.3169 1.0000
6.500 1.2739 0.01082 0.00518 -0.1167 0.2957 1.0000
6.750 1.2903 0.01120 0.00549 -0.1148 0.2803 1.0000
7.000 1.3012 0.01182 0.00595 -0.1120 0.2531 1.0000
7.250 1.3134 0.01241 0.00642 -0.1095 0.2301 1.0000
7.500 1.3251 0.01304 0.00694 -0.1069 0.2094 1.0000
7.750 1.3377 0.01364 0.00745 -0.1046 0.1907 1.0000
8.000 1.3460 0.01448 0.00814 -0.1017 0.1644 1.0000
8.250 1.3338 0.01641 0.00965 -0.0959 0.0962 1.0000
8.500 1.3235 0.01840 0.01136 -0.0907 0.0355 1.0000
8.750 1.3305 0.01950 0.01237 -0.0881 0.0166 1.0000
9.000 1.3452 0.02017 0.01307 -0.0866 0.0139 1.0000
9.250 1.3591 0.02090 0.01383 -0.0851 0.0124 1.0000
9.500 1.3719 0.02172 0.01468 -0.0834 0.0108 1.0000
9.750 1.3858 0.02249 0.01548 -0.0820 0.0100 1.0000
10.000 1.3991 0.02333 0.01635 -0.0806 0.0092 1.0000
10.250 1.4115 0.02424 0.01729 -0.0792 0.0086 1.0000
10.500 1.4225 0.02526 0.01836 -0.0777 0.0079 1.0000
10.750 1.4324 0.02641 0.01955 -0.0761 0.0075 1.0000
11.000 1.4445 0.02741 0.02060 -0.0748 0.0071 1.0000
11.250 1.4550 0.02857 0.02180 -0.0735 0.0067 1.0000
11.500 1.4648 0.02980 0.02308 -0.0722 0.0065 1.0000
11.750 1.4736 0.03115 0.02448 -0.0709 0.0061 1.0000
12.000 1.4821 0.03257 0.02594 -0.0696 0.0058 1.0000
12.500 1.4948 0.03590 0.02939 -0.0671 0.0052 1.0000
12.750 1.5011 0.03763 0.03119 -0.0660 0.0051 1.0000
13.000 1.5070 0.03945 0.03308 -0.0649 0.0049 1.0000
13.250 1.5121 0.04139 0.03508 -0.0639 0.0047 1.0000
13.500 1.5164 0.04344 0.03721 -0.0630 0.0045 1.0000
13.750 1.5209 0.04550 0.03933 -0.0621 0.0044 1.0000
14.000 1.5226 0.04791 0.04182 -0.0612 0.0043 1.0000
14.250 1.5256 0.05025 0.04421 -0.0605 0.0041 1.0000
14.500 1.5262 0.05288 0.04692 -0.0599 0.0040 1.0000
14.750 1.5251 0.05576 0.04989 -0.0592 0.0039 1.0000
15.000 1.5222 0.05891 0.05312 -0.0587 0.0038 1.0000
15.250 1.5174 0.06238 0.05669 -0.0583 0.0037 1.0000
15.500 1.5104 0.06624 0.06064 -0.0580 0.0036 1.0000
15.750 1.5085 0.06949 0.06398 -0.0579 0.0035 1.0000
16.000 1.5048 0.07303 0.06761 -0.0579 0.0035 1.0000
16.250 1.5005 0.07674 0.07142 -0.0580 0.0034 1.0000
16.500 1.4946 0.08075 0.07552 -0.0582 0.0034 1.0000
16.750 1.4896 0.08469 0.07955 -0.0586 0.0033 1.0000
17.000 1.4837 0.08880 0.08376 -0.0591 0.0033 1.0000
17.250 1.4817 0.09239 0.08743 -0.0596 0.0031 1.0000
17.500 1.4727 0.09712 0.09226 -0.0605 0.0031 1.0000
17.750 1.4654 0.10164 0.09687 -0.0614 0.0031 1.0000
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