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GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 437 AIRFOIL (goe437-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.15 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe437-il-1000000.txt
Download as CSV file: xf-goe437-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 437 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3271   0.09374   0.09220  -0.0250   1.0000   0.0083
  -8.000  -0.3278   0.09128   0.08976  -0.0245   1.0000   0.0088
  -7.750  -0.3309   0.08915   0.08767  -0.0236   1.0000   0.0093
  -7.500  -0.3277   0.08637   0.08491  -0.0252   0.9991   0.0096
  -7.250  -0.3062   0.08212   0.08066  -0.0323   0.9955   0.0098
  -7.000  -0.2830   0.07737   0.07591  -0.0394   0.9916   0.0098
  -6.750  -0.2587   0.07254   0.07106  -0.0468   0.9876   0.0098
  -6.250  -0.1480   0.04061   0.03917  -0.0691   0.9678   0.0102
  -6.000  -0.1290   0.03531   0.03381  -0.0753   0.9571   0.0105
  -5.750  -0.1100   0.03144   0.02988  -0.0792   0.9441   0.0107
  -5.500  -0.0912   0.02786   0.02621  -0.0823   0.9279   0.0110
  -5.250  -0.0726   0.02446   0.02269  -0.0848   0.9067   0.0116
  -5.000  -0.0522   0.02053   0.01858  -0.0876   0.8830   0.0123
  -4.750  -0.0270   0.01510   0.01166  -0.1014   0.9207   0.0094
  -4.500  -0.0020   0.01360   0.00981  -0.1009   0.9017   0.0097
  -4.250   0.0229   0.01260   0.00849  -0.1002   0.8766   0.0099
  -4.000   0.0449   0.01007   0.00537  -0.0991   0.8503   0.0105
  -3.750   0.0695   0.00931   0.00436  -0.0983   0.8273   0.0114
  -3.500   0.0950   0.00884   0.00372  -0.0977   0.8085   0.0121
  -3.250   0.1210   0.00853   0.00327  -0.0971   0.7924   0.0135
  -3.000   0.1472   0.00826   0.00286  -0.0966   0.7781   0.0145
  -2.750   0.1732   0.00786   0.00231  -0.0961   0.7656   0.0158
  -2.500   0.1996   0.00753   0.00190  -0.0956   0.7544   0.0192
  -2.250   0.2264   0.00748   0.00179  -0.0953   0.7436   0.0221
  -2.000   0.2528   0.00724   0.00149  -0.0949   0.7327   0.0309
  -1.750   0.2796   0.00711   0.00133  -0.0946   0.7217   0.0402
  -1.500   0.3067   0.00708   0.00125  -0.0943   0.7111   0.0456
  -1.250   0.3334   0.00696   0.00110  -0.0940   0.7002   0.0555
  -1.000   0.3601   0.00686   0.00102  -0.0937   0.6877   0.0757
  -0.750   0.3868   0.00683   0.00102  -0.0934   0.6730   0.1053
  -0.500   0.4136   0.00684   0.00097  -0.0931   0.6557   0.1154
  -0.250   0.4400   0.00687   0.00094  -0.0928   0.6346   0.1240
   0.000   0.4660   0.00692   0.00090  -0.0924   0.6068   0.1325
   0.250   0.4917   0.00702   0.00089  -0.0919   0.5778   0.1411
   0.500   0.5176   0.00710   0.00091  -0.0915   0.5553   0.1564
   0.750   0.5436   0.00712   0.00096  -0.0912   0.5387   0.1975
   1.000   0.5675   0.00666   0.00107  -0.0907   0.5262   0.4609
   1.250   0.6113   0.00557   0.00120  -0.0946   0.5143   1.0000
   1.500   0.6374   0.00567   0.00124  -0.0942   0.5048   1.0000
   1.750   0.6633   0.00579   0.00129  -0.0937   0.4955   1.0000
   2.000   0.6894   0.00590   0.00135  -0.0934   0.4857   1.0000
   2.250   0.7156   0.00600   0.00141  -0.0930   0.4764   1.0000
   2.500   0.7416   0.00611   0.00148  -0.0926   0.4671   1.0000
   2.750   0.7678   0.00622   0.00156  -0.0922   0.4570   1.0000
   3.000   0.7940   0.00633   0.00163  -0.0919   0.4462   1.0000
   3.250   0.8200   0.00646   0.00172  -0.0915   0.4345   1.0000
   3.500   0.8458   0.00660   0.00181  -0.0911   0.4201   1.0000
   3.750   0.8709   0.00681   0.00194  -0.0906   0.3983   1.0000
   4.000   0.8959   0.00702   0.00206  -0.0901   0.3760   1.0000
   4.250   0.9206   0.00728   0.00222  -0.0896   0.3534   1.0000
   4.500   0.9451   0.00755   0.00239  -0.0890   0.3317   1.0000
   4.750   0.9699   0.00779   0.00258  -0.0885   0.3122   1.0000
   5.000   0.9941   0.00810   0.00278  -0.0879   0.2873   1.0000
   5.250   1.0160   0.00864   0.00306  -0.0870   0.2351   1.0000
   5.500   1.0209   0.01103   0.00435  -0.0836   0.0338   1.0000
   5.750   1.0433   0.01158   0.00485  -0.0826   0.0170   1.0000
   6.000   1.0664   0.01203   0.00541  -0.0817   0.0139   1.0000
   6.250   1.0900   0.01240   0.00582  -0.0809   0.0128   1.0000
   6.500   1.1132   0.01280   0.00625  -0.0802   0.0112   1.0000
   6.750   1.1347   0.01338   0.00689  -0.0791   0.0099   1.0000
   7.000   1.1491   0.01471   0.00841  -0.0767   0.0087   1.0000
   7.250   1.1708   0.01519   0.00895  -0.0757   0.0085   1.0000
   7.500   1.1917   0.01573   0.00955  -0.0746   0.0081   1.0000
   7.750   1.2107   0.01641   0.01030  -0.0731   0.0075   1.0000
   8.000   1.2279   0.01724   0.01120  -0.0714   0.0070   1.0000
   8.250   1.2459   0.01793   0.01194  -0.0699   0.0065   1.0000
   8.500   1.2635   0.01862   0.01267  -0.0684   0.0062   1.0000
   8.750   1.2775   0.01957   0.01367  -0.0664   0.0058   1.0000
   9.000   1.2861   0.02096   0.01515  -0.0635   0.0056   1.0000
   9.250   1.2895   0.02292   0.01721  -0.0598   0.0054   1.0000
   9.500   1.2960   0.02596   0.02039  -0.0569   0.0052   1.0000
   9.750   1.3072   0.02656   0.02110  -0.0544   0.0051   1.0000
  10.000   1.3184   0.02733   0.02196  -0.0520   0.0050   1.0000
  10.250   1.3293   0.02908   0.02385  -0.0498   0.0049   1.0000
  10.500   1.3390   0.03026   0.02514  -0.0474   0.0046   1.0000
  10.750   1.3478   0.03213   0.02717  -0.0451   0.0043   1.0000
  11.000   1.3557   0.03510   0.03036  -0.0429   0.0043   1.0000
  11.250   1.3573   0.03880   0.03434  -0.0402   0.0043   1.0000
  11.500   1.3503   0.04288   0.03871  -0.0370   0.0045   1.0000
  11.750   1.3362   0.04712   0.04320  -0.0339   0.0048   1.0000
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