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GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il)
Reynolds number: 50,000
Max Cl/Cd: 21.53 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe229-il-50000-n5.txt
Download as CSV file: xf-goe229-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 229 (MVA H.39) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2878   0.09339   0.08717  -0.0920   0.9558   0.0573
 -10.500  -0.3062   0.08649   0.08020  -0.0969   0.9462   0.0571
 -10.250  -0.3241   0.07949   0.07306  -0.1033   0.9382   0.0569
 -10.000  -0.3442   0.07415   0.06757  -0.1074   0.9270   0.0567
  -9.750  -0.3650   0.06995   0.06320  -0.1100   0.9147   0.0566
  -9.500  -0.3706   0.06433   0.05718  -0.1173   0.9055   0.0570
  -9.250  -0.3781   0.06105   0.05364  -0.1187   0.8935   0.0574
  -9.000  -0.3551   0.05734   0.04974  -0.1219   0.8890   0.0588
  -8.750  -0.3528   0.05529   0.04753  -0.1208   0.8779   0.0595
  -8.500  -0.3262   0.05256   0.04455  -0.1233   0.8731   0.0614
  -8.250  -0.3181   0.05102   0.04286  -0.1223   0.8630   0.0634
  -8.000  -0.2911   0.04887   0.04041  -0.1239   0.8575   0.0665
  -7.750  -0.2737   0.04745   0.03872  -0.1231   0.8494   0.0684
  -7.500  -0.2500   0.04623   0.03734  -0.1221   0.8428   0.0701
  -7.250  -0.2188   0.04499   0.03613  -0.1227   0.8387   0.0740
  -7.000  -0.2101   0.04439   0.03548  -0.1205   0.8281   0.0770
  -6.750  -0.1807   0.04333   0.03425  -0.1208   0.8231   0.0809
  -6.500  -0.1680   0.04274   0.03364  -0.1190   0.8139   0.0832
  -6.250  -0.1432   0.04166   0.03254  -0.1196   0.8075   0.0875
  -6.000  -0.1183   0.04067   0.03141  -0.1204   0.8011   0.0946
  -5.750  -0.1000   0.03963   0.03039  -0.1210   0.7922   0.1017
  -5.500  -0.0640   0.03793   0.02863  -0.1245   0.7881   0.1147
  -5.250  -0.0456   0.03655   0.02742  -0.1264   0.7781   0.1348
  -5.000  -0.0155   0.03592   0.02811  -0.1277   0.7729   0.2883
  -4.750   0.0146   0.03647   0.02830  -0.1289   0.7656   0.3614
  -4.500   0.0364   0.03776   0.02945  -0.1270   0.7577   0.3914
  -4.250   0.0706   0.03833   0.02976  -0.1271   0.7538   0.4150
  -4.000   0.0815   0.03938   0.03070  -0.1246   0.7436   0.4314
  -3.750   0.1084   0.04007   0.03127  -0.1233   0.7387   0.4492
  -3.500   0.1303   0.04093   0.03206  -0.1210   0.7332   0.4671
  -3.250   0.1375   0.04198   0.03315  -0.1166   0.7240   0.4762
  -3.000   0.1728   0.04156   0.03249  -0.1182   0.7203   0.4874
  -2.750   0.1850   0.04196   0.03280  -0.1166   0.7118   0.4918
  -2.500   0.2132   0.04172   0.03236  -0.1180   0.7062   0.4986
  -2.250   0.2502   0.04118   0.03159  -0.1202   0.7030   0.5048
  -2.000   0.2587   0.04185   0.03222  -0.1182   0.6941   0.5086
  -1.750   0.2860   0.04178   0.03201  -0.1190   0.6888   0.5144
  -1.500   0.3250   0.04127   0.03127  -0.1218   0.6858   0.5213
  -1.250   0.3304   0.04229   0.03228  -0.1196   0.6773   0.5245
  -1.000   0.3531   0.04254   0.03246  -0.1196   0.6719   0.5293
  -0.750   0.3901   0.04219   0.03192  -0.1218   0.6689   0.5361
  -0.500   0.3988   0.04329   0.03299  -0.1206   0.6608   0.5400
  -0.250   0.4180   0.04386   0.03353  -0.1202   0.6551   0.5440
   0.000   0.4500   0.04376   0.03334  -0.1212   0.6521   0.5495
   0.250   0.4897   0.04339   0.03281  -0.1237   0.6499   0.5563
   0.500   0.4805   0.04593   0.03543  -0.1209   0.6386   0.5589
   0.750   0.5098   0.04595   0.03540  -0.1214   0.6354   0.5635
   1.000   0.5446   0.04570   0.03507  -0.1227   0.6332   0.5695
   1.500   0.5673   0.04881   0.03819  -0.1217   0.6188   0.5784
   1.750   0.6002   0.04860   0.03795  -0.1224   0.6165   0.5838
   2.250   0.6231   0.05198   0.04131  -0.1219   0.6019   0.5935
   2.500   0.6704   0.04984   0.03913  -0.1224   0.5989   0.6000
   2.750   0.6655   0.05258   0.04191  -0.1207   0.5863   0.6042
   3.000   0.7034   0.05069   0.03992  -0.1206   0.5761   0.6115
   3.250   0.7702   0.04533   0.03441  -0.1209   0.5662   0.6198
   3.500   0.7806   0.04615   0.03522  -0.1195   0.5532   0.6261
   3.750   0.8147   0.04445   0.03345  -0.1189   0.5417   0.6334
   4.000   0.8612   0.04185   0.03071  -0.1193   0.5310   0.6427
   4.250   0.8652   0.04315   0.03205  -0.1173   0.5173   0.6485
   4.500   0.8788   0.04364   0.03255  -0.1160   0.5050   0.6555
   4.750   0.9134   0.04243   0.03125  -0.1160   0.4955   0.6652
   5.000   0.9095   0.04467   0.03361  -0.1139   0.4823   0.6716
   5.250   0.9182   0.04605   0.03504  -0.1129   0.4714   0.6802
   5.500   0.9354   0.04647   0.03550  -0.1120   0.4620   0.6893
   5.750   0.9324   0.04916   0.03832  -0.1107   0.4495   0.6974
   6.000   0.9397   0.05067   0.03994  -0.1096   0.4382   0.7069
   6.250   0.9511   0.05176   0.04111  -0.1087   0.4268   0.7183
   6.500   0.9471   0.05480   0.04430  -0.1077   0.4130   0.7287
   6.750   0.9476   0.05726   0.04693  -0.1067   0.3998   0.7407
   7.000   0.9538   0.05904   0.04884  -0.1059   0.3877   0.7562
   7.250   0.9653   0.06000   0.04995  -0.1049   0.3764   0.7783
   7.500   0.9666   0.06206   0.05222  -0.1036   0.3633   0.8115
   7.750   0.9638   0.06360   0.05392  -0.1016   0.3513   1.0000
   8.000   0.9794   0.06493   0.05518  -0.1017   0.3401   1.0000
   8.250   0.9968   0.06592   0.05607  -0.1017   0.3295   1.0000
   8.500   1.0087   0.06760   0.05772  -0.1015   0.3184   1.0000
   8.750   1.0234   0.06883   0.05887  -0.1013   0.3088   1.0000
   9.000   1.0374   0.07014   0.06010  -0.1010   0.2999   1.0000
   9.250   1.0490   0.07179   0.06171  -0.1007   0.2921   1.0000
   9.500   1.0605   0.07344   0.06336  -0.1004   0.2853   1.0000
   9.750   1.0728   0.07494   0.06482  -0.1001   0.2799   1.0000
  10.000   1.0809   0.07710   0.06702  -0.0998   0.2740   1.0000
  10.250   1.0909   0.07894   0.06885  -0.0995   0.2683   1.0000
  10.500   1.1024   0.08051   0.07038  -0.0992   0.2634   1.0000
  10.750   1.1088   0.08297   0.07292  -0.0991   0.2584   1.0000
  11.000   1.1164   0.08520   0.07522  -0.0989   0.2536   1.0000
  11.250   1.1256   0.08716   0.07721  -0.0987   0.2494   1.0000
  11.500   1.1363   0.08885   0.07890  -0.0984   0.2458   1.0000
  11.750   1.1413   0.09157   0.08174  -0.0984   0.2419   1.0000
  12.000   1.1466   0.09423   0.08450  -0.0984   0.2381   1.0000
  12.250   1.1531   0.09667   0.08703  -0.0985   0.2345   1.0000
  12.500   1.1610   0.09887   0.08933  -0.0984   0.2314   1.0000
  12.750   1.1704   0.10080   0.09131  -0.0983   0.2289   1.0000
  13.000   1.1741   0.10376   0.09440  -0.0986   0.2258   1.0000
  13.250   1.1744   0.10733   0.09814  -0.0991   0.2221   1.0000
  13.500   1.1761   0.11063   0.10158  -0.0995   0.2182   1.0000
  13.750   1.1807   0.11343   0.10448  -0.0999   0.2150   1.0000
  14.000   1.1884   0.11567   0.10680  -0.1001   0.2123   1.0000
  14.250   1.1883   0.11933   0.11061  -0.1009   0.2082   1.0000
  14.500   1.1774   0.12506   0.11655  -0.1025   0.2022   1.0000
  14.750   1.1783   0.12854   0.12013  -0.1035   0.1966   1.0000
  15.000   1.1783   0.13225   0.12393  -0.1046   0.1910   1.0000
  15.250   1.1602   0.13975   0.13164  -0.1074   0.1843   1.0000
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