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GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 460 AIRFOIL (goe460-il)
Reynolds number: 50,000
Max Cl/Cd: 25.79 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe460-il-50000-n5.txt
Download as CSV file: xf-goe460-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 460 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
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.5747   0.11803   0.10857  -0.0455   1.0000   0.1701
 -14.500  -0.6046   0.10659   0.09710  -0.0489   1.0000   0.1838
 -14.000  -0.6503   0.09328   0.08375  -0.0527   1.0000   0.1995
 -13.750  -0.6101   0.09723   0.08770  -0.0498   1.0000   0.2022
 -13.500  -0.7723   0.07153   0.06183  -0.0583   1.0000   0.2165
 -13.250  -0.6712   0.08252   0.07296  -0.0533   1.0000   0.2194
 -13.000  -0.7353   0.07169   0.06204  -0.0556   1.0000   0.2286
 -12.750  -0.8357   0.05934   0.04944  -0.0557   1.0000   0.2349
 -12.500  -0.7854   0.06207   0.05231  -0.0545   1.0000   0.2413
 -12.250  -0.8355   0.05599   0.04606  -0.0524   1.0000   0.2474
 -12.000  -0.8756   0.05164   0.04155  -0.0490   1.0000   0.2524
 -11.750  -0.8409   0.05229   0.04231  -0.0484   1.0000   0.2586
 -11.500  -0.8574   0.04981   0.03974  -0.0454   1.0000   0.2644
 -11.250  -0.8946   0.04663   0.03634  -0.0403   1.0000   0.2694
 -11.000  -0.8624   0.04692   0.03679  -0.0399   1.0000   0.2757
 -10.750  -0.8696   0.04549   0.03532  -0.0365   1.0000   0.2817
 -10.500  -0.8982   0.04341   0.03307  -0.0307   1.0000   0.2871
 -10.250  -0.8756   0.04335   0.03313  -0.0296   1.0000   0.2934
 -10.000  -0.8827   0.04232   0.03207  -0.0254   1.0000   0.2993
  -9.750  -0.9067   0.04091   0.03051  -0.0191   1.0000   0.3047
  -9.500  -0.8904   0.04069   0.03040  -0.0172   1.0000   0.3106
  -9.250  -0.8969   0.03995   0.02963  -0.0126   1.0000   0.3164
  -9.000  -0.9180   0.03898   0.02854  -0.0059   1.0000   0.3218
  -8.750  -0.9085   0.03868   0.02832  -0.0031   1.0000   0.3277
  -8.500  -0.9146   0.03814   0.02776   0.0018   1.0000   0.3338
  -8.250  -0.9277   0.03732   0.02684   0.0076   1.0000   0.3404
  -8.000  -0.9174   0.03707   0.02668   0.0102   1.0000   0.3470
  -7.750  -0.9210   0.03646   0.02601   0.0147   1.0000   0.3544
  -7.500  -0.9187   0.03601   0.02557   0.0184   1.0000   0.3619
  -7.250  -0.9175   0.03560   0.02515   0.0223   0.9998   0.3712
  -7.000  -0.8858   0.03537   0.02495   0.0206   0.9923   0.3844
  -6.750  -0.8597   0.03499   0.02454   0.0199   0.9839   0.3984
  -6.500  -0.8337   0.03463   0.02410   0.0192   0.9757   0.4128
  -6.250  -0.7985   0.03455   0.02410   0.0175   0.9680   0.4254
  -6.000  -0.7689   0.03425   0.02379   0.0165   0.9598   0.4381
  -5.750  -0.7411   0.03384   0.02329   0.0156   0.9512   0.4521
  -5.500  -0.7090   0.03377   0.02328   0.0147   0.9425   0.4646
  -5.250  -0.6744   0.03363   0.02314   0.0131   0.9346   0.4788
  -5.000  -0.6529   0.03333   0.02279   0.0137   0.9241   0.4925
  -4.750  -0.6182   0.03314   0.02256   0.0121   0.9164   0.5074
  -4.500  -0.5910   0.03311   0.02258   0.0121   0.9059   0.5192
  -4.250  -0.5540   0.03296   0.02240   0.0103   0.8986   0.5339
  -4.000  -0.5410   0.03263   0.02201   0.0125   0.8862   0.5479
  -3.750  -0.4939   0.03270   0.02212   0.0093   0.8801   0.5615
  -3.500  -0.4737   0.03263   0.02205   0.0106   0.8681   0.5736
  -3.250  -0.4373   0.03234   0.02170   0.0089   0.8613   0.5883
  -3.000  -0.4114   0.03249   0.02190   0.0095   0.8495   0.5991
  -2.750  -0.3693   0.03236   0.02176   0.0071   0.8431   0.6124
  -2.500  -0.3556   0.03225   0.02163   0.0096   0.8306   0.6254
  -2.250  -0.3032   0.03244   0.02187   0.0058   0.8248   0.6370
  -2.000  -0.2809   0.03250   0.02194   0.0070   0.8139   0.6504
  -1.750  -0.2485   0.03248   0.02191   0.0066   0.8057   0.6661
  -1.500  -0.1802   0.03295   0.02244   0.0007   0.8018   0.6786
  -1.250  -0.1658   0.03327   0.02279   0.0033   0.7883   0.6907
  -1.000  -0.1257   0.03304   0.02253   0.0015   0.7823   0.7046
  -0.750  -0.0956   0.03354   0.02307   0.0015   0.7699   0.7121
  -0.500  -0.0624   0.03314   0.02263   0.0007   0.7631   0.7243
  -0.250  -0.0315   0.03355   0.02308   0.0004   0.7509   0.7317
   0.000  -0.0001   0.03316   0.02265   0.0000   0.7437   0.7437
   0.250   0.0313   0.03355   0.02308  -0.0004   0.7317   0.7509
   0.500   0.0621   0.03314   0.02263  -0.0007   0.7243   0.7631
   0.750   0.0955   0.03353   0.02307  -0.0015   0.7122   0.7699
   1.000   0.1253   0.03303   0.02253  -0.0015   0.7046   0.7823
   1.250   0.1655   0.03328   0.02280  -0.0032   0.6907   0.7883
   1.500   0.1805   0.03295   0.02244  -0.0007   0.6786   0.8018
   1.750   0.2486   0.03247   0.02190  -0.0066   0.6660   0.8057
   2.000   0.2806   0.03251   0.02195  -0.0070   0.6505   0.8140
   2.250   0.3031   0.03244   0.02187  -0.0058   0.6370   0.8248
   2.500   0.3557   0.03225   0.02162  -0.0096   0.6255   0.8306
   2.750   0.3692   0.03237   0.02177  -0.0071   0.6125   0.8431
   3.000   0.4114   0.03249   0.02190  -0.0095   0.5992   0.8496
   3.250   0.4372   0.03233   0.02170  -0.0089   0.5883   0.8613
   3.500   0.4738   0.03262   0.02204  -0.0106   0.5735   0.8681
   3.750   0.4940   0.03270   0.02211  -0.0093   0.5615   0.8801
   4.000   0.5409   0.03263   0.02201  -0.0125   0.5479   0.8862
   4.250   0.5541   0.03295   0.02239  -0.0103   0.5338   0.8986
   4.500   0.5911   0.03310   0.02257  -0.0122   0.5192   0.9060
   4.750   0.6184   0.03313   0.02256  -0.0121   0.5072   0.9165
   5.000   0.6531   0.03332   0.02279  -0.0137   0.4926   0.9242
   5.250   0.6747   0.03362   0.02313  -0.0131   0.4787   0.9347
   5.500   0.7092   0.03376   0.02327  -0.0147   0.4647   0.9426
   5.750   0.7414   0.03383   0.02328  -0.0157   0.4521   0.9513
   6.000   0.7691   0.03424   0.02378  -0.0165   0.4381   0.9599
   6.250   0.7987   0.03454   0.02409  -0.0175   0.4253   0.9681
   6.500   0.8337   0.03462   0.02410  -0.0192   0.4127   0.9758
   6.750   0.8601   0.03497   0.02451  -0.0200   0.3982   0.9840
   7.000   0.8862   0.03536   0.02493  -0.0207   0.3843   0.9924
   7.250   0.9180   0.03559   0.02514  -0.0224   0.3711   0.9999
   7.500   0.9190   0.03601   0.02557  -0.0185   0.3621   1.0000
   7.750   0.9212   0.03645   0.02599  -0.0147   0.3544   1.0000
   8.000   0.9175   0.03706   0.02666  -0.0102   0.3469   1.0000
   8.250   0.9278   0.03732   0.02683  -0.0076   0.3404   1.0000
   8.500   0.9151   0.03813   0.02775  -0.0019   0.3339   1.0000
   8.750   0.9090   0.03867   0.02831   0.0030   0.3277   1.0000
   9.000   0.9178   0.03897   0.02853   0.0059   0.3217   1.0000
   9.250   0.8973   0.03994   0.02961   0.0125   0.3164   1.0000
   9.500   0.8908   0.04067   0.03037   0.0172   0.3106   1.0000
   9.750   0.9071   0.04089   0.03048   0.0190   0.3046   1.0000
  10.000   0.8831   0.04230   0.03204   0.0253   0.2993   1.0000
  10.250   0.8763   0.04332   0.03310   0.0295   0.2934   1.0000
  10.500   0.8980   0.04340   0.03305   0.0307   0.2870   1.0000
  10.750   0.8704   0.04546   0.03528   0.0364   0.2817   1.0000
  11.000   0.8632   0.04686   0.03673   0.0399   0.2756   1.0000
  11.250   0.8946   0.04662   0.03634   0.0403   0.2694   1.0000
  11.500   0.8578   0.04978   0.03971   0.0453   0.2643   1.0000
  11.750   0.8419   0.05223   0.04225   0.0483   0.2586   1.0000
  12.000   0.8775   0.05154   0.04144   0.0489   0.2524   1.0000
  12.250   0.8367   0.05592   0.04599   0.0524   0.2474   1.0000
  12.500   0.7870   0.06196   0.05219   0.0544   0.2412   1.0000
  12.750   0.8385   0.05914   0.04923   0.0556   0.2348   1.0000
  13.000   0.7444   0.07068   0.06102   0.0558   0.2288   1.0000
  13.250   0.6747   0.08211   0.07255   0.0534   0.2195   1.0000
  13.500   0.7742   0.07139   0.06169   0.0582   0.2165   1.0000
  13.750   0.6119   0.09707   0.08754   0.0497   0.2022   1.0000
  14.000   0.6537   0.09288   0.08335   0.0527   0.1996   1.0000
  14.500   0.6064   0.10648   0.09699   0.0488   0.1838   1.0000
  15.000   0.5766   0.11794   0.10847   0.0454   0.1701   1.0000
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