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GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il)
Reynolds number: 100,000
Max Cl/Cd: 45.24 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe229-il-100000.txt
Download as CSV file: xf-goe229-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1330   0.11093   0.10677  -0.0850   0.9441   0.1837
  -9.500  -0.0930   0.10667   0.10245  -0.0871   0.9413   0.1881
  -9.250  -0.3382   0.06981   0.06550  -0.1135   0.9167   0.0876
  -9.000  -0.3497   0.06283   0.05828  -0.1211   0.9067   0.0846
  -8.750  -0.3707   0.05753   0.05256  -0.1241   0.8938   0.0814
  -8.500  -0.3664   0.05230   0.04615  -0.1304   0.8846   0.0771
  -8.250  -0.3464   0.04888   0.04245  -0.1316   0.8766   0.0763
  -8.000  -0.3081   0.04480   0.03796  -0.1357   0.8731   0.0757
  -7.750  -0.2933   0.04299   0.03583  -0.1351   0.8630   0.0760
  -7.500  -0.2557   0.04025   0.03273  -0.1381   0.8584   0.0778
  -7.250  -0.2105   0.03769   0.03008  -0.1414   0.8559   0.0798
  -7.000  -0.1976   0.03686   0.02920  -0.1393   0.8449   0.0808
  -6.750  -0.1542   0.03527   0.02752  -0.1419   0.8413   0.0845
  -6.500  -0.1065   0.03376   0.02587  -0.1447   0.8390   0.0886
  -6.250  -0.0950   0.03348   0.02558  -0.1421   0.8272   0.0901
  -6.000  -0.0566   0.03210   0.02443  -0.1433   0.8240   0.0952
  -5.750  -0.0379   0.03186   0.02420  -0.1421   0.8146   0.1006
  -5.500  -0.0032   0.03092   0.02327  -0.1433   0.8092   0.1078
  -5.250   0.0425   0.02933   0.02165  -0.1472   0.8064   0.1229
  -5.000   0.0672   0.02740   0.02052  -0.1504   0.7960   0.2321
  -4.750   0.1055   0.02858   0.02198  -0.1504   0.7915   0.3930
  -4.500   0.1244   0.03019   0.02365  -0.1473   0.7832   0.4146
  -4.250   0.1478   0.03160   0.02509  -0.1445   0.7764   0.4337
  -4.000   0.1832   0.03216   0.02557  -0.1439   0.7734   0.4491
  -3.750   0.1965   0.03287   0.02613  -0.1424   0.7626   0.4612
  -3.500   0.2233   0.03382   0.02719  -0.1393   0.7586   0.4726
  -3.250   0.2571   0.03416   0.02749  -0.1381   0.7559   0.4865
  -3.000   0.2618   0.03516   0.02845  -0.1354   0.7443   0.4980
  -2.750   0.2922   0.03556   0.02881  -0.1340   0.7412   0.5146
  -2.500   0.2915   0.03696   0.03032  -0.1286   0.7318   0.5210
  -2.250   0.3251   0.03652   0.02971  -0.1305   0.7270   0.5324
  -2.000   0.3617   0.03586   0.02896  -0.1314   0.7243   0.5371
  -1.750   0.3658   0.03686   0.02995  -0.1294   0.7146   0.5417
  -1.500   0.4038   0.03628   0.02915  -0.1330   0.7104   0.5489
  -1.250   0.4390   0.03572   0.02855  -0.1337   0.7079   0.5530
  -1.000   0.4362   0.03729   0.03015  -0.1307   0.6980   0.5566
  -0.750   0.4790   0.03637   0.02906  -0.1337   0.6938   0.5636
  -0.500   0.5359   0.03428   0.02682  -0.1372   0.6912   0.5692
  -0.250   0.5457   0.03501   0.02756  -0.1351   0.6822   0.5731
   0.000   0.6109   0.03218   0.02447  -0.1398   0.6760   0.5806
   0.250   0.6533   0.03041   0.02254  -0.1411   0.6654   0.5858
   0.500   0.7090   0.02800   0.01985  -0.1438   0.6553   0.5920
   0.750   0.7279   0.02796   0.01980  -0.1430   0.6442   0.5968
   1.000   0.7650   0.02715   0.01882  -0.1446   0.6361   0.6021
   1.250   0.7896   0.02677   0.01842  -0.1438   0.6262   0.6066
   1.500   0.8172   0.02638   0.01796  -0.1438   0.6165   0.6121
   1.750   0.8538   0.02572   0.01710  -0.1456   0.6072   0.6180
   2.000   0.8725   0.02567   0.01711  -0.1442   0.5976   0.6219
   2.250   0.9062   0.02516   0.01647  -0.1450   0.5897   0.6279
   2.500   0.9263   0.02527   0.01659  -0.1443   0.5799   0.6339
   2.750   0.9566   0.02489   0.01612  -0.1447   0.5718   0.6390
   3.000   0.9755   0.02494   0.01622  -0.1434   0.5619   0.6440
   3.250   1.0020   0.02481   0.01600  -0.1435   0.5523   0.6509
   3.500   1.0243   0.02468   0.01584  -0.1426   0.5419   0.6566
   3.750   1.0427   0.02475   0.01594  -0.1413   0.5311   0.6632
   4.000   1.0672   0.02469   0.01578  -0.1411   0.5208   0.6701
   4.250   1.0839   0.02483   0.01599  -0.1395   0.5109   0.6761
   4.500   1.1066   0.02496   0.01609  -0.1391   0.5029   0.6842
   4.750   1.1227   0.02513   0.01633  -0.1374   0.4937   0.6913
   5.000   1.1396   0.02535   0.01655  -0.1361   0.4845   0.7004
   5.250   1.1546   0.02555   0.01681  -0.1343   0.4759   0.7085
   5.500   1.1709   0.02592   0.01724  -0.1330   0.4673   0.7182
   5.750   1.1870   0.02624   0.01761  -0.1316   0.4586   0.7277
   6.000   1.2012   0.02674   0.01819  -0.1301   0.4497   0.7388
   6.250   1.2170   0.02717   0.01865  -0.1288   0.4408   0.7520
   6.500   1.2286   0.02782   0.01945  -0.1271   0.4313   0.7665
   6.750   1.2418   0.02835   0.02006  -0.1255   0.4223   0.7836
   7.000   1.2518   0.02906   0.02094  -0.1236   0.4120   0.8048
   7.250   1.2609   0.02968   0.02175  -0.1216   0.4020   0.8411
   7.500   1.2647   0.03030   0.02252  -0.1189   0.3912   1.0000
   7.750   1.2780   0.03154   0.02370  -0.1186   0.3775   1.0000
   8.000   1.2888   0.03287   0.02495  -0.1177   0.3633   1.0000
   8.250   1.2974   0.03431   0.02631  -0.1166   0.3491   1.0000
   8.500   1.3044   0.03587   0.02780  -0.1153   0.3357   1.0000
   8.750   1.3103   0.03755   0.02944  -0.1140   0.3239   1.0000
   9.000   1.3149   0.03937   0.03121  -0.1126   0.3134   1.0000
   9.250   1.3202   0.04121   0.03304  -0.1114   0.3041   1.0000
   9.500   1.3241   0.04318   0.03499  -0.1101   0.2963   1.0000
   9.750   1.3293   0.04513   0.03696  -0.1090   0.2890   1.0000
  10.000   1.3332   0.04720   0.03903  -0.1079   0.2828   1.0000
  10.250   1.3388   0.04918   0.04106  -0.1069   0.2774   1.0000
  10.500   1.3434   0.05129   0.04321  -0.1060   0.2716   1.0000
  10.750   1.3460   0.05359   0.04548  -0.1049   0.2655   1.0000
  11.000   1.3493   0.05595   0.04788  -0.1041   0.2584   1.0000
  11.250   1.3496   0.05857   0.05048  -0.1032   0.2510   1.0000
  11.500   1.3512   0.06119   0.05313  -0.1025   0.2435   1.0000
  11.750   1.3516   0.06394   0.05588  -0.1018   0.2361   1.0000
  12.000   1.3545   0.06648   0.05847  -0.1013   0.2300   1.0000
  12.250   1.3576   0.06905   0.06110  -0.1008   0.2242   1.0000
  12.500   1.3612   0.07151   0.06358  -0.1003   0.2197   1.0000
  12.750   1.3654   0.07402   0.06617  -0.0999   0.2147   1.0000
  13.000   1.3672   0.07686   0.06909  -0.0997   0.2085   1.0000
  13.250   1.3672   0.07988   0.07213  -0.0994   0.2021   1.0000
  13.500   1.3697   0.08277   0.07515  -0.0993   0.1955   1.0000
  13.750   1.3719   0.08562   0.07807  -0.0992   0.1904   1.0000
  14.000   1.3748   0.08841   0.08097  -0.0991   0.1855   1.0000
  14.250   1.3772   0.09135   0.08404  -0.0992   0.1787   1.0000
  14.500   1.3779   0.09454   0.08733  -0.0993   0.1708   1.0000
  14.750   1.3777   0.09787   0.09075  -0.0995   0.1579   1.0000
  15.000   1.3697   0.10226   0.09509  -0.1000   0.1414   1.0000
  15.250   1.3591   0.10707   0.09979  -0.1006   0.1321   1.0000
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