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GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il)
Reynolds number: 200,000
Max Cl/Cd: 88.54 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe227-il-200000-n5.txt
Download as CSV file: xf-goe227-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0155   0.09207   0.08760  -0.1037   0.8282   0.0403
  -9.500  -0.0119   0.08849   0.08396  -0.1056   0.8210   0.0408
  -9.250  -0.0134   0.08369   0.07914  -0.1087   0.8137   0.0419
  -9.000  -0.0190   0.07776   0.07318  -0.1125   0.8061   0.0424
  -8.750  -0.0168   0.07373   0.06911  -0.1149   0.7988   0.0428
  -8.500  -0.0072   0.07142   0.06678  -0.1163   0.7904   0.0432
  -8.000  -0.0179   0.02534   0.01910  -0.1919   0.7715   0.0489
  -7.750   0.0138   0.02382   0.01734  -0.1948   0.7642   0.0499
  -7.500   0.0435   0.02311   0.01655  -0.1962   0.7558   0.0508
  -7.250   0.0740   0.02243   0.01572  -0.1977   0.7487   0.0521
  -7.000   0.1053   0.02155   0.01465  -0.1995   0.7409   0.0538
  -6.750   0.1377   0.02048   0.01325  -0.2016   0.7345   0.0558
  -6.500   0.1693   0.01955   0.01208  -0.2032   0.7278   0.0573
  -6.250   0.1993   0.01907   0.01154  -0.2041   0.7217   0.0587
  -6.000   0.2297   0.01863   0.01100  -0.2050   0.7165   0.0604
  -5.750   0.2603   0.01819   0.01042  -0.2060   0.7110   0.0628
  -5.500   0.2914   0.01774   0.00975  -0.2070   0.7063   0.0654
  -5.250   0.3219   0.01728   0.00920  -0.2079   0.7024   0.0676
  -5.000   0.3522   0.01697   0.00885  -0.2087   0.6984   0.0699
  -4.750   0.3826   0.01667   0.00845  -0.2094   0.6946   0.0727
  -4.500   0.4131   0.01642   0.00805  -0.2101   0.6912   0.0758
  -4.250   0.4437   0.01605   0.00763  -0.2109   0.6882   0.0788
  -4.000   0.4741   0.01584   0.00737  -0.2116   0.6855   0.0819
  -3.750   0.5042   0.01566   0.00713  -0.2122   0.6819   0.0855
  -3.500   0.5341   0.01550   0.00687  -0.2128   0.6778   0.0886
  -3.250   0.5645   0.01524   0.00661  -0.2135   0.6737   0.0923
  -3.000   0.5946   0.01513   0.00641  -0.2140   0.6700   0.0964
  -2.750   0.6244   0.01502   0.00626  -0.2145   0.6661   0.1002
  -2.500   0.6544   0.01490   0.00613  -0.2151   0.6624   0.1044
  -2.250   0.6844   0.01481   0.00604  -0.2156   0.6590   0.1097
  -2.000   0.7144   0.01477   0.00592  -0.2161   0.6561   0.1154
  -1.750   0.7449   0.01471   0.00583  -0.2168   0.6532   0.1222
  -1.500   0.7744   0.01468   0.00579  -0.2172   0.6497   0.1319
  -1.250   0.8041   0.01461   0.00574  -0.2177   0.6459   0.1448
  -1.000   0.8340   0.01453   0.00569  -0.2183   0.6428   0.1623
  -0.750   0.8646   0.01438   0.00569  -0.2191   0.6395   0.2059
  -0.500   0.8943   0.01440   0.00584  -0.2196   0.6361   0.2855
  -0.250   0.9228   0.01451   0.00594  -0.2198   0.6326   0.3135
   0.000   0.9508   0.01462   0.00607  -0.2198   0.6289   0.3327
   0.250   0.9790   0.01472   0.00619  -0.2199   0.6254   0.3467
   0.500   1.0073   0.01482   0.00630  -0.2200   0.6220   0.3604
   0.750   1.0359   0.01496   0.00641  -0.2202   0.6190   0.3757
   1.000   1.0642   0.01509   0.00654  -0.2203   0.6160   0.3892
   1.250   1.0912   0.01520   0.00672  -0.2202   0.6122   0.4025
   1.500   1.1184   0.01530   0.00688  -0.2201   0.6081   0.4141
   1.750   1.1460   0.01541   0.00700  -0.2201   0.6041   0.4251
   2.000   1.1743   0.01554   0.00711  -0.2202   0.6005   0.4350
   2.250   1.2012   0.01566   0.00730  -0.2201   0.5966   0.4457
   2.750   1.2539   0.01588   0.00767  -0.2197   0.5869   0.4717
   3.000   1.2814   0.01600   0.00778  -0.2196   0.5824   0.4847
   3.250   1.3065   0.01612   0.00803  -0.2192   0.5767   0.4987
   3.500   1.3319   0.01624   0.00822  -0.2188   0.5708   0.5146
   3.750   1.3581   0.01635   0.00835  -0.2185   0.5654   0.5321
   4.000   1.3823   0.01649   0.00862  -0.2179   0.5580   0.5501
   4.250   1.4068   0.01660   0.00878  -0.2173   0.5504   0.5693
   4.500   1.4305   0.01673   0.00902  -0.2166   0.5416   0.5898
   4.750   1.4536   0.01684   0.00919  -0.2158   0.5325   0.6118
   5.000   1.4757   0.01697   0.00945  -0.2148   0.5205   0.6369
   5.250   1.4966   0.01710   0.00968  -0.2135   0.5066   0.6722
   5.500   1.5150   0.01720   0.00989  -0.2118   0.4909   0.7527
   5.750   1.5273   0.01725   0.01004  -0.2087   0.4760   1.0000
   6.000   1.5438   0.01769   0.01039  -0.2068   0.4624   1.0000
   6.250   1.5591   0.01821   0.01081  -0.2047   0.4511   1.0000
   6.500   1.5717   0.01879   0.01130  -0.2021   0.4407   1.0000
   6.750   1.5856   0.01940   0.01187  -0.1999   0.4314   1.0000
   7.000   1.5987   0.02009   0.01249  -0.1975   0.4229   1.0000
   7.250   1.6142   0.02072   0.01311  -0.1957   0.4153   1.0000
   7.500   1.6290   0.02141   0.01377  -0.1938   0.4086   1.0000
   7.750   1.6446   0.02209   0.01445  -0.1920   0.4028   1.0000
   8.000   1.6602   0.02276   0.01516  -0.1904   0.3966   1.0000
   8.250   1.6746   0.02352   0.01591  -0.1885   0.3907   1.0000
   8.500   1.6892   0.02428   0.01669  -0.1868   0.3849   1.0000
   8.750   1.7020   0.02510   0.01758  -0.1849   0.3777   1.0000
   9.000   1.7124   0.02610   0.01854  -0.1827   0.3702   1.0000
   9.250   1.7225   0.02710   0.01962  -0.1806   0.3611   1.0000
   9.500   1.7301   0.02829   0.02079  -0.1782   0.3525   1.0000
   9.750   1.7396   0.02941   0.02200  -0.1763   0.3436   1.0000
  10.000   1.7464   0.03075   0.02334  -0.1740   0.3357   1.0000
  10.250   1.7552   0.03201   0.02470  -0.1721   0.3267   1.0000
  10.500   1.7608   0.03352   0.02622  -0.1700   0.3185   1.0000
  10.750   1.7684   0.03495   0.02773  -0.1682   0.3094   1.0000
  11.000   1.7725   0.03667   0.02948  -0.1661   0.2997   1.0000
  11.250   1.7728   0.03875   0.03157  -0.1638   0.2876   1.0000
  11.500   1.7737   0.04087   0.03373  -0.1617   0.2735   1.0000
  11.750   1.7728   0.04324   0.03610  -0.1597   0.2586   1.0000
  12.000   1.7691   0.04597   0.03881  -0.1576   0.2419   1.0000
  12.250   1.7628   0.04908   0.04188  -0.1555   0.2218   1.0000
  12.500   1.7506   0.05293   0.04562  -0.1534   0.1976   1.0000
  12.750   1.7325   0.05756   0.05010  -0.1513   0.1679   1.0000
  13.000   1.7118   0.06269   0.05506  -0.1493   0.1399   1.0000
  13.250   1.6949   0.06752   0.05979  -0.1477   0.1196   1.0000
  13.500   1.6806   0.07217   0.06439  -0.1464   0.1024   1.0000
  13.750   1.6600   0.07772   0.06983  -0.1451   0.0672   1.0000
  14.000   1.6349   0.08399   0.07596  -0.1441   0.0467   1.0000
  14.250   1.6211   0.08898   0.08098  -0.1434   0.0390   1.0000
  14.500   1.6120   0.09345   0.08553  -0.1430   0.0349   1.0000
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