GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.57 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe241-il-1000000.txt Download as CSV file: xf-goe241-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 241 (MVA PR.1) 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
------ -------- --------- --------- -------- -------- --------
-10.500 0.0884 0.09373 0.09099 -0.1050 0.7716 0.0293
-10.250 0.0973 0.09095 0.08821 -0.1067 0.7669 0.0299
-10.000 0.0695 0.07894 0.07620 -0.1150 0.7633 0.0322
-9.750 0.0810 0.07710 0.07435 -0.1158 0.7576 0.0323
-9.500 -0.0724 0.02806 0.02440 -0.1787 0.7530 0.0295
-9.250 -0.0353 0.02401 0.02002 -0.1889 0.7478 0.0299
-9.000 -0.0027 0.02204 0.01781 -0.1932 0.7419 0.0304
-8.750 0.0298 0.02003 0.01553 -0.1969 0.7360 0.0309
-8.500 0.0618 0.01856 0.01385 -0.1994 0.7307 0.0312
-8.250 0.0937 0.01749 0.01263 -0.2012 0.7248 0.0315
-8.000 0.1253 0.01676 0.01174 -0.2027 0.7184 0.0317
-7.750 0.1569 0.01625 0.01111 -0.2039 0.7122 0.0319
-7.500 0.1873 0.01477 0.00954 -0.2053 0.7055 0.0325
-7.250 0.2178 0.01429 0.00900 -0.2062 0.6977 0.0328
-7.000 0.2488 0.01391 0.00858 -0.2070 0.6901 0.0332
-6.750 0.2796 0.01359 0.00819 -0.2078 0.6812 0.0336
-6.500 0.3104 0.01331 0.00785 -0.2085 0.6726 0.0341
-6.250 0.3410 0.01304 0.00752 -0.2091 0.6629 0.0346
-6.000 0.3718 0.01272 0.00713 -0.2098 0.6536 0.0351
-5.750 0.4023 0.01244 0.00676 -0.2105 0.6429 0.0355
-5.500 0.4330 0.01219 0.00644 -0.2111 0.6324 0.0359
-5.250 0.4631 0.01204 0.00619 -0.2116 0.6200 0.0363
-5.000 0.4941 0.01165 0.00572 -0.2124 0.6064 0.0368
-4.750 0.5250 0.01139 0.00540 -0.2132 0.5929 0.0375
-4.500 0.5551 0.01128 0.00523 -0.2138 0.5797 0.0382
-4.250 0.5847 0.01123 0.00508 -0.2142 0.5664 0.0389
-4.000 0.6150 0.01114 0.00493 -0.2147 0.5541 0.0396
-3.750 0.6448 0.01110 0.00481 -0.2151 0.5429 0.0405
-3.500 0.6740 0.01111 0.00474 -0.2154 0.5318 0.0412
-3.250 0.7053 0.01089 0.00446 -0.2163 0.5224 0.0423
-3.000 0.7349 0.01086 0.00436 -0.2167 0.5128 0.0434
-2.750 0.7650 0.01082 0.00428 -0.2172 0.5058 0.0447
-2.500 0.7945 0.01081 0.00422 -0.2175 0.4984 0.0460
-2.250 0.8237 0.01082 0.00416 -0.2178 0.4915 0.0472
-2.000 0.8542 0.01072 0.00404 -0.2184 0.4859 0.0494
-1.750 0.8833 0.01074 0.00402 -0.2186 0.4798 0.0516
-1.500 0.9121 0.01078 0.00400 -0.2188 0.4737 0.0543
-1.250 0.9419 0.01074 0.00395 -0.2192 0.4692 0.0578
-1.000 0.9709 0.01076 0.00393 -0.2195 0.4635 0.0620
-0.750 0.9990 0.01082 0.00396 -0.2196 0.4571 0.0685
-0.500 1.0334 0.01019 0.00384 -0.2216 0.4529 0.2836
-0.250 1.0626 0.01016 0.00392 -0.2220 0.4488 0.3400
0.000 1.0906 0.01025 0.00402 -0.2220 0.4446 0.3614
0.250 1.1179 0.01038 0.00414 -0.2219 0.4403 0.3771
0.500 1.1454 0.01051 0.00426 -0.2219 0.4366 0.3899
0.750 1.1737 0.01058 0.00435 -0.2219 0.4336 0.4005
1.000 1.2012 0.01070 0.00446 -0.2219 0.4299 0.4104
1.250 1.2283 0.01083 0.00459 -0.2218 0.4264 0.4189
1.500 1.2546 0.01100 0.00473 -0.2215 0.4224 0.4270
1.750 1.2810 0.01116 0.00487 -0.2212 0.4187 0.4342
2.000 1.3085 0.01125 0.00499 -0.2212 0.4158 0.4420
2.250 1.3351 0.01139 0.00512 -0.2210 0.4124 0.4496
2.500 1.3612 0.01154 0.00527 -0.2207 0.4089 0.4564
2.750 1.3862 0.01173 0.00545 -0.2203 0.4051 0.4621
3.000 1.4107 0.01194 0.00564 -0.2197 0.4014 0.4672
3.250 1.4372 0.01205 0.00576 -0.2195 0.3992 0.4713
3.500 1.4630 0.01217 0.00591 -0.2192 0.3963 0.4769
3.750 1.4878 0.01234 0.00609 -0.2188 0.3929 0.4819
4.000 1.5110 0.01255 0.00628 -0.2180 0.3892 0.4869
4.250 1.5309 0.01281 0.00651 -0.2166 0.3851 0.4910
4.500 1.5526 0.01296 0.00670 -0.2155 0.3823 0.4960
4.750 1.5756 0.01313 0.00690 -0.2148 0.3790 0.5006
5.000 1.5980 0.01337 0.00714 -0.2139 0.3747 0.5049
5.250 1.6185 0.01369 0.00743 -0.2128 0.3696 0.5089
5.500 1.6402 0.01397 0.00771 -0.2119 0.3649 0.5128
5.750 1.6627 0.01422 0.00798 -0.2111 0.3595 0.5176
6.000 1.6819 0.01461 0.00835 -0.2099 0.3524 0.5216
6.250 1.7024 0.01496 0.00870 -0.2088 0.3458 0.5256
6.500 1.7202 0.01544 0.00913 -0.2074 0.3361 0.5290
6.750 1.7378 0.01594 0.00960 -0.2060 0.3245 0.5326
7.000 1.7507 0.01669 0.01027 -0.2039 0.3078 0.5365
7.500 1.7650 0.01891 0.01225 -0.1984 0.2673 0.5431
8.000 1.7861 0.02091 0.01414 -0.1941 0.2473 0.5493
8.250 1.7967 0.02194 0.01516 -0.1921 0.2408 0.5529
8.500 1.8103 0.02281 0.01605 -0.1906 0.2365 0.5563
8.750 1.8248 0.02365 0.01692 -0.1893 0.2338 0.5597
9.000 1.8380 0.02458 0.01788 -0.1878 0.2311 0.5632
9.250 1.8496 0.02565 0.01895 -0.1862 0.2283 0.5664
9.500 1.8598 0.02685 0.02016 -0.1845 0.2253 0.5693
9.750 1.8700 0.02808 0.02143 -0.1830 0.2224 0.5726
10.000 1.8850 0.02897 0.02239 -0.1819 0.2212 0.5761
10.250 1.8991 0.02994 0.02340 -0.1808 0.2196 0.5796
10.500 1.9108 0.03110 0.02460 -0.1795 0.2178 0.5829
10.750 1.9221 0.03231 0.02584 -0.1783 0.2161 0.5854
11.000 1.9318 0.03370 0.02729 -0.1769 0.2144 0.5890
11.250 1.9411 0.03514 0.02878 -0.1756 0.2127 0.5925
11.500 1.9470 0.03690 0.03057 -0.1741 0.2104 0.5958
11.750 1.9519 0.03877 0.03248 -0.1725 0.2083 0.5990
12.000 1.9599 0.04041 0.03417 -0.1713 0.2070 0.6020
12.250 1.9720 0.04171 0.03554 -0.1704 0.2063 0.6055
12.500 1.9835 0.04308 0.03699 -0.1696 0.2054 0.6095
12.750 1.9946 0.04449 0.03847 -0.1687 0.2042 0.6138
13.000 2.0033 0.04615 0.04020 -0.1677 0.2030 0.6178
13.250 2.0117 0.04782 0.04193 -0.1668 0.2015 0.6216
13.500 2.0172 0.04984 0.04402 -0.1657 0.1999 0.6261
13.750 2.0220 0.05194 0.04617 -0.1647 0.1981 0.6307
14.000 2.0229 0.05449 0.04877 -0.1635 0.1959 0.6356
14.250 2.0193 0.05753 0.05187 -0.1622 0.1930 0.6410
14.500 2.0279 0.05931 0.05373 -0.1615 0.1916 0.6496
14.750 2.0361 0.06117 0.05569 -0.1609 0.1905 0.6614
15.000 2.0444 0.06302 0.05768 -0.1604 0.1891 0.6878
15.250 2.0496 0.06486 0.05991 -0.1596 0.1873 1.0000
15.500 2.0524 0.06733 0.06243 -0.1589 0.1852 1.0000
15.750 2.0509 0.07031 0.06545 -0.1580 0.1827 1.0000
16.000 2.0469 0.07357 0.06875 -0.1572 0.1801 1.0000
16.250 2.0446 0.07666 0.07189 -0.1565 0.1776 1.0000
16.500 2.0503 0.07883 0.07413 -0.1560 0.1753 1.0000
16.750 2.0502 0.08170 0.07705 -0.1555 0.1712 1.0000
17.000 2.0406 0.08576 0.08113 -0.1549 0.1664 1.0000
17.250 2.0360 0.08920 0.08460 -0.1544 0.1604 1.0000
17.500 2.0202 0.09404 0.08944 -0.1538 0.1512 1.0000
17.750 1.9949 0.10017 0.09553 -0.1534 0.1372 1.0000
18.000 1.9569 0.10808 0.10338 -0.1533 0.1202 1.0000
18.250 1.9217 0.11571 0.11097 -0.1535 0.1061 1.0000
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