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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.17 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe408-il-1000000-n5.txt
Download as CSV file: xf-goe408-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4045   0.08628   0.08469  -0.0320   0.9950   0.0054
  -8.500  -0.4533   0.06039   0.05867  -0.0587   0.9871   0.0060
  -8.250  -0.4541   0.05291   0.05104  -0.0631   0.9824   0.0061
  -8.000  -0.4403   0.04589   0.04381  -0.0682   0.9797   0.0062
  -7.750  -0.4366   0.03804   0.03563  -0.0700   0.9755   0.0063
  -7.500  -0.4287   0.03211   0.02937  -0.0697   0.9709   0.0064
  -7.000  -0.4242   0.02021   0.01651  -0.0635   0.9592   0.0073
  -6.750  -0.4296   0.01494   0.01068  -0.0576   0.9498   0.0077
  -6.500  -0.4141   0.01359   0.00914  -0.0552   0.9408   0.0080
  -6.000  -0.3658   0.01194   0.00719  -0.0536   0.9224   0.0091
  -5.750  -0.3270   0.01098   0.00609  -0.0560   0.9133   0.0103
  -5.500  -0.2693   0.00992   0.00487  -0.0627   0.9021   0.0123
  -5.250  -0.1996   0.00913   0.00398  -0.0724   0.8838   0.0195
  -5.000  -0.1385   0.00909   0.00385  -0.0800   0.8581   0.0255
  -4.750  -0.0983   0.00937   0.00403  -0.0828   0.8233   0.0278
  -4.500  -0.0720   0.00948   0.00396  -0.0823   0.7886   0.0293
  -4.250  -0.0487   0.00958   0.00391  -0.0812   0.7617   0.0304
  -4.000  -0.0252   0.00959   0.00379  -0.0801   0.7422   0.0308
  -3.750  -0.0020   0.00945   0.00356  -0.0790   0.7261   0.0318
  -3.500   0.0230   0.00963   0.00370  -0.0783   0.7119   0.0329
  -3.250   0.0482   0.00987   0.00392  -0.0776   0.6993   0.0339
  -3.000   0.0725   0.00970   0.00367  -0.0767   0.6899   0.0345
  -2.750   0.0967   0.00955   0.00343  -0.0758   0.6783   0.0351
  -2.500   0.1211   0.00937   0.00319  -0.0750   0.6688   0.0358
  -2.250   0.1453   0.00921   0.00296  -0.0741   0.6593   0.0363
  -2.000   0.1696   0.00906   0.00275  -0.0732   0.6492   0.0367
  -1.750   0.1937   0.00890   0.00253  -0.0723   0.6393   0.0371
  -1.500   0.2174   0.00876   0.00233  -0.0713   0.6289   0.0373
  -1.250   0.2416   0.00867   0.00219  -0.0704   0.6188   0.0376
  -1.000   0.2658   0.00858   0.00205  -0.0695   0.6087   0.0379
  -0.750   0.2896   0.00848   0.00190  -0.0685   0.5987   0.0381
  -0.250   0.3369   0.00831   0.00163  -0.0666   0.5743   0.0388
   0.000   0.3602   0.00819   0.00147  -0.0655   0.5617   0.0400
   0.250   0.3836   0.00822   0.00142  -0.0645   0.5404   0.0411
   0.500   0.4077   0.00824   0.00138  -0.0636   0.5229   0.0418
   0.750   0.4318   0.00830   0.00136  -0.0627   0.5015   0.0428
   1.000   0.4558   0.00834   0.00134  -0.0619   0.4837   0.0435
   1.250   0.4802   0.00839   0.00134  -0.0611   0.4676   0.0447
   1.500   0.5043   0.00848   0.00135  -0.0603   0.4480   0.0457
   1.750   0.5284   0.00857   0.00137  -0.0594   0.4294   0.0462
   2.000   0.5526   0.00865   0.00139  -0.0586   0.4143   0.0469
   2.250   0.5767   0.00874   0.00144  -0.0578   0.3998   0.0474
   2.500   0.6008   0.00879   0.00146  -0.0570   0.3886   0.0484
   2.750   0.6249   0.00883   0.00148  -0.0562   0.3793   0.0515
   3.000   0.6490   0.00889   0.00154  -0.0553   0.3701   0.0532
   3.250   0.6728   0.00897   0.00160  -0.0545   0.3594   0.0564
   3.500   0.6966   0.00904   0.00166  -0.0536   0.3497   0.0589
   3.750   0.7202   0.00913   0.00174  -0.0527   0.3390   0.0647
   4.000   0.7423   0.00930   0.00190  -0.0516   0.3116   0.1119
   4.500   1.0125   0.00991   0.00366  -0.1039   0.1666   1.0000
   4.750   1.0346   0.01015   0.00385  -0.1027   0.1541   1.0000
   5.000   1.0567   0.01040   0.00405  -0.1016   0.1434   1.0000
   5.250   1.0784   0.01066   0.00426  -0.1003   0.1312   1.0000
   5.500   1.0997   0.01095   0.00450  -0.0990   0.1177   1.0000
   5.750   1.1214   0.01120   0.00472  -0.0978   0.1083   1.0000
   6.000   1.1424   0.01149   0.00497  -0.0965   0.0975   1.0000
   6.250   1.1570   0.01223   0.00545  -0.0939   0.0547   1.0000
   6.500   1.1778   0.01251   0.00574  -0.0926   0.0479   1.0000
   6.750   1.1980   0.01284   0.00608  -0.0911   0.0424   1.0000
   7.000   1.2182   0.01315   0.00640  -0.0896   0.0377   1.0000
   7.250   1.2368   0.01358   0.00677  -0.0878   0.0285   1.0000
   7.500   1.2528   0.01415   0.00725  -0.0856   0.0147   1.0000
   7.750   1.2716   0.01454   0.00765  -0.0839   0.0123   1.0000
   8.000   1.2899   0.01494   0.00809  -0.0821   0.0103   1.0000
   8.250   1.3085   0.01532   0.00850  -0.0804   0.0092   1.0000
   8.500   1.3260   0.01574   0.00895  -0.0784   0.0081   1.0000
   8.750   1.3421   0.01625   0.00949  -0.0762   0.0070   1.0000
   9.000   1.3593   0.01665   0.00994  -0.0743   0.0067   1.0000
   9.250   1.3761   0.01704   0.01037  -0.0723   0.0062   1.0000
   9.500   1.3896   0.01751   0.01089  -0.0696   0.0058   1.0000
   9.750   1.4022   0.01794   0.01137  -0.0668   0.0054   1.0000
  10.000   1.4131   0.01846   0.01193  -0.0637   0.0050   1.0000
  10.250   1.4230   0.01904   0.01258  -0.0604   0.0046   1.0000
  10.500   1.4344   0.01957   0.01317  -0.0575   0.0046   1.0000
  10.750   1.4461   0.02010   0.01377  -0.0547   0.0043   1.0000
  11.000   1.4577   0.02064   0.01436  -0.0520   0.0040   1.0000
  11.250   1.4680   0.02128   0.01506  -0.0492   0.0039   1.0000
  11.500   1.4785   0.02190   0.01575  -0.0465   0.0038   1.0000
  11.750   1.4865   0.02270   0.01663  -0.0434   0.0037   1.0000
  12.000   1.4944   0.02351   0.01751  -0.0405   0.0035   1.0000
  12.250   1.5009   0.02442   0.01850  -0.0376   0.0034   1.0000
  12.500   1.5013   0.02578   0.01995  -0.0339   0.0032   1.0000
  12.750   1.5077   0.02678   0.02104  -0.0313   0.0030   1.0000
  13.000   1.5136   0.02789   0.02223  -0.0288   0.0030   1.0000
  13.250   1.5148   0.02940   0.02385  -0.0261   0.0030   1.0000
  13.500   1.5186   0.03082   0.02535  -0.0240   0.0030   1.0000
  13.750   1.5195   0.03258   0.02722  -0.0219   0.0029   1.0000
  14.000   1.5210   0.03442   0.02916  -0.0202   0.0027   1.0000
  14.250   1.5219   0.03644   0.03130  -0.0188   0.0027   1.0000
  14.500   1.5180   0.03910   0.03408  -0.0175   0.0027   1.0000
  14.750   1.5205   0.04122   0.03629  -0.0168   0.0025   1.0000
  15.000   1.5156   0.04428   0.03947  -0.0161   0.0025   1.0000
  15.250   1.5092   0.04769   0.04300  -0.0158   0.0025   1.0000
  15.500   1.5060   0.05080   0.04621  -0.0157   0.0024   1.0000
  15.750   1.4942   0.05517   0.05073  -0.0160   0.0025   1.0000
  16.000   1.4850   0.05936   0.05505  -0.0166   0.0025   1.0000
  16.250   1.4758   0.06369   0.05948  -0.0174   0.0024   1.0000
  16.500   1.4806   0.06608   0.06192  -0.0178   0.0022   1.0000
  16.750   1.4534   0.07345   0.06949  -0.0198   0.0024   1.0000
  17.000   1.4441   0.07823   0.07438  -0.0212   0.0024   1.0000
  17.250   1.4358   0.08295   0.07918  -0.0227   0.0023   1.0000
  17.500   1.4199   0.08907   0.08543  -0.0248   0.0022   1.0000
  17.750   1.4000   0.09598   0.09249  -0.0273   0.0023   1.0000
  18.000   1.3907   0.10118   0.09776  -0.0293   0.0022   1.0000
  18.250   1.3742   0.10774   0.10445  -0.0318   0.0022   1.0000
  18.500   1.3559   0.11479   0.11161  -0.0347   0.0022   1.0000
  18.750   1.3388   0.12169   0.11864  -0.0376   0.0022   1.0000
  19.000   1.3205   0.12901   0.12607  -0.0409   0.0023   1.0000
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