Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 526 AIRFOIL (goe526-il)
Reynolds number: 500,000
Max Cl/Cd: 91.8 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe526-il-500000-n5.txt
Download as CSV file: xf-goe526-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 526 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8973   0.03799   0.03439  -0.0968   1.0000   0.0276
 -13.500  -0.9276   0.03580   0.03208  -0.0917   1.0000   0.0276
 -13.250  -0.9208   0.03286   0.02885  -0.0930   0.9948   0.0279
 -13.000  -0.9065   0.03063   0.02643  -0.0940   0.9886   0.0282
 -12.750  -0.8866   0.02894   0.02463  -0.0949   0.9840   0.0285
 -12.500  -0.8655   0.02763   0.02321  -0.0955   0.9794   0.0287
 -12.250  -0.8432   0.02646   0.02194  -0.0959   0.9744   0.0290
 -12.000  -0.8167   0.02531   0.02068  -0.0970   0.9710   0.0293
 -11.750  -0.7924   0.02428   0.01954  -0.0974   0.9656   0.0297
 -11.500  -0.7657   0.02331   0.01845  -0.0982   0.9605   0.0301
 -11.250  -0.7364   0.02237   0.01738  -0.0994   0.9566   0.0306
 -11.000  -0.7124   0.02145   0.01633  -0.0994   0.9495   0.0310
 -10.750  -0.6849   0.02052   0.01524  -0.1000   0.9432   0.0313
 -10.500  -0.6593   0.01970   0.01426  -0.1001   0.9354   0.0317
 -10.250  -0.6327   0.01896   0.01337  -0.1003   0.9267   0.0320
 -10.000  -0.6087   0.01822   0.01252  -0.0999   0.9169   0.0324
  -9.750  -0.5837   0.01753   0.01174  -0.0997   0.9075   0.0328
  -9.500  -0.5602   0.01701   0.01115  -0.0990   0.8964   0.0332
  -9.250  -0.5355   0.01656   0.01062  -0.0985   0.8859   0.0337
  -9.000  -0.5110   0.01614   0.01010  -0.0979   0.8748   0.0341
  -8.750  -0.4870   0.01572   0.00958  -0.0972   0.8645   0.0347
  -8.500  -0.4627   0.01531   0.00906  -0.0965   0.8551   0.0352
  -8.250  -0.4388   0.01491   0.00856  -0.0957   0.8455   0.0357
  -8.000  -0.4144   0.01453   0.00806  -0.0950   0.8369   0.0362
  -7.750  -0.3900   0.01418   0.00761  -0.0942   0.8280   0.0366
  -7.500  -0.3658   0.01380   0.00715  -0.0935   0.8205   0.0372
  -7.250  -0.3414   0.01344   0.00675  -0.0927   0.8133   0.0378
  -7.000  -0.3164   0.01315   0.00640  -0.0921   0.8063   0.0385
  -6.750  -0.2910   0.01289   0.00609  -0.0915   0.7999   0.0393
  -6.500  -0.2655   0.01265   0.00579  -0.0909   0.7932   0.0402
  -6.250  -0.2398   0.01242   0.00548  -0.0904   0.7874   0.0412
  -6.000  -0.2139   0.01219   0.00519  -0.0898   0.7821   0.0420
  -5.750  -0.1888   0.01189   0.00488  -0.0892   0.7754   0.0430
  -5.500  -0.1632   0.01169   0.00462  -0.0886   0.7684   0.0442
  -5.250  -0.1374   0.01149   0.00439  -0.0880   0.7609   0.0456
  -5.000  -0.1115   0.01131   0.00416  -0.0875   0.7538   0.0470
  -4.750  -0.0856   0.01113   0.00393  -0.0869   0.7473   0.0485
  -4.500  -0.0597   0.01094   0.00373  -0.0864   0.7404   0.0504
  -4.250  -0.0337   0.01080   0.00354  -0.0858   0.7334   0.0527
  -4.000  -0.0075   0.01065   0.00337  -0.0853   0.7265   0.0550
  -3.750   0.0184   0.01049   0.00320  -0.0848   0.7192   0.0577
  -3.500   0.0447   0.01038   0.00305  -0.0842   0.7134   0.0607
  -3.250   0.0712   0.01023   0.00291  -0.0838   0.7077   0.0638
  -3.000   0.0975   0.01011   0.00279  -0.0833   0.7019   0.0678
  -2.500   0.1504   0.00989   0.00258  -0.0824   0.6908   0.0783
  -2.250   0.1766   0.00978   0.00249  -0.0819   0.6843   0.0848
  -2.000   0.2029   0.00971   0.00240  -0.0814   0.6786   0.0920
  -1.750   0.2295   0.00962   0.00235  -0.0810   0.6727   0.1012
  -1.500   0.2557   0.00954   0.00231  -0.0805   0.6658   0.1111
  -1.250   0.2820   0.00949   0.00226  -0.0801   0.6592   0.1201
  -1.000   0.3084   0.00944   0.00223  -0.0796   0.6512   0.1292
  -0.750   0.3343   0.00941   0.00219  -0.0790   0.6438   0.1374
  -0.500   0.3608   0.00937   0.00217  -0.0786   0.6357   0.1451
  -0.250   0.3864   0.00935   0.00214  -0.0779   0.6269   0.1534
   0.000   0.4120   0.00933   0.00211  -0.0773   0.6143   0.1613
   0.250   0.4367   0.00933   0.00209  -0.0765   0.5981   0.1702
   0.500   0.4609   0.00936   0.00208  -0.0756   0.5799   0.1807
   0.750   0.4846   0.00938   0.00209  -0.0747   0.5614   0.1961
   1.000   0.5083   0.00940   0.00211  -0.0737   0.5439   0.2187
   1.500   0.5526   0.00935   0.00222  -0.0713   0.5048   0.3209
   1.750   0.5690   0.00900   0.00233  -0.0692   0.4848   0.5092
   2.000   0.5753   0.00829   0.00242  -0.0646   0.4687   0.7910
   2.250   0.6407   0.00850   0.00283  -0.0723   0.4444   0.9521
   2.500   0.6805   0.00877   0.00301  -0.0748   0.4287   0.9680
   2.750   0.7192   0.00902   0.00317  -0.0771   0.4168   0.9769
   3.000   0.7537   0.00924   0.00333  -0.0786   0.4070   0.9838
   3.250   0.7964   0.00943   0.00348  -0.0818   0.3982   0.9906
   3.750   0.8796   0.00981   0.00375  -0.0878   0.3803   0.9997
   4.000   0.9014   0.00999   0.00389  -0.0866   0.3728   1.0000
   4.250   0.9216   0.01013   0.00401  -0.0850   0.3656   1.0000
   4.500   0.9411   0.01029   0.00414  -0.0833   0.3577   1.0000
   4.750   0.9601   0.01047   0.00429  -0.0815   0.3489   1.0000
   5.000   0.9780   0.01068   0.00445  -0.0796   0.3379   1.0000
   5.250   0.9969   0.01086   0.00460  -0.0777   0.3276   1.0000
   5.500   1.0145   0.01108   0.00478  -0.0757   0.3183   1.0000
   5.750   1.0330   0.01127   0.00494  -0.0738   0.3085   1.0000
   6.000   1.0503   0.01150   0.00513  -0.0718   0.2977   1.0000
   6.250   1.0666   0.01177   0.00534  -0.0695   0.2845   1.0000
   6.500   1.0820   0.01207   0.00558  -0.0671   0.2678   1.0000
   6.750   1.0953   0.01245   0.00585  -0.0644   0.2454   1.0000
   7.000   1.1055   0.01291   0.00618  -0.0611   0.2196   1.0000
   7.250   1.1118   0.01343   0.00655  -0.0571   0.1946   1.0000
   7.500   1.1213   0.01389   0.00693  -0.0538   0.1804   1.0000
   7.750   1.1335   0.01430   0.00729  -0.0510   0.1710   1.0000
   8.000   1.1469   0.01470   0.00767  -0.0485   0.1643   1.0000
   8.250   1.1617   0.01508   0.00805  -0.0463   0.1585   1.0000
   8.500   1.1756   0.01553   0.00848  -0.0440   0.1529   1.0000
   8.750   1.1909   0.01593   0.00890  -0.0420   0.1479   1.0000
   9.000   1.2066   0.01634   0.00932  -0.0402   0.1429   1.0000
   9.250   1.2209   0.01684   0.00981  -0.0381   0.1374   1.0000
   9.500   1.2363   0.01730   0.01029  -0.0364   0.1321   1.0000
   9.750   1.2512   0.01782   0.01081  -0.0346   0.1251   1.0000
  10.000   1.2655   0.01838   0.01137  -0.0328   0.1186   1.0000
  10.250   1.2788   0.01903   0.01198  -0.0310   0.1099   1.0000
  10.500   1.2915   0.01973   0.01266  -0.0292   0.1004   1.0000
  10.750   1.3030   0.02053   0.01343  -0.0273   0.0926   1.0000
  11.000   1.3136   0.02142   0.01429  -0.0255   0.0858   1.0000
  11.250   1.3252   0.02227   0.01515  -0.0238   0.0811   1.0000
  11.500   1.3355   0.02324   0.01613  -0.0222   0.0772   1.0000
  11.750   1.3473   0.02415   0.01708  -0.0207   0.0744   1.0000
  12.000   1.3584   0.02514   0.01810  -0.0193   0.0714   1.0000
  12.250   1.3678   0.02627   0.01926  -0.0178   0.0685   1.0000
  12.500   1.3773   0.02743   0.02045  -0.0164   0.0662   1.0000
  12.750   1.3881   0.02853   0.02161  -0.0153   0.0640   1.0000
  13.000   1.3973   0.02978   0.02291  -0.0141   0.0617   1.0000
  13.250   1.4046   0.03121   0.02436  -0.0128   0.0597   1.0000
  13.500   1.4123   0.03264   0.02584  -0.0117   0.0578   1.0000
  13.750   1.4211   0.03401   0.02728  -0.0108   0.0558   1.0000
  14.000   1.4282   0.03557   0.02888  -0.0098   0.0538   1.0000
  14.250   1.4328   0.03738   0.03072  -0.0089   0.0517   1.0000
  14.500   1.4386   0.03913   0.03253  -0.0080   0.0504   1.0000
  14.750   1.4454   0.04084   0.03432  -0.0074   0.0489   1.0000
  15.000   1.4505   0.04276   0.03630  -0.0067   0.0474   1.0000
  15.250   1.4542   0.04485   0.03845  -0.0061   0.0462   1.0000
  15.500   1.4558   0.04722   0.04087  -0.0057   0.0448   1.0000
  15.750   1.4590   0.04949   0.04321  -0.0053   0.0437   1.0000
  16.000   1.4624   0.05179   0.04560  -0.0051   0.0427   1.0000
  16.250   1.4643   0.05430   0.04818  -0.0049   0.0415   1.0000
  16.500   1.4647   0.05704   0.05100  -0.0049   0.0405   1.0000
  16.750   1.4637   0.06003   0.05405  -0.0050   0.0393   1.0000
  17.250   1.4612   0.06621   0.06040  -0.0055   0.0377   1.0000
  17.500   1.4607   0.06930   0.06358  -0.0059   0.0366   1.0000
  17.750   1.4581   0.07269   0.06706  -0.0064   0.0359   1.0000
  18.000   1.4547   0.07627   0.07070  -0.0071   0.0348   1.0000
  18.250   1.4497   0.08008   0.07460  -0.0079   0.0343   1.0000
  18.500   1.4427   0.08421   0.07881  -0.0089   0.0334   1.0000
  18.750   1.4392   0.08790   0.08260  -0.0098   0.0328   1.0000
  19.000   1.4352   0.09168   0.08648  -0.0108   0.0322   1.0000
  19.250   1.4303   0.09562   0.09050  -0.0119   0.0314   1.0000
<< Back to GOE 526 AIRFOIL (goe526-il)

Polar data table (+)

Polar graphs


<< Back to GOE 526 AIRFOIL (goe526-il)