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GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
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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