GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 421 AIRFOIL (goe421-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.22 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe421-il-1000000-n5.txt Download as CSV file: xf-goe421-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 421 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
------ -------- --------- --------- -------- -------- --------
-19.250 -0.2923 0.13058 0.12818 -0.1201 0.9506 0.0195
-19.000 -0.2977 0.12584 0.12344 -0.1227 0.9481 0.0202
-18.750 -0.3244 0.11761 0.11514 -0.1268 0.9457 0.0211
-18.500 -0.3485 0.11011 0.10754 -0.1307 0.9432 0.0218
-18.250 -0.3680 0.10358 0.10091 -0.1342 0.9405 0.0224
-18.000 -0.3812 0.09803 0.09527 -0.1374 0.9380 0.0228
-17.750 -0.3951 0.09251 0.08970 -0.1406 0.9347 0.0232
-17.500 -0.4103 0.08693 0.08406 -0.1438 0.9311 0.0236
-17.250 -0.4243 0.08169 0.07875 -0.1469 0.9273 0.0240
-17.000 -0.4348 0.07698 0.07397 -0.1497 0.9235 0.0244
-16.750 -0.4433 0.07256 0.06950 -0.1525 0.9191 0.0248
-16.500 -0.4540 0.06795 0.06481 -0.1555 0.9137 0.0251
-16.250 -0.4606 0.06404 0.06082 -0.1579 0.9084 0.0254
-16.000 -0.4724 0.05941 0.05611 -0.1611 0.9018 0.0257
-15.750 -0.4833 0.05517 0.05177 -0.1641 0.8941 0.0260
-15.500 -0.5047 0.04979 0.04628 -0.1681 0.8847 0.0261
-15.250 -0.5354 0.04332 0.03966 -0.1732 0.8732 0.0262
-15.000 -0.6276 0.02491 0.02077 -0.1946 0.8518 0.0258
-14.750 -0.6136 0.02266 0.01832 -0.1970 0.8438 0.0262
-14.500 -0.5960 0.02140 0.01694 -0.1979 0.8364 0.0265
-14.250 -0.5787 0.02023 0.01566 -0.1984 0.8293 0.0271
-14.000 -0.5585 0.01935 0.01471 -0.1986 0.8228 0.0276
-13.750 -0.5373 0.01866 0.01393 -0.1987 0.8158 0.0282
-13.500 -0.5149 0.01807 0.01325 -0.1987 0.8100 0.0288
-13.250 -0.4917 0.01753 0.01265 -0.1987 0.8042 0.0294
-13.000 -0.4684 0.01705 0.01208 -0.1986 0.7985 0.0299
-12.750 -0.4444 0.01661 0.01155 -0.1985 0.7935 0.0303
-12.500 -0.4206 0.01611 0.01099 -0.1984 0.7879 0.0309
-12.250 -0.3971 0.01565 0.01046 -0.1982 0.7820 0.0316
-12.000 -0.3727 0.01526 0.01001 -0.1980 0.7769 0.0322
-11.750 -0.3474 0.01489 0.00960 -0.1980 0.7721 0.0329
-11.500 -0.3222 0.01457 0.00922 -0.1978 0.7670 0.0336
-11.250 -0.2971 0.01429 0.00886 -0.1976 0.7619 0.0342
-11.000 -0.2711 0.01401 0.00852 -0.1975 0.7575 0.0348
-10.750 -0.2458 0.01366 0.00812 -0.1973 0.7522 0.0354
-10.500 -0.2208 0.01335 0.00776 -0.1971 0.7467 0.0363
-10.250 -0.1953 0.01309 0.00745 -0.1969 0.7420 0.0371
-10.000 -0.1689 0.01284 0.00716 -0.1968 0.7376 0.0378
-9.750 -0.1427 0.01260 0.00687 -0.1966 0.7328 0.0385
-9.500 -0.1169 0.01241 0.00661 -0.1964 0.7279 0.0392
-9.250 -0.0905 0.01222 0.00637 -0.1962 0.7236 0.0398
-9.000 -0.0643 0.01196 0.00607 -0.1961 0.7187 0.0408
-8.750 -0.0384 0.01174 0.00581 -0.1958 0.7135 0.0417
-8.250 0.0142 0.01139 0.00538 -0.1954 0.7048 0.0435
-8.000 0.0411 0.01123 0.00518 -0.1953 0.7004 0.0445
-7.750 0.0674 0.01111 0.00500 -0.1951 0.6957 0.0453
-7.500 0.0929 0.01094 0.00479 -0.1947 0.6909 0.0466
-7.250 0.1199 0.01077 0.00460 -0.1946 0.6868 0.0480
-7.000 0.1466 0.01063 0.00444 -0.1945 0.6823 0.0493
-6.750 0.1729 0.01053 0.00429 -0.1942 0.6779 0.0505
-6.500 0.1987 0.01045 0.00416 -0.1938 0.6734 0.0516
-6.250 0.2254 0.01030 0.00399 -0.1937 0.6683 0.0534
-6.000 0.2510 0.01020 0.00386 -0.1933 0.6621 0.0553
-5.750 0.2757 0.01014 0.00375 -0.1927 0.6562 0.0573
-5.500 0.3026 0.01005 0.00364 -0.1925 0.6517 0.0591
-5.250 0.3287 0.00994 0.00352 -0.1922 0.6468 0.0619
-5.000 0.3534 0.00989 0.00343 -0.1917 0.6414 0.0647
-4.750 0.3791 0.00982 0.00334 -0.1913 0.6365 0.0678
-4.500 0.4048 0.00973 0.00325 -0.1909 0.6312 0.0725
-4.250 0.4281 0.00968 0.00318 -0.1900 0.6254 0.0777
-4.000 0.4513 0.00962 0.00311 -0.1892 0.6203 0.0844
-3.750 0.4763 0.00953 0.00304 -0.1887 0.6152 0.0924
-3.500 0.4998 0.00948 0.00299 -0.1879 0.6090 0.1009
-3.250 0.5231 0.00944 0.00295 -0.1871 0.6031 0.1128
-3.000 0.5488 0.00934 0.00291 -0.1868 0.5973 0.1340
-2.750 0.5736 0.00932 0.00295 -0.1863 0.5917 0.1595
-2.500 0.5977 0.00938 0.00301 -0.1857 0.5868 0.1704
-2.250 0.6242 0.00942 0.00304 -0.1855 0.5824 0.1765
-2.000 0.6501 0.00947 0.00308 -0.1851 0.5773 0.1802
-1.750 0.6753 0.00956 0.00316 -0.1847 0.5723 0.1847
-1.500 0.7012 0.00964 0.00322 -0.1844 0.5680 0.1884
-1.250 0.7277 0.00971 0.00328 -0.1843 0.5634 0.1908
-1.000 0.7531 0.00983 0.00336 -0.1839 0.5579 0.1930
-0.750 0.7771 0.00996 0.00345 -0.1833 0.5525 0.1960
-0.500 0.8035 0.01002 0.00353 -0.1832 0.5475 0.2004
-0.250 0.8285 0.01013 0.00363 -0.1828 0.5413 0.2036
0.000 0.8521 0.01029 0.00376 -0.1822 0.5349 0.2063
0.250 0.8773 0.01041 0.00386 -0.1818 0.5285 0.2081
0.500 0.8998 0.01060 0.00400 -0.1810 0.5201 0.2096
0.750 0.9232 0.01078 0.00415 -0.1803 0.5118 0.2107
1.000 0.9447 0.01103 0.00433 -0.1793 0.5015 0.2115
1.250 0.9674 0.01122 0.00450 -0.1786 0.4908 0.2134
1.500 0.9879 0.01150 0.00472 -0.1775 0.4797 0.2153
2.000 1.0285 0.01211 0.00524 -0.1752 0.4552 0.2192
2.250 1.0481 0.01246 0.00553 -0.1740 0.4426 0.2211
2.500 1.0662 0.01286 0.00587 -0.1726 0.4298 0.2230
2.750 1.0840 0.01330 0.00624 -0.1711 0.4167 0.2250
3.000 1.1033 0.01369 0.00658 -0.1699 0.4045 0.2270
3.250 1.1216 0.01412 0.00697 -0.1686 0.3935 0.2290
3.750 1.1585 0.01499 0.00778 -0.1661 0.3739 0.2370
4.000 1.1763 0.01547 0.00823 -0.1648 0.3653 0.2424
4.250 1.1961 0.01587 0.00863 -0.1638 0.3588 0.2487
4.500 1.2147 0.01632 0.00909 -0.1627 0.3521 0.2603
4.750 1.2339 0.01675 0.00955 -0.1617 0.3466 0.2798
5.000 1.2542 0.01712 0.01001 -0.1610 0.3422 0.3167
5.250 1.2728 0.01760 0.01054 -0.1599 0.3369 0.3479
5.500 1.2898 0.01818 0.01113 -0.1587 0.3308 0.3689
5.750 1.3093 0.01864 0.01164 -0.1579 0.3269 0.3859
6.000 1.3276 0.01916 0.01219 -0.1569 0.3226 0.4004
6.250 1.3453 0.01974 0.01278 -0.1558 0.3183 0.4153
6.500 1.3617 0.02039 0.01347 -0.1546 0.3140 0.4335
6.750 1.3811 0.02089 0.01406 -0.1539 0.3115 0.4633
7.000 1.4037 0.02119 0.01471 -0.1539 0.3094 0.6239
7.250 1.4194 0.02113 0.01538 -0.1524 0.3074 1.0000
7.500 1.4371 0.02178 0.01604 -0.1514 0.3052 1.0000
7.750 1.4544 0.02247 0.01672 -0.1505 0.3027 1.0000
8.000 1.4707 0.02322 0.01748 -0.1494 0.3002 1.0000
8.250 1.4860 0.02405 0.01831 -0.1483 0.2974 1.0000
8.500 1.5032 0.02477 0.01904 -0.1474 0.2954 1.0000
8.750 1.5213 0.02545 0.01975 -0.1466 0.2943 1.0000
9.000 1.5387 0.02619 0.02051 -0.1458 0.2922 1.0000
9.250 1.5551 0.02698 0.02131 -0.1449 0.2888 1.0000
9.500 1.5694 0.02793 0.02227 -0.1438 0.2853 1.0000
9.750 1.5819 0.02901 0.02333 -0.1425 0.2815 1.0000
10.000 1.5967 0.02994 0.02427 -0.1415 0.2782 1.0000
10.250 1.6123 0.03084 0.02520 -0.1407 0.2752 1.0000
10.500 1.6267 0.03182 0.02619 -0.1397 0.2713 1.0000
10.750 1.6386 0.03299 0.02736 -0.1385 0.2669 1.0000
11.000 1.6496 0.03425 0.02863 -0.1373 0.2628 1.0000
11.250 1.6642 0.03524 0.02964 -0.1364 0.2586 1.0000
11.500 1.6736 0.03665 0.03104 -0.1351 0.2519 1.0000
11.750 1.6831 0.03805 0.03243 -0.1338 0.2460 1.0000
12.000 1.6883 0.03981 0.03416 -0.1321 0.2351 1.0000
12.250 1.6784 0.04282 0.03701 -0.1292 0.2070 1.0000
12.500 1.6479 0.04766 0.04162 -0.1246 0.1670 1.0000
12.750 1.6403 0.05068 0.04457 -0.1222 0.1519 1.0000
13.000 1.6399 0.05315 0.04702 -0.1205 0.1432 1.0000
13.250 1.6422 0.05541 0.04929 -0.1192 0.1362 1.0000
13.500 1.6447 0.05766 0.05154 -0.1179 0.1299 1.0000
13.750 1.6465 0.06002 0.05391 -0.1166 0.1239 1.0000
14.000 1.6475 0.06248 0.05636 -0.1153 0.1165 1.0000
14.250 1.6474 0.06511 0.05899 -0.1141 0.1099 1.0000
14.500 1.6447 0.06802 0.06187 -0.1128 0.1012 1.0000
14.750 1.6390 0.07130 0.06514 -0.1115 0.0915 1.0000
15.000 1.6255 0.07547 0.06925 -0.1099 0.0779 1.0000
15.250 1.5946 0.08174 0.07543 -0.1078 0.0549 1.0000
15.500 1.5651 0.08807 0.08173 -0.1061 0.0344 1.0000
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