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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 50,000
Max Cl/Cd: 44.49 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe394-il-50000-n5.txt
Download as CSV file: xf-goe394-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2961   0.11020   0.10357  -0.0258   1.0000   0.0834
  -8.000  -0.2977   0.10942   0.10291  -0.0278   1.0000   0.0841
  -7.750  -0.2990   0.10876   0.10240  -0.0304   1.0000   0.0845
  -7.500  -0.2854   0.10219   0.09584  -0.0272   1.0000   0.0867
  -7.250  -0.2827   0.09966   0.09340  -0.0263   1.0000   0.0889
  -7.000  -0.2869   0.09816   0.09202  -0.0251   1.0000   0.0905
  -6.750  -0.2959   0.09719   0.09116  -0.0232   1.0000   0.0916
  -6.500  -0.3060   0.09636   0.09042  -0.0212   1.0000   0.0927
  -6.250  -0.3070   0.09493   0.08904  -0.0221   0.9979   0.0943
  -6.000  -0.2777   0.09216   0.08619  -0.0330   0.9879   0.0963
  -5.750  -0.2520   0.08835   0.08234  -0.0403   0.9804   0.0973
  -5.500  -0.2396   0.08368   0.07765  -0.0378   0.9765   0.1011
  -5.250  -0.2146   0.08044   0.07435  -0.0433   0.9694   0.1061
  -5.000  -0.1706   0.07736   0.07107  -0.0565   0.9627   0.1092
  -4.750  -0.1416   0.07389   0.06749  -0.0629   0.9559   0.1098
  -4.500  -0.1294   0.06975   0.06339  -0.0608   0.9518   0.1128
  -4.250  -0.0800   0.06737   0.06071  -0.0733   0.9456   0.1229
  -4.000  -0.0641   0.06348   0.05684  -0.0730   0.9405   0.1246
  -3.500   0.0287   0.05349   0.04618  -0.0902   0.9320   0.0841
  -3.250   0.0523   0.05120   0.04387  -0.0915   0.9261   0.0874
  -3.000   0.0940   0.04828   0.04073  -0.0969   0.9214   0.0903
  -2.750   0.1512   0.04358   0.03537  -0.1062   0.9154   0.0845
  -2.500   0.1908   0.04075   0.03227  -0.1101   0.9084   0.0840
  -2.250   0.2351   0.03782   0.02893  -0.1147   0.9021   0.0840
  -2.000   0.2728   0.03541   0.02610  -0.1175   0.8941   0.0849
  -1.750   0.3086   0.03410   0.02468  -0.1196   0.8878   0.0891
  -1.500   0.3431   0.03251   0.02259  -0.1213   0.8797   0.0958
  -1.250   0.3821   0.03089   0.02067  -0.1236   0.8744   0.0999
  -1.000   0.4107   0.02979   0.01926  -0.1240   0.8656   0.1044
  -0.750   0.4488   0.02837   0.01742  -0.1255   0.8599   0.1125
  -0.500   0.4759   0.02772   0.01656  -0.1255   0.8508   0.1256
  -0.250   0.5105   0.02714   0.01584  -0.1264   0.8444   0.1478
   0.000   0.5376   0.02688   0.01543  -0.1263   0.8346   0.1690
   0.250   0.5692   0.02644   0.01477  -0.1265   0.8266   0.1817
   0.500   0.5990   0.02607   0.01434  -0.1264   0.8178   0.1927
   0.750   0.6269   0.02584   0.01401  -0.1260   0.8080   0.2003
   1.000   0.6585   0.02545   0.01355  -0.1258   0.8002   0.2063
   1.250   0.6839   0.02539   0.01344  -0.1250   0.7888   0.2127
   1.500   0.7105   0.02526   0.01336  -0.1244   0.7783   0.2234
   1.750   0.7403   0.02496   0.01310  -0.1238   0.7696   0.2353
   2.000   0.7649   0.02495   0.01319  -0.1229   0.7572   0.2467
   2.250   0.7904   0.02490   0.01326  -0.1221   0.7451   0.2652
   2.500   0.8166   0.02467   0.01336  -0.1213   0.7335   0.3185
   3.000   0.8678   0.02391   0.01337  -0.1191   0.7098   1.0000
   3.250   0.8920   0.02421   0.01361  -0.1180   0.6959   1.0000
   3.500   0.9161   0.02450   0.01389  -0.1170   0.6818   1.0000
   3.750   0.9399   0.02481   0.01420  -0.1160   0.6675   1.0000
   4.000   0.9636   0.02512   0.01453  -0.1149   0.6530   1.0000
   4.250   0.9872   0.02543   0.01489  -0.1139   0.6385   1.0000
   4.500   1.0107   0.02575   0.01529  -0.1129   0.6243   1.0000
   4.750   1.0344   0.02605   0.01566  -0.1119   0.6103   1.0000
   5.000   1.0583   0.02635   0.01604  -0.1110   0.5969   1.0000
   5.250   1.0827   0.02660   0.01640  -0.1100   0.5841   1.0000
   5.500   1.1077   0.02682   0.01671  -0.1090   0.5720   1.0000
   5.750   1.1329   0.02695   0.01691  -0.1079   0.5590   1.0000
   6.000   1.1575   0.02705   0.01707  -0.1066   0.5437   1.0000
   6.250   1.1813   0.02713   0.01721  -0.1051   0.5252   1.0000
   6.500   1.2054   0.02714   0.01719  -0.1035   0.5045   1.0000
   6.750   1.2265   0.02757   0.01766  -0.1019   0.4829   1.0000
   7.000   1.2477   0.02811   0.01830  -0.1005   0.4639   1.0000
   7.250   1.2690   0.02871   0.01908  -0.0992   0.4462   1.0000
   7.500   1.2896   0.02933   0.01981  -0.0977   0.4277   1.0000
   7.750   1.3075   0.03009   0.02077  -0.0961   0.4072   1.0000
   8.000   1.3242   0.03086   0.02173  -0.0943   0.3847   1.0000
   8.250   1.3382   0.03172   0.02277  -0.0922   0.3588   1.0000
   8.500   1.3493   0.03268   0.02385  -0.0899   0.3284   1.0000
   8.750   1.3551   0.03384   0.02504  -0.0871   0.2900   1.0000
   9.000   1.3561   0.03541   0.02644  -0.0841   0.2457   1.0000
   9.250   1.3528   0.03742   0.02815  -0.0810   0.2045   1.0000
   9.500   1.3484   0.03984   0.03031  -0.0783   0.1712   1.0000
   9.750   1.3433   0.04262   0.03287  -0.0761   0.1461   1.0000
  10.000   1.3388   0.04560   0.03578  -0.0743   0.1255   1.0000
  10.250   1.3333   0.04884   0.03899  -0.0726   0.1091   1.0000
  10.500   1.3278   0.05224   0.04240  -0.0713   0.0945   1.0000
  10.750   1.3231   0.05567   0.04588  -0.0701   0.0824   1.0000
  11.000   1.3192   0.05911   0.04938  -0.0690   0.0737   1.0000
  11.250   1.3156   0.06253   0.05284  -0.0681   0.0669   1.0000
  11.500   1.3145   0.06579   0.05624  -0.0671   0.0609   1.0000
  11.750   1.3126   0.06914   0.05974  -0.0665   0.0562   1.0000
  12.000   1.3113   0.07246   0.06306  -0.0656   0.0530   1.0000
  12.250   1.3163   0.07530   0.06619  -0.0642   0.0496   1.0000
  12.500   1.3178   0.07850   0.06959  -0.0634   0.0468   1.0000
  12.750   1.3172   0.08189   0.07304  -0.0630   0.0444   1.0000
  13.000   1.3184   0.08524   0.07647  -0.0623   0.0423   1.0000
  13.250   1.3173   0.08933   0.08094  -0.0621   0.0407   1.0000
  13.500   1.3140   0.09381   0.08574  -0.0623   0.0396   1.0000
  13.750   1.3073   0.09889   0.09110  -0.0631   0.0389   1.0000
  14.000   1.2973   0.10461   0.09710  -0.0648   0.0385   1.0000
  14.250   1.2844   0.11107   0.10382  -0.0673   0.0383   1.0000
  14.500   1.2689   0.11842   0.11142  -0.0708   0.0382   1.0000
  14.750   1.2507   0.12691   0.12016  -0.0755   0.0384   1.0000
  15.000   1.2293   0.13693   0.13040  -0.0816   0.0388   1.0000
  15.250   1.2066   0.14841   0.14204  -0.0889   0.0394   1.0000
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