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GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il)
Reynolds number: 500,000
Max Cl/Cd: 118.29 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe227-il-500000-n5.txt
Download as CSV file: xf-goe227-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 227 (MVA H.37) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4299   0.04600   0.04230  -0.1333   0.8081   0.0310
 -11.500  -0.4355   0.03514   0.03107  -0.1523   0.8009   0.0312
 -11.250  -0.4080   0.02886   0.02450  -0.1667   0.7943   0.0316
 -11.000  -0.3711   0.02467   0.02008  -0.1780   0.7873   0.0322
 -10.750  -0.3341   0.02231   0.01755  -0.1852   0.7808   0.0328
 -10.500  -0.3013   0.02100   0.01611  -0.1889   0.7731   0.0333
 -10.250  -0.2695   0.01993   0.01488  -0.1917   0.7653   0.0339
 -10.000  -0.2380   0.01898   0.01378  -0.1941   0.7558   0.0344
  -9.750  -0.2068   0.01815   0.01278  -0.1961   0.7454   0.0350
  -9.500  -0.1760   0.01741   0.01187  -0.1978   0.7325   0.0356
  -9.250  -0.1455   0.01678   0.01105  -0.1992   0.7175   0.0362
  -9.000  -0.1153   0.01624   0.01031  -0.2005   0.7018   0.0367
  -8.750  -0.0847   0.01565   0.00960  -0.2018   0.6885   0.0375
  -8.500  -0.0544   0.01524   0.00908  -0.2029   0.6786   0.0384
  -8.000   0.0063   0.01454   0.00816  -0.2047   0.6645   0.0401
  -7.750   0.0368   0.01421   0.00771  -0.2056   0.6593   0.0411
  -7.500   0.0673   0.01390   0.00729  -0.2065   0.6549   0.0420
  -7.250   0.0980   0.01358   0.00687  -0.2073   0.6513   0.0430
  -7.000   0.1288   0.01328   0.00653  -0.2082   0.6482   0.0443
  -6.750   0.1594   0.01306   0.00627  -0.2089   0.6454   0.0457
  -6.500   0.1898   0.01287   0.00601  -0.2096   0.6427   0.0473
  -6.250   0.2201   0.01270   0.00575  -0.2102   0.6402   0.0489
  -6.000   0.2507   0.01250   0.00550  -0.2109   0.6380   0.0507
  -5.500   0.3112   0.01224   0.00515  -0.2121   0.6342   0.0545
  -5.250   0.3416   0.01210   0.00497  -0.2127   0.6325   0.0564
  -5.000   0.3722   0.01193   0.00477  -0.2133   0.6303   0.0584
  -4.750   0.4024   0.01183   0.00465  -0.2138   0.6274   0.0605
  -4.500   0.4322   0.01176   0.00454  -0.2143   0.6243   0.0629
  -4.250   0.4619   0.01172   0.00443  -0.2147   0.6214   0.0651
  -4.000   0.4920   0.01163   0.00428  -0.2152   0.6190   0.0671
  -3.750   0.5222   0.01153   0.00416  -0.2158   0.6166   0.0695
  -3.500   0.5524   0.01144   0.00407  -0.2162   0.6145   0.0721
  -3.250   0.5824   0.01138   0.00398  -0.2167   0.6125   0.0746
  -3.000   0.6122   0.01134   0.00391  -0.2171   0.6107   0.0765
  -2.750   0.6427   0.01121   0.00378  -0.2177   0.6088   0.0798
  -2.500   0.6727   0.01115   0.00371  -0.2182   0.6068   0.0829
  -2.250   0.7024   0.01112   0.00365  -0.2186   0.6046   0.0859
  -2.000   0.7319   0.01111   0.00360  -0.2189   0.6024   0.0883
  -1.750   0.7617   0.01109   0.00356  -0.2194   0.6003   0.0925
  -1.500   0.7915   0.01106   0.00354  -0.2198   0.5985   0.0979
  -1.250   0.8212   0.01101   0.00352  -0.2202   0.5965   0.1039
  -1.000   0.8509   0.01095   0.00351  -0.2206   0.5941   0.1141
  -0.750   0.8805   0.01091   0.00351  -0.2210   0.5916   0.1283
  -0.500   0.9100   0.01088   0.00351  -0.2214   0.5892   0.1442
  -0.250   0.9393   0.01086   0.00351  -0.2217   0.5866   0.1613
   0.250   0.9982   0.01074   0.00365  -0.2227   0.5808   0.2775
   0.500   1.0272   0.01076   0.00371  -0.2229   0.5784   0.2964
   0.750   1.0560   0.01078   0.00379  -0.2231   0.5757   0.3117
   1.000   1.0845   0.01082   0.00385  -0.2233   0.5726   0.3218
   1.250   1.1127   0.01088   0.00392  -0.2234   0.5691   0.3310
   1.500   1.1406   0.01096   0.00399  -0.2234   0.5655   0.3386
   1.750   1.1690   0.01100   0.00407  -0.2235   0.5620   0.3485
   2.000   1.1972   0.01103   0.00416  -0.2237   0.5579   0.3574
   2.250   1.2250   0.01109   0.00424  -0.2237   0.5532   0.3676
   2.500   1.2521   0.01117   0.00433  -0.2236   0.5481   0.3771
   2.750   1.2800   0.01121   0.00443  -0.2236   0.5415   0.3865
   3.000   1.3067   0.01129   0.00452  -0.2235   0.5331   0.3946
   3.500   1.3591   0.01149   0.00475  -0.2230   0.5075   0.4191
   3.750   1.3814   0.01175   0.00493  -0.2220   0.4816   0.4342
   4.000   1.4006   0.01222   0.00526  -0.2205   0.4541   0.4490
   4.250   1.4204   0.01270   0.00564  -0.2192   0.4345   0.4643
   4.500   1.4410   0.01313   0.00603  -0.2180   0.4210   0.4818
   4.750   1.4630   0.01346   0.00637  -0.2171   0.4111   0.5011
   5.000   1.4842   0.01383   0.00673  -0.2160   0.4030   0.5202
   5.250   1.5066   0.01411   0.00705  -0.2151   0.3963   0.5384
   5.500   1.5272   0.01447   0.00742  -0.2139   0.3899   0.5548
   5.750   1.5485   0.01476   0.00776  -0.2129   0.3850   0.5705
   6.000   1.5693   0.01503   0.00808  -0.2117   0.3802   0.5866
   6.250   1.5867   0.01536   0.00846  -0.2099   0.3754   0.6034
   6.500   1.6038   0.01577   0.00892  -0.2081   0.3702   0.6230
   6.750   1.6245   0.01605   0.00931  -0.2071   0.3650   0.6523
   7.000   1.6428   0.01638   0.00985  -0.2056   0.3577   0.7612
   7.250   1.6544   0.01663   0.01030  -0.2028   0.3517   1.0000
   7.500   1.6723   0.01710   0.01079  -0.2013   0.3444   1.0000
   7.750   1.6856   0.01781   0.01145  -0.1992   0.3363   1.0000
   8.000   1.7025   0.01836   0.01202  -0.1977   0.3274   1.0000
   8.250   1.7151   0.01916   0.01278  -0.1956   0.3186   1.0000
   8.500   1.7308   0.01982   0.01346  -0.1940   0.3105   1.0000
   8.750   1.7426   0.02073   0.01435  -0.1920   0.3012   1.0000
   9.000   1.7541   0.02169   0.01528  -0.1900   0.2899   1.0000
   9.250   1.7654   0.02270   0.01628  -0.1880   0.2790   1.0000
   9.500   1.7745   0.02390   0.01746  -0.1859   0.2676   1.0000
   9.750   1.7807   0.02534   0.01885  -0.1835   0.2527   1.0000
  10.000   1.7836   0.02708   0.02052  -0.1809   0.2341   1.0000
  10.250   1.7809   0.02931   0.02263  -0.1779   0.2115   1.0000
  10.500   1.7731   0.03202   0.02519  -0.1745   0.1836   1.0000
  11.000   1.7415   0.03917   0.03198  -0.1671   0.1214   1.0000
  11.250   1.7372   0.04197   0.03474  -0.1647   0.1069   1.0000
  11.500   1.7331   0.04486   0.03760  -0.1626   0.0915   1.0000
  11.750   1.7095   0.04984   0.04237  -0.1594   0.0524   1.0000
  12.000   1.6967   0.05397   0.04645  -0.1573   0.0349   1.0000
  12.250   1.6953   0.05694   0.04945  -0.1559   0.0291   1.0000
  12.500   1.6955   0.05979   0.05235  -0.1547   0.0256   1.0000
  12.750   1.6980   0.06241   0.05502  -0.1536   0.0234   1.0000
  13.000   1.6992   0.06522   0.05789  -0.1526   0.0216   1.0000
  13.250   1.7005   0.06804   0.06078  -0.1516   0.0204   1.0000
  13.500   1.7023   0.07077   0.06358  -0.1507   0.0193   1.0000
  13.750   1.7023   0.07378   0.06667  -0.1498   0.0184   1.0000
  14.000   1.7017   0.07689   0.06984  -0.1489   0.0175   1.0000
  14.250   1.7006   0.08011   0.07313  -0.1482   0.0169   1.0000
  14.500   1.7009   0.08317   0.07628  -0.1475   0.0162   1.0000
  14.750   1.6996   0.08644   0.07963  -0.1469   0.0157   1.0000
  15.000   1.6977   0.08984   0.08311  -0.1463   0.0151   1.0000
  15.250   1.6951   0.09337   0.08673  -0.1459   0.0147   1.0000
  15.500   1.6906   0.09722   0.09066  -0.1455   0.0143   1.0000
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