GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Reynolds number: 100,000 Max Cl/Cd: 49.43 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe243-il-100000-n5.txt Download as CSV file: xf-goe243-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 243 (MVA PR.3) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.1723 0.10288 0.09723 -0.1175 0.8558 0.0887
-9.250 0.1608 0.09981 0.09416 -0.1216 0.8482 0.0902
-8.750 0.1723 0.08825 0.08248 -0.1249 0.8376 0.0599
-8.500 0.1847 0.08635 0.08057 -0.1248 0.8309 0.0588
-8.250 0.1940 0.08355 0.07775 -0.1257 0.8256 0.0577
-8.000 0.1740 0.07534 0.06949 -0.1311 0.8189 0.0538
-7.750 0.1782 0.07279 0.06695 -0.1317 0.8113 0.0534
-7.500 0.1803 0.06897 0.06310 -0.1335 0.8054 0.0529
-7.250 0.1699 0.06382 0.05792 -0.1362 0.7988 0.0522
-7.000 0.1356 0.05614 0.05013 -0.1432 0.7882 0.0513
-6.750 0.1401 0.04559 0.03902 -0.1652 0.7816 0.0511
-6.500 0.1706 0.04083 0.03381 -0.1782 0.7728 0.0518
-6.250 0.2131 0.03727 0.02974 -0.1879 0.7665 0.0526
-6.000 0.2574 0.03455 0.02659 -0.1944 0.7621 0.0530
-5.750 0.2956 0.03264 0.02434 -0.1984 0.7571 0.0534
-5.500 0.3232 0.03147 0.02296 -0.1998 0.7492 0.0538
-5.250 0.3549 0.03035 0.02176 -0.2010 0.7439 0.0543
-5.000 0.3894 0.02929 0.02061 -0.2024 0.7397 0.0551
-4.750 0.4150 0.02869 0.01998 -0.2024 0.7330 0.0558
-4.500 0.4417 0.02811 0.01937 -0.2024 0.7262 0.0569
-4.250 0.4739 0.02740 0.01854 -0.2031 0.7211 0.0588
-4.000 0.5060 0.02676 0.01785 -0.2035 0.7168 0.0606
-3.750 0.5255 0.02666 0.01787 -0.2022 0.7084 0.0621
-3.500 0.5525 0.02632 0.01754 -0.2016 0.7023 0.0637
-3.250 0.5830 0.02595 0.01711 -0.2013 0.6976 0.0655
-3.000 0.6056 0.02592 0.01716 -0.2004 0.6899 0.0672
-2.750 0.6361 0.02565 0.01690 -0.2011 0.6830 0.0698
-2.500 0.6751 0.02512 0.01627 -0.2035 0.6776 0.0746
-2.250 0.7089 0.02478 0.01590 -0.2056 0.6699 0.0806
-2.000 0.7489 0.02419 0.01523 -0.2091 0.6624 0.0890
-1.750 0.7985 0.02316 0.01409 -0.2145 0.6568 0.1093
-1.500 0.8424 0.02236 0.01397 -0.2197 0.6482 0.3055
-1.250 0.8721 0.02254 0.01405 -0.2200 0.6405 0.3425
-1.000 0.9012 0.02282 0.01425 -0.2196 0.6344 0.3676
-0.750 0.9229 0.02333 0.01477 -0.2184 0.6252 0.3870
-0.500 0.9456 0.02373 0.01522 -0.2166 0.6182 0.3986
-0.250 0.9735 0.02391 0.01527 -0.2166 0.6105 0.4107
0.000 0.9942 0.02424 0.01564 -0.2149 0.6019 0.4161
0.250 1.0252 0.02419 0.01544 -0.2152 0.5954 0.4211
0.500 1.0490 0.02438 0.01558 -0.2149 0.5859 0.4259
0.750 1.0809 0.02428 0.01527 -0.2159 0.5781 0.4319
1.000 1.1049 0.02445 0.01542 -0.2151 0.5698 0.4346
1.250 1.1281 0.02465 0.01559 -0.2143 0.5606 0.4379
1.500 1.1545 0.02476 0.01559 -0.2139 0.5524 0.4420
1.750 1.1765 0.02502 0.01581 -0.2131 0.5424 0.4471
2.000 1.2064 0.02505 0.01562 -0.2136 0.5344 0.4546
2.250 1.2244 0.02547 0.01611 -0.2120 0.5251 0.4582
2.500 1.2483 0.02570 0.01628 -0.2112 0.5175 0.4629
2.750 1.2691 0.02608 0.01663 -0.2101 0.5095 0.4686
3.000 1.2925 0.02638 0.01684 -0.2096 0.5017 0.4761
3.250 1.3169 0.02664 0.01702 -0.2090 0.4953 0.4809
3.500 1.3323 0.02718 0.01762 -0.2071 0.4873 0.4855
3.750 1.3524 0.02755 0.01794 -0.2059 0.4803 0.4922
4.000 1.3740 0.02793 0.01822 -0.2050 0.4738 0.5006
4.250 1.3871 0.02854 0.01890 -0.2028 0.4664 0.5052
4.500 1.4068 0.02899 0.01929 -0.2015 0.4598 0.5118
4.750 1.4278 0.02950 0.01972 -0.2008 0.4536 0.5211
5.000 1.4423 0.03020 0.02050 -0.1990 0.4472 0.5256
5.250 1.4610 0.03076 0.02104 -0.1977 0.4416 0.5320
5.500 1.4840 0.03122 0.02137 -0.1972 0.4364 0.5421
5.750 1.4944 0.03212 0.02241 -0.1950 0.4298 0.5468
6.000 1.5088 0.03287 0.02317 -0.1933 0.4235 0.5537
6.250 1.5303 0.03337 0.02354 -0.1926 0.4181 0.5628
6.500 1.5397 0.03440 0.02469 -0.1904 0.4120 0.5677
6.750 1.5506 0.03538 0.02572 -0.1885 0.4056 0.5745
7.000 1.5678 0.03607 0.02634 -0.1874 0.3999 0.5829
7.250 1.5794 0.03706 0.02739 -0.1856 0.3946 0.5884
7.500 1.5879 0.03831 0.02873 -0.1837 0.3887 0.5954
7.750 1.6001 0.03933 0.02976 -0.1821 0.3832 0.6026
8.000 1.6158 0.04007 0.03047 -0.1808 0.3782 0.6088
8.250 1.6189 0.04178 0.03233 -0.1787 0.3719 0.6155
8.500 1.6260 0.04323 0.03383 -0.1769 0.3657 0.6218
8.750 1.6383 0.04421 0.03478 -0.1754 0.3603 0.6277
9.000 1.6404 0.04615 0.03686 -0.1735 0.3538 0.6339
9.250 1.6440 0.04800 0.03878 -0.1717 0.3472 0.6401
9.500 1.6529 0.04928 0.04004 -0.1702 0.3413 0.6457
9.750 1.6514 0.05171 0.04261 -0.1684 0.3343 0.6513
10.000 1.6532 0.05388 0.04484 -0.1668 0.3273 0.6573
10.250 1.6588 0.05560 0.04657 -0.1653 0.3211 0.6623
10.500 1.6537 0.05863 0.04977 -0.1638 0.3131 0.6673
10.750 1.6564 0.06083 0.05196 -0.1625 0.3060 0.6734
11.000 1.6521 0.06397 0.05521 -0.1612 0.2980 0.6778
11.250 1.6508 0.06675 0.05804 -0.1600 0.2901 0.6825
11.500 1.6474 0.06992 0.06127 -0.1589 0.2822 0.6875
11.750 1.6439 0.07317 0.06455 -0.1580 0.2740 0.6928
12.000 1.6415 0.07631 0.06775 -0.1571 0.2665 0.6973
12.250 1.6375 0.07974 0.07123 -0.1564 0.2589 0.7020
12.500 1.6384 0.08255 0.07402 -0.1557 0.2527 0.7074
12.750 1.6343 0.08617 0.07771 -0.1552 0.2461 0.7122
13.000 1.6367 0.08876 0.08029 -0.1546 0.2410 0.7176
13.250 1.6383 0.09160 0.08317 -0.1541 0.2365 0.7234
13.500 1.6372 0.09491 0.08655 -0.1538 0.2319 0.7287
13.750 1.6407 0.09747 0.08914 -0.1534 0.2283 0.7343
14.000 1.6496 0.09921 0.09085 -0.1530 0.2254 0.7415
14.250 1.6551 0.10152 0.09319 -0.1527 0.2225 0.7480
14.500 1.6543 0.10485 0.09666 -0.1526 0.2194 0.7541
14.750 1.6565 0.10774 0.09963 -0.1526 0.2166 0.7608
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