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GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il)
Reynolds number: 500,000
Max Cl/Cd: 91.66 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe241-il-500000-n5.txt
Download as CSV file: xf-goe241-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1863   0.04118   0.03705  -0.1465   0.7642   0.0277
 -10.500  -0.1841   0.03639   0.03206  -0.1546   0.7578   0.0278
 -10.250  -0.1658   0.03296   0.02846  -0.1620   0.7524   0.0280
 -10.000  -0.1395   0.03013   0.02548  -0.1691   0.7468   0.0282
  -9.750  -0.1086   0.02774   0.02292  -0.1758   0.7405   0.0284
  -9.500  -0.0750   0.02569   0.02066  -0.1818   0.7344   0.0286
  -9.250  -0.0408   0.02393   0.01873  -0.1869   0.7281   0.0289
  -9.000  -0.0087   0.02252   0.01715  -0.1903   0.7213   0.0293
  -8.750   0.0228   0.02133   0.01576  -0.1929   0.7151   0.0296
  -8.500   0.0547   0.02027   0.01456  -0.1952   0.7088   0.0301
  -8.250   0.0862   0.01934   0.01346  -0.1971   0.7015   0.0306
  -8.000   0.1174   0.01850   0.01244  -0.1987   0.6945   0.0310
  -7.750   0.1485   0.01777   0.01157  -0.2001   0.6860   0.0313
  -7.500   0.1789   0.01715   0.01080  -0.2012   0.6773   0.0315
  -7.250   0.2096   0.01659   0.01020  -0.2022   0.6681   0.0318
  -7.000   0.2398   0.01620   0.00972  -0.2030   0.6590   0.0321
  -6.750   0.2706   0.01582   0.00930  -0.2040   0.6495   0.0325
  -6.500   0.3009   0.01551   0.00889  -0.2047   0.6399   0.0328
  -6.250   0.3315   0.01519   0.00850  -0.2055   0.6295   0.0332
  -6.000   0.3618   0.01490   0.00813  -0.2062   0.6192   0.0337
  -5.750   0.3922   0.01463   0.00777  -0.2070   0.6080   0.0342
  -5.500   0.4225   0.01438   0.00743  -0.2076   0.5971   0.0347
  -5.250   0.4522   0.01421   0.00713  -0.2082   0.5854   0.0353
  -5.000   0.4825   0.01402   0.00685  -0.2088   0.5739   0.0358
  -4.750   0.5127   0.01382   0.00660  -0.2095   0.5633   0.0365
  -4.500   0.5427   0.01369   0.00640  -0.2101   0.5529   0.0370
  -4.250   0.5725   0.01358   0.00622  -0.2107   0.5428   0.0377
  -4.000   0.6021   0.01350   0.00606  -0.2112   0.5321   0.0384
  -3.750   0.6319   0.01341   0.00589  -0.2117   0.5227   0.0392
  -3.500   0.6611   0.01336   0.00575  -0.2121   0.5130   0.0400
  -3.250   0.6911   0.01327   0.00560  -0.2126   0.5052   0.0408
  -3.000   0.7207   0.01321   0.00549  -0.2131   0.4975   0.0419
  -2.750   0.7496   0.01321   0.00543  -0.2134   0.4913   0.0432
  -2.500   0.7792   0.01316   0.00535  -0.2138   0.4858   0.0448
  -2.250   0.8084   0.01315   0.00528  -0.2142   0.4797   0.0462
  -1.750   0.8660   0.01315   0.00520  -0.2147   0.4684   0.0500
  -1.500   0.8947   0.01317   0.00517  -0.2149   0.4629   0.0522
  -1.250   0.9228   0.01320   0.00516  -0.2151   0.4576   0.0553
  -1.000   0.9507   0.01327   0.00518  -0.2152   0.4528   0.0591
  -0.750   0.9794   0.01328   0.00518  -0.2154   0.4483   0.0647
  -0.500   1.0075   0.01331   0.00521  -0.2155   0.4439   0.0746
  -0.250   1.0406   0.01279   0.00518  -0.2174   0.4398   0.2907
   0.000   1.0676   0.01289   0.00532  -0.2174   0.4362   0.3295
   0.250   1.0951   0.01298   0.00544  -0.2174   0.4332   0.3525
   0.500   1.1223   0.01308   0.00557  -0.2173   0.4301   0.3698
   0.750   1.1489   0.01322   0.00572  -0.2171   0.4264   0.3828
   1.000   1.1745   0.01340   0.00588  -0.2167   0.4221   0.3943
   1.250   1.1992   0.01361   0.00606  -0.2162   0.4177   0.4048
   1.500   1.2252   0.01376   0.00621  -0.2159   0.4147   0.4136
   1.750   1.2511   0.01391   0.00639  -0.2156   0.4118   0.4234
   2.000   1.2763   0.01409   0.00656  -0.2151   0.4086   0.4316
   2.250   1.3006   0.01428   0.00676  -0.2145   0.4050   0.4386
   2.500   1.3235   0.01453   0.00698  -0.2137   0.4010   0.4443
   2.750   1.3456   0.01475   0.00718  -0.2127   0.3972   0.4493
   3.000   1.3678   0.01493   0.00737  -0.2117   0.3933   0.4541
   3.250   1.3887   0.01515   0.00762  -0.2106   0.3889   0.4593
   3.500   1.4099   0.01544   0.00789  -0.2095   0.3847   0.4648
   3.750   1.4305   0.01578   0.00820  -0.2084   0.3807   0.4698
   4.000   1.4540   0.01601   0.00845  -0.2078   0.3772   0.4741
   4.250   1.4764   0.01628   0.00875  -0.2070   0.3732   0.4785
   4.500   1.4974   0.01662   0.00909  -0.2060   0.3686   0.4834
   4.750   1.5168   0.01703   0.00949  -0.2048   0.3641   0.4885
   5.000   1.5384   0.01735   0.00982  -0.2040   0.3597   0.4933
   5.250   1.5590   0.01772   0.01020  -0.2030   0.3541   0.4973
   5.500   1.5768   0.01823   0.01070  -0.2017   0.3480   0.5012
   5.750   1.5964   0.01866   0.01115  -0.2006   0.3418   0.5056
   6.000   1.6137   0.01922   0.01169  -0.1993   0.3334   0.5102
   6.250   1.6302   0.01984   0.01228  -0.1978   0.3245   0.5144
   6.500   1.6440   0.02061   0.01302  -0.1961   0.3127   0.5179
   6.750   1.6555   0.02155   0.01391  -0.1941   0.2980   0.5213
   7.000   1.6643   0.02269   0.01497  -0.1919   0.2824   0.5250
   7.500   1.6829   0.02506   0.01724  -0.1879   0.2596   0.5327
   8.000   1.7039   0.02739   0.01957  -0.1844   0.2469   0.5389
   8.250   1.7153   0.02854   0.02074  -0.1829   0.2424   0.5425
   8.500   1.7252   0.02983   0.02205  -0.1813   0.2384   0.5462
   8.750   1.7351   0.03113   0.02336  -0.1798   0.2350   0.5496
   9.000   1.7473   0.03228   0.02455  -0.1785   0.2329   0.5527
   9.250   1.7593   0.03347   0.02579  -0.1773   0.2306   0.5558
   9.500   1.7692   0.03484   0.02722  -0.1759   0.2282   0.5591
   9.750   1.7788   0.03627   0.02869  -0.1746   0.2259   0.5624
  10.000   1.7862   0.03792   0.03037  -0.1732   0.2234   0.5655
  10.250   1.7931   0.03964   0.03212  -0.1717   0.2209   0.5685
  10.500   1.7992   0.04148   0.03400  -0.1703   0.2185   0.5714
  10.750   1.8103   0.04288   0.03549  -0.1694   0.2175   0.5745
  11.000   1.8202   0.04443   0.03711  -0.1684   0.2164   0.5778
  11.250   1.8298   0.04600   0.03876  -0.1674   0.2153   0.5811
  11.500   1.8378   0.04777   0.04059  -0.1663   0.2138   0.5841
  11.750   1.8452   0.04960   0.04248  -0.1653   0.2120   0.5873
  12.000   1.8506   0.05167   0.04462  -0.1642   0.2100   0.5903
  12.250   1.8551   0.05388   0.04688  -0.1632   0.2080   0.5934
  12.500   1.8583   0.05624   0.04930  -0.1622   0.2060   0.5967
  12.750   1.8603   0.05875   0.05187  -0.1611   0.2042   0.5999
  13.000   1.8625   0.06124   0.05441  -0.1601   0.2024   0.6029
  13.250   1.8690   0.06334   0.05660  -0.1594   0.2013   0.6060
  13.500   1.8769   0.06528   0.05864  -0.1588   0.2002   0.6099
  13.750   1.8829   0.06748   0.06093  -0.1582   0.1987   0.6142
  14.000   1.8882   0.06974   0.06328  -0.1576   0.1968   0.6186
  14.500   1.8929   0.07499   0.06869  -0.1564   0.1926   0.6272
  14.750   1.8930   0.07792   0.07168  -0.1558   0.1908   0.6320
  15.000   1.8929   0.08087   0.07470  -0.1552   0.1890   0.6375
  15.250   1.8915   0.08402   0.07792  -0.1548   0.1871   0.6445
  15.500   1.8958   0.08648   0.08049  -0.1544   0.1856   0.6552
  15.750   1.9004   0.08891   0.08307  -0.1542   0.1840   0.6742
  16.000   1.9031   0.09099   0.08551  -0.1535   0.1820   0.9586
  16.250   1.9039   0.09387   0.08847  -0.1532   0.1798   1.0000
  16.500   1.9043   0.09681   0.09146  -0.1530   0.1773   1.0000
  16.750   1.9003   0.10036   0.09506  -0.1529   0.1744   1.0000
  17.000   1.8987   0.10359   0.09832  -0.1528   0.1714   1.0000
  17.250   1.8996   0.10651   0.10133  -0.1528   0.1672   1.0000
  17.500   1.8938   0.11032   0.10517  -0.1529   0.1610   1.0000
  17.750   1.8878   0.11421   0.10910  -0.1532   0.1542   1.0000
  18.000   1.8738   0.11924   0.11411  -0.1537   0.1426   1.0000
  18.250   1.8412   0.12701   0.12178  -0.1548   0.1231   1.0000
  18.500   1.8104   0.13457   0.12929  -0.1563   0.1065   1.0000
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