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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 100,000
Max Cl/Cd: 54.7 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe234-il-100000.txt
Download as CSV file: xf-goe234-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 234 (MVA CA5) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1498   0.12283   0.11823  -0.0575   0.9613   0.1227
  -8.500  -0.1447   0.12164   0.11704  -0.0636   0.9555   0.1300
  -8.250  -0.1465   0.11932   0.11476  -0.0653   0.9471   0.1318
  -8.000  -0.1093   0.11424   0.10962  -0.0658   0.9441   0.1362
  -7.750  -0.1055   0.11383   0.10921  -0.0726   0.9383   0.1451
  -7.500  -0.1146   0.11206   0.10750  -0.0713   0.9271   0.1467
  -7.250  -0.0687   0.10638   0.10175  -0.0727   0.9256   0.1520
  -7.000  -0.0639   0.10495   0.10032  -0.0740   0.9178   0.1585
  -6.750  -0.0797   0.10480   0.10024  -0.0775   0.9071   0.1622
  -6.500  -0.0340   0.09911   0.09447  -0.0787   0.9064   0.1665
  -6.250  -0.0400   0.09844   0.09384  -0.0754   0.8949   0.1702
  -5.750  -0.0327   0.09470   0.09014  -0.0782   0.8778   0.1797
  -5.500   0.1585   0.03930   0.03268  -0.2015   0.8776   0.1032
  -5.250   0.2201   0.03641   0.02943  -0.2099   0.8755   0.1049
  -5.000   0.2676   0.03513   0.02815  -0.2133   0.8733   0.1081
  -4.750   0.2854   0.03514   0.02813  -0.2124   0.8632   0.1116
  -4.500   0.3316   0.03425   0.02704  -0.2157   0.8596   0.1168
  -4.250   0.3690   0.03415   0.02715  -0.2155   0.8568   0.1225
  -4.000   0.3845   0.03463   0.02762  -0.2138   0.8463   0.1283
  -3.750   0.4284   0.03419   0.02725  -0.2166   0.8426   0.1432
  -3.500   0.4777   0.03378   0.02723  -0.2199   0.8403   0.1785
  -3.250   0.4714   0.03596   0.02980  -0.2124   0.8282   0.1971
  -3.000   0.4958   0.03802   0.03188  -0.2085   0.8237   0.2511
  -2.750   0.4938   0.04037   0.03423  -0.2022   0.8129   0.2652
  -2.500   0.5050   0.04239   0.03627  -0.1959   0.8071   0.2778
  -2.250   0.5351   0.04361   0.03741  -0.1933   0.8046   0.2982
  -1.750   0.5435   0.04625   0.04009  -0.1827   0.7880   0.3188
  -1.500   0.5799   0.04651   0.04028  -0.1821   0.7863   0.3472
  -0.750   0.6044   0.04835   0.04221  -0.1686   0.7659   0.4279
  -0.500   0.5942   0.04950   0.04342  -0.1636   0.7534   0.4355
  -0.250   0.6451   0.04795   0.04176  -0.1677   0.7518   0.4603
   0.000   0.6958   0.04611   0.03983  -0.1714   0.7508   0.4800
   0.250   0.7562   0.04474   0.03831  -0.1780   0.7494   0.5050
   0.500   0.7384   0.04631   0.03998  -0.1723   0.7350   0.5085
   0.750   0.7398   0.04799   0.04168  -0.1704   0.7227   0.5218
   1.000   0.7821   0.04624   0.03988  -0.1724   0.7198   0.5415
   1.250   0.8366   0.04393   0.03751  -0.1760   0.7185   0.5727
   1.500   0.8898   0.04088   0.03440  -0.1783   0.7172   0.6188
   1.750   0.8914   0.04136   0.03494  -0.1746   0.7047   0.6496
   2.000   0.9403   0.03812   0.03167  -0.1758   0.7024   0.6912
   2.250   0.9918   0.03529   0.02877  -0.1782   0.7001   0.7281
   2.500   1.0036   0.03576   0.02930  -0.1765   0.6893   0.7467
   2.750   1.0542   0.03420   0.02767  -0.1801   0.6855   0.7676
   3.000   1.1066   0.03231   0.02573  -0.1839   0.6827   0.7788
   3.250   1.1281   0.03306   0.02652  -0.1843   0.6722   0.7813
   3.500   1.1849   0.03190   0.02528  -0.1897   0.6677   0.7743
   3.750   1.2632   0.03109   0.02426  -0.1997   0.6641   0.7300
   4.000   1.2928   0.03227   0.02546  -0.2022   0.6523   0.6907
   4.250   1.3675   0.03152   0.02445  -0.2114   0.6473   0.6239
   4.500   1.3943   0.03229   0.02522  -0.2126   0.6354   0.5888
   4.750   1.4471   0.03147   0.02422  -0.2170   0.6287   0.5629
   5.000   1.4728   0.03185   0.02462  -0.2171   0.6169   0.5514
   5.250   1.5035   0.03154   0.02430  -0.2176   0.6072   0.5465
   5.500   1.5402   0.03115   0.02383  -0.2191   0.5972   0.5383
   5.750   1.5635   0.03144   0.02416  -0.2185   0.5849   0.5332
   6.000   1.5973   0.03109   0.02374  -0.2193   0.5743   0.5307
   6.250   1.6259   0.03097   0.02360  -0.2194   0.5619   0.5294
   6.500   1.6460   0.03125   0.02394  -0.2181   0.5479   0.5296
   6.750   1.6693   0.03142   0.02410  -0.2172   0.5341   0.5303
   7.000   1.6952   0.03151   0.02414  -0.2168   0.5204   0.5308
   7.250   1.7233   0.03155   0.02409  -0.2167   0.5067   0.5308
   7.500   1.7439   0.03188   0.02440  -0.2154   0.4921   0.5309
   7.750   1.7597   0.03241   0.02494  -0.2135   0.4773   0.5313
   8.000   1.7757   0.03296   0.02548  -0.2115   0.4632   0.5322
   8.250   1.7937   0.03349   0.02598  -0.2099   0.4504   0.5342
   8.500   1.8163   0.03382   0.02619  -0.2090   0.4384   0.5370
   8.750   1.8270   0.03456   0.02699  -0.2064   0.4266   0.5394
   9.000   1.8401   0.03534   0.02780  -0.2041   0.4162   0.5416
   9.250   1.8643   0.03576   0.02811  -0.2036   0.4065   0.5440
   9.500   1.8671   0.03688   0.02939  -0.1998   0.3977   0.5453
   9.750   1.8967   0.03732   0.02967  -0.2002   0.3894   0.5482
  10.000   1.8925   0.03861   0.03118  -0.1954   0.3820   0.5496
  10.250   1.9146   0.03904   0.03151  -0.1945   0.3731   0.5534
  10.500   1.9103   0.04047   0.03313  -0.1901   0.3653   0.5559
  10.750   1.9292   0.04100   0.03357  -0.1888   0.3566   0.5604
  11.000   1.9265   0.04259   0.03536  -0.1849   0.3497   0.5629
  11.250   1.9378   0.04350   0.03627  -0.1828   0.3418   0.5661
  11.500   1.9393   0.04494   0.03785  -0.1796   0.3344   0.5685
  11.750   1.9412   0.04623   0.03920  -0.1766   0.3258   0.5711
  12.000   1.9405   0.04786   0.04093  -0.1735   0.3179   0.5738
  12.250   1.9392   0.04952   0.04270  -0.1704   0.3099   0.5768
  12.500   1.9387   0.05128   0.04454  -0.1677   0.3020   0.5804
  12.750   1.9310   0.05351   0.04690  -0.1645   0.2934   0.5834
  13.000   1.9246   0.05579   0.04931  -0.1617   0.2848   0.5870
  13.250   1.9149   0.05842   0.05207  -0.1589   0.2757   0.5903
  13.500   1.9043   0.06140   0.05522  -0.1564   0.2672   0.5936
  13.750   1.8950   0.06430   0.05818  -0.1541   0.2574   0.5970
  14.000   1.8781   0.06847   0.06260  -0.1522   0.2482   0.5993
  14.250   1.8641   0.07244   0.06667  -0.1506   0.2370   0.6022
  14.500   1.8462   0.07722   0.07158  -0.1494   0.2246   0.6046
  14.750   1.8248   0.08300   0.07757  -0.1489   0.2107   0.6064
  15.000   1.8012   0.08943   0.08413  -0.1488   0.1935   0.6080
  15.250   1.7753   0.09670   0.09158  -0.1494   0.1683   0.6091
  15.500   1.7459   0.10446   0.09918  -0.1504   0.1376   0.6097
  15.750   1.7160   0.11251   0.10704  -0.1517   0.1211   0.6100
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