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GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 384 AIRFOIL (goe384-il)
Reynolds number: 200,000
Max Cl/Cd: 63.43 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe384-il-200000.txt
Download as CSV file: xf-goe384-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 384 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0117   0.10430   0.10006  -0.0881   0.7950   0.0745
 -10.250   0.0200   0.10170   0.09744  -0.0891   0.7869   0.0761
 -10.000  -0.0153   0.09652   0.09225  -0.0995   0.7804   0.0800
  -9.750   0.0016   0.09351   0.08916  -0.0976   0.7748   0.0806
  -9.500   0.0219   0.09149   0.08712  -0.0962   0.7667   0.0813
  -9.250   0.0360   0.08941   0.08498  -0.0958   0.7602   0.0824
  -9.000   0.0454   0.08702   0.08254  -0.0965   0.7547   0.0841
  -8.750  -0.0175   0.07717   0.07274  -0.1166   0.7497   0.0892
  -8.500   0.0178   0.07647   0.07203  -0.1099   0.7442   0.0897
  -8.250   0.0373   0.07500   0.07048  -0.1074   0.7396   0.0904
  -8.000   0.0522   0.07314   0.06861  -0.1069   0.7342   0.0914
  -7.750   0.0619   0.07074   0.06620  -0.1079   0.7287   0.0930
  -7.500   0.0039   0.05997   0.05505  -0.1252   0.7253   0.0997
  -7.250   0.0276   0.05784   0.05297  -0.1240   0.7211   0.1005
  -7.000   0.0475   0.05649   0.05168  -0.1230   0.7160   0.1015
  -6.750   0.0638   0.05487   0.05006  -0.1228   0.7113   0.1032
  -6.500   0.0522   0.04936   0.04394  -0.1273   0.7080   0.1116
  -6.250   0.0738   0.04707   0.04171  -0.1271   0.7046   0.1127
  -6.000   0.0936   0.04538   0.04001  -0.1270   0.7011   0.1142
  -5.750   0.0860   0.03564   0.02879  -0.1269   0.6983   0.0895
  -5.500   0.1097   0.03354   0.02678  -0.1270   0.6940   0.0878
  -5.250   0.1306   0.03127   0.02428  -0.1267   0.6902   0.0861
  -5.000   0.1512   0.02842   0.02092  -0.1260   0.6869   0.0829
  -4.750   0.1751   0.02662   0.01869  -0.1255   0.6836   0.0822
  -4.500   0.1993   0.02568   0.01764  -0.1251   0.6795   0.0831
  -4.250   0.2248   0.02491   0.01674  -0.1249   0.6752   0.0847
  -4.000   0.2515   0.02406   0.01566  -0.1247   0.6711   0.0862
  -3.750   0.2796   0.02325   0.01457  -0.1246   0.6673   0.0873
  -3.500   0.3059   0.02271   0.01384  -0.1243   0.6630   0.0886
  -3.250   0.3315   0.02195   0.01305  -0.1241   0.6583   0.0905
  -3.000   0.3588   0.02150   0.01259  -0.1241   0.6539   0.0930
  -2.750   0.3877   0.02108   0.01206  -0.1242   0.6498   0.0956
  -2.500   0.4155   0.02079   0.01164  -0.1241   0.6454   0.0980
  -2.250   0.4404   0.02035   0.01121  -0.1237   0.6399   0.1006
  -2.000   0.4674   0.01994   0.01084  -0.1236   0.6347   0.1043
  -1.750   0.4967   0.01967   0.01047  -0.1237   0.6302   0.1085
  -1.500   0.5224   0.01940   0.01020  -0.1234   0.6251   0.1122
  -1.250   0.5466   0.01909   0.01001  -0.1229   0.6193   0.1176
  -1.000   0.5741   0.01885   0.00972  -0.1228   0.6139   0.1243
  -0.750   0.6029   0.01853   0.00938  -0.1230   0.6092   0.1337
  -0.500   0.6243   0.01829   0.00930  -0.1220   0.6025   0.1459
  -0.250   0.6499   0.01798   0.00909  -0.1217   0.5962   0.1713
   0.000   0.6738   0.01698   0.00896  -0.1215   0.5913   0.4124
   0.250   0.6832   0.01599   0.00932  -0.1173   0.5853   0.7860
   0.500   0.7431   0.01595   0.00944  -0.1226   0.5776   0.9693
   0.750   0.8188   0.01600   0.00919  -0.1322   0.5712   1.0000
   1.000   0.8329   0.01612   0.00933  -0.1299   0.5633   1.0000
   1.250   0.8540   0.01614   0.00922  -0.1287   0.5569   1.0000
   1.500   0.8776   0.01620   0.00911  -0.1280   0.5516   1.0000
   1.750   0.8930   0.01634   0.00926  -0.1259   0.5436   1.0000
   2.000   0.9152   0.01638   0.00917  -0.1250   0.5378   1.0000
   2.250   0.9363   0.01650   0.00920  -0.1238   0.5319   1.0000
   2.500   0.9545   0.01663   0.00930  -0.1222   0.5246   1.0000
   2.750   0.9782   0.01668   0.00921  -0.1215   0.5192   1.0000
   3.000   0.9977   0.01687   0.00936  -0.1202   0.5126   1.0000
   3.250   1.0182   0.01702   0.00946  -0.1191   0.5062   1.0000
   3.500   1.0436   0.01713   0.00942  -0.1188   0.5015   1.0000
   3.750   1.0629   0.01741   0.00969  -0.1175   0.4955   1.0000
   4.000   1.0841   0.01763   0.00987  -0.1165   0.4899   1.0000
   4.250   1.1095   0.01780   0.00991  -0.1163   0.4853   1.0000
   4.500   1.1305   0.01812   0.01019  -0.1154   0.4801   1.0000
   4.750   1.1504   0.01842   0.01047  -0.1143   0.4748   1.0000
   5.000   1.1745   0.01866   0.01063  -0.1140   0.4703   1.0000
   5.250   1.2020   0.01897   0.01081  -0.1142   0.4662   1.0000
   5.500   1.2192   0.01940   0.01129  -0.1128   0.4617   1.0000
   5.750   1.2405   0.01977   0.01164  -0.1120   0.4574   1.0000
   6.000   1.2655   0.02010   0.01189  -0.1119   0.4537   1.0000
   6.250   1.2978   0.02046   0.01212  -0.1131   0.4500   1.0000
   6.500   1.3110   0.02097   0.01272  -0.1111   0.4461   1.0000
   6.750   1.3291   0.02142   0.01319  -0.1099   0.4421   1.0000
   7.000   1.3519   0.02182   0.01356  -0.1095   0.4385   1.0000
   7.250   1.3819   0.02222   0.01387  -0.1104   0.4353   1.0000
   7.500   1.4096   0.02275   0.01436  -0.1109   0.4321   1.0000
   7.750   1.4195   0.02335   0.01507  -0.1084   0.4290   1.0000
   8.000   1.4347   0.02392   0.01570  -0.1069   0.4257   1.0000
   8.250   1.4554   0.02442   0.01620  -0.1062   0.4225   1.0000
   8.500   1.4832   0.02483   0.01657  -0.1068   0.4194   1.0000
   8.750   1.5245   0.02532   0.01694  -0.1097   0.4163   1.0000
   9.000   1.5276   0.02609   0.01786  -0.1063   0.4137   1.0000
   9.250   1.5343   0.02691   0.01879  -0.1036   0.4108   1.0000
   9.500   1.5473   0.02766   0.01962  -0.1020   0.4079   1.0000
   9.750   1.5667   0.02828   0.02026  -0.1014   0.4051   1.0000
  10.000   1.5947   0.02871   0.02066  -0.1020   0.4023   1.0000
  10.250   1.6360   0.02909   0.02096  -0.1047   0.3995   1.0000
  10.500   1.6402   0.03014   0.02213  -0.1019   0.3970   1.0000
  10.750   1.6351   0.03140   0.02358  -0.0981   0.3943   1.0000
  11.000   1.6364   0.03260   0.02489  -0.0952   0.3912   1.0000
  11.250   1.6496   0.03334   0.02568  -0.0940   0.3878   1.0000
  11.500   1.6842   0.03331   0.02555  -0.0953   0.3842   1.0000
  11.750   1.7116   0.03381   0.02603  -0.0959   0.3805   1.0000
  12.000   1.6853   0.03592   0.02837  -0.0900   0.3769   1.0000
  12.250   1.6770   0.03767   0.03026  -0.0867   0.3734   1.0000
  12.500   1.6884   0.03861   0.03126  -0.0856   0.3702   1.0000
  12.750   1.7172   0.03875   0.03138  -0.0862   0.3675   1.0000
  13.000   1.7636   0.03838   0.03092  -0.0887   0.3649   1.0000
  13.250   1.7365   0.04121   0.03399  -0.0838   0.3619   1.0000
  13.500   1.6976   0.04512   0.03815  -0.0786   0.3581   1.0000
  13.750   1.6854   0.04775   0.04091  -0.0761   0.3545   1.0000
  14.000   1.7058   0.04822   0.04139  -0.0760   0.3518   1.0000
  14.250   1.7515   0.04702   0.04012  -0.0776   0.3494   1.0000
  14.500   1.7567   0.04862   0.04180  -0.0764   0.3462   1.0000
  14.750   1.5924   0.06460   0.05832  -0.0673   0.3378   1.0000
  15.000   1.6253   0.06362   0.05732  -0.0676   0.3355   1.0000
  15.250   1.6920   0.05940   0.05301  -0.0692   0.3337   1.0000
  15.500   1.7743   0.05438   0.04779  -0.0719   0.3310   1.0000
  15.750   1.4568   0.09092   0.08508  -0.0636   0.3141   1.0000
  16.000   1.5109   0.08680   0.08095  -0.0637   0.3138   1.0000
  16.250   1.5796   0.08103   0.07515  -0.0641   0.3135   1.0000
  16.500   1.4443   0.10104   0.09537  -0.0638   0.2992   1.0000
  16.750   1.4957   0.09691   0.09125  -0.0636   0.2989   1.0000
  17.000   1.5597   0.09128   0.08560  -0.0636   0.2985   1.0000
  17.500   1.5011   0.10459   0.09909  -0.0643   0.2843   1.0000
  17.750   1.5826   0.09639   0.09084  -0.0640   0.2846   1.0000
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