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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 500,000
Max Cl/Cd: 114.08 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe81-il-500000.txt
Download as CSV file: xf-goe81-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2506   0.10456   0.10234  -0.0316   1.0000   0.0170
  -8.750  -0.2482   0.10238   0.10020  -0.0314   1.0000   0.0174
  -8.500  -0.2478   0.10041   0.09828  -0.0308   0.9995   0.0177
  -8.250  -0.2287   0.09660   0.09446  -0.0355   0.9953   0.0185
  -8.000  -0.2074   0.09290   0.09076  -0.0424   0.9869   0.0191
  -7.750  -0.1855   0.08920   0.08705  -0.0517   0.9726   0.0193
  -7.500  -0.0781   0.06777   0.06560  -0.0598   0.9217   0.0198
  -7.250  -0.0713   0.06503   0.06280  -0.0604   0.9078   0.0201
  -7.000  -0.0648   0.06235   0.06007  -0.0611   0.8953   0.0204
  -6.750  -0.0578   0.05958   0.05725  -0.0624   0.8837   0.0209
  -6.500  -0.0471   0.05649   0.05413  -0.0648   0.8722   0.0215
  -6.250  -0.0323   0.05319   0.05078  -0.0689   0.8615   0.0226
  -6.000  -0.0538   0.06550   0.06301  -0.0756   0.8865   0.0221
  -5.750  -0.0111   0.06164   0.05901  -0.0879   0.8745   0.0229
  -5.500   0.0228   0.05787   0.05508  -0.0950   0.8639   0.0230
  -5.250   0.0385   0.05418   0.05135  -0.0960   0.8535   0.0232
  -5.000   0.0546   0.05160   0.04875  -0.0961   0.8429   0.0234
  -4.750   0.0755   0.04922   0.04630  -0.0975   0.8328   0.0238
  -4.500   0.1008   0.04676   0.04376  -0.1000   0.8217   0.0244
  -4.250   0.1293   0.04414   0.04104  -0.1031   0.8096   0.0252
  -4.000   0.1613   0.04142   0.03818  -0.1065   0.7981   0.0265
  -3.750   0.2121   0.03841   0.03481  -0.1126   0.7876   0.0275
  -3.500   0.2377   0.03495   0.03122  -0.1146   0.7761   0.0278
  -3.250   0.2599   0.03297   0.02917  -0.1154   0.7643   0.0281
  -3.000   0.2857   0.03122   0.02732  -0.1164   0.7537   0.0286
  -2.750   0.3139   0.02947   0.02543  -0.1176   0.7441   0.0294
  -2.500   0.3440   0.02766   0.02348  -0.1189   0.7350   0.0306
  -2.250   0.3848   0.02603   0.02141  -0.1199   0.7272   0.0329
  -2.000   0.4125   0.02309   0.01832  -0.1213   0.7182   0.0335
  -1.750   0.4386   0.02181   0.01695  -0.1219   0.7090   0.0341
  -1.500   0.4657   0.02078   0.01581  -0.1223   0.6997   0.0351
  -1.250   0.4946   0.01965   0.01454  -0.1227   0.6911   0.0368
  -1.000   0.5275   0.01944   0.01393  -0.1223   0.6831   0.0398
  -0.750   0.5555   0.01695   0.01132  -0.1233   0.6760   0.0413
  -0.500   0.5830   0.01618   0.01048  -0.1235   0.6684   0.0428
  -0.250   0.6117   0.01562   0.00976  -0.1235   0.6609   0.0465
   0.000   0.6406   0.01463   0.00855  -0.1237   0.6523   0.0509
   0.250   0.6682   0.01411   0.00798  -0.1238   0.6432   0.0542
   1.750   0.8372   0.01108   0.00416  -0.1225   0.5860   0.0477
   2.000   0.8649   0.01053   0.00358  -0.1223   0.5739   0.0447
   2.250   0.8922   0.01029   0.00329  -0.1220   0.5595   0.0438
   2.500   0.9191   0.01018   0.00315  -0.1218   0.5422   0.0448
   2.750   0.9457   0.01014   0.00305  -0.1215   0.5216   0.0458
   3.000   0.9715   0.01019   0.00298  -0.1211   0.4939   0.0457
   3.250   0.9968   0.01035   0.00299  -0.1206   0.4671   0.0464
   3.500   1.0223   0.01054   0.00307  -0.1202   0.4482   0.0477
   4.000   1.0743   0.01087   0.00329  -0.1196   0.4221   0.0585
   4.250   1.0963   0.00961   0.00363  -0.1188   0.4127   1.0000
   4.500   1.1220   0.00987   0.00380  -0.1184   0.4032   1.0000
   4.750   1.1482   0.01007   0.00397  -0.1182   0.3933   1.0000
   5.000   1.1739   0.01032   0.00416  -0.1178   0.3824   1.0000
   5.250   1.1993   0.01057   0.00436  -0.1175   0.3720   1.0000
   5.500   1.2252   0.01078   0.00456  -0.1172   0.3609   1.0000
   5.750   1.2506   0.01102   0.00476  -0.1168   0.3495   1.0000
   6.000   1.2757   0.01128   0.00498  -0.1164   0.3374   1.0000
   6.250   1.3005   0.01156   0.00522  -0.1160   0.3248   1.0000
   6.500   1.3250   0.01186   0.00548  -0.1155   0.3082   1.0000
   6.750   1.3485   0.01223   0.00577  -0.1149   0.2865   1.0000
   7.000   1.3709   0.01270   0.00612  -0.1142   0.2642   1.0000
   7.250   1.3928   0.01321   0.00651  -0.1134   0.2395   1.0000
   7.500   1.4134   0.01381   0.00699  -0.1124   0.2125   1.0000
   7.750   1.4326   0.01452   0.00753  -0.1112   0.1821   1.0000
   8.000   1.4499   0.01538   0.00818  -0.1098   0.1501   1.0000
   8.250   1.4690   0.01604   0.00876  -0.1086   0.1356   1.0000
   8.500   1.4884   0.01665   0.00934  -0.1074   0.1263   1.0000
   8.750   1.5085   0.01716   0.00987  -0.1063   0.1192   1.0000
   9.000   1.5273   0.01775   0.01045  -0.1051   0.1126   1.0000
   9.250   1.5469   0.01824   0.01097  -0.1040   0.1063   1.0000
   9.500   1.5639   0.01889   0.01160  -0.1025   0.0964   1.0000
   9.750   1.5785   0.01965   0.01223  -0.1007   0.0700   1.0000
  10.000   1.5852   0.02074   0.01321  -0.0976   0.0562   1.0000
  10.250   1.5962   0.02159   0.01409  -0.0952   0.0489   1.0000
  10.500   1.6052   0.02260   0.01511  -0.0926   0.0400   1.0000
  11.000   1.6129   0.02549   0.01789  -0.0869   0.0200   1.0000
  11.250   1.6185   0.02694   0.01941  -0.0846   0.0181   1.0000
  11.500   1.6255   0.02835   0.02092  -0.0826   0.0172   1.0000
  11.750   1.6310   0.02994   0.02262  -0.0807   0.0165   1.0000
  12.000   1.6347   0.03175   0.02455  -0.0788   0.0159   1.0000
  12.250   1.6362   0.03385   0.02676  -0.0770   0.0154   1.0000
  12.500   1.6348   0.03632   0.02934  -0.0752   0.0149   1.0000
  12.750   1.6302   0.03923   0.03238  -0.0736   0.0145   1.0000
  13.000   1.6227   0.04260   0.03589  -0.0723   0.0142   1.0000
  13.250   1.6222   0.04535   0.03875  -0.0714   0.0140   1.0000
  13.500   1.6197   0.04839   0.04192  -0.0706   0.0138   1.0000
  13.750   1.6159   0.05168   0.04533  -0.0701   0.0136   1.0000
  14.000   1.6109   0.05522   0.04900  -0.0697   0.0134   1.0000
  14.250   1.6050   0.05896   0.05285  -0.0694   0.0132   1.0000
  14.500   1.5984   0.06291   0.05693  -0.0694   0.0129   1.0000
  14.750   1.5910   0.06708   0.06122  -0.0696   0.0127   1.0000
  15.000   1.5831   0.07141   0.06566  -0.0699   0.0125   1.0000
  15.250   1.5746   0.07592   0.07028  -0.0704   0.0123   1.0000
  15.500   1.5659   0.08059   0.07505  -0.0711   0.0121   1.0000
  15.750   1.5571   0.08534   0.07991  -0.0719   0.0119   1.0000
  16.000   1.5480   0.09018   0.08484  -0.0728   0.0118   1.0000
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