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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 50,000
Max Cl/Cd: 40.39 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe374-il-50000-n5.txt
Download as CSV file: xf-goe374-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 374 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3263   0.10483   0.09824  -0.0206   1.0000   0.0484
  -7.750  -0.3289   0.10364   0.09718  -0.0219   1.0000   0.0491
  -7.500  -0.3280   0.10226   0.09590  -0.0246   1.0000   0.0495
  -7.250  -0.3240   0.10074   0.09446  -0.0280   1.0000   0.0498
  -7.000  -0.3184   0.09563   0.08946  -0.0263   1.0000   0.0508
  -6.750  -0.3122   0.09103   0.08491  -0.0233   1.0000   0.0529
  -6.500  -0.3074   0.08815   0.08210  -0.0233   1.0000   0.0547
  -6.250  -0.3024   0.08547   0.07949  -0.0239   1.0000   0.0570
  -6.000  -0.2967   0.08295   0.07704  -0.0253   1.0000   0.0599
  -5.750  -0.2867   0.08127   0.07536  -0.0294   1.0000   0.0630
  -5.500  -0.2704   0.08042   0.07439  -0.0353   1.0000   0.0641
  -5.250  -0.2744   0.07479   0.06902  -0.0294   1.0000   0.0669
  -5.000  -0.2681   0.07201   0.06628  -0.0287   1.0000   0.0716
  -4.750  -0.2438   0.07114   0.06518  -0.0359   1.0000   0.0784
  -4.500  -0.2466   0.06648   0.06071  -0.0312   1.0000   0.0822
  -4.250  -0.2205   0.06570   0.05962  -0.0368   1.0000   0.0920
  -4.000  -0.2215   0.06105   0.05522  -0.0330   1.0000   0.0958
  -3.750  -0.2021   0.05883   0.05284  -0.0355   1.0000   0.1072
  -3.500  -0.1871   0.05637   0.05030  -0.0364   1.0000   0.1211
  -3.250  -0.1750   0.05327   0.04723  -0.0361   0.9993   0.1367
  -3.000  -0.1394   0.04939   0.04331  -0.0407   0.9881   0.1812
  -1.750   0.1095   0.03374   0.02518  -0.0631   0.9325   0.0748
  -1.500   0.1518   0.03139   0.02236  -0.0655   0.9210   0.0722
  -1.250   0.1968   0.02931   0.01972  -0.0677   0.9103   0.0673
  -1.000   0.2372   0.02759   0.01763  -0.0695   0.8977   0.0710
  -0.500   0.3143   0.02486   0.01413  -0.0717   0.8695   0.0726
  -0.250   0.3535   0.02381   0.01272  -0.0728   0.8545   0.0748
   0.000   0.3881   0.02293   0.01163  -0.0733   0.8367   0.0816
   0.250   0.4213   0.02218   0.01068  -0.0734   0.8183   0.0830
   0.500   0.4536   0.02159   0.00989  -0.0735   0.7997   0.0845
   0.750   0.4833   0.02117   0.00929  -0.0731   0.7789   0.0865
   1.000   0.5124   0.02087   0.00879  -0.0727   0.7577   0.0891
   1.250   0.5414   0.02064   0.00838  -0.0722   0.7363   0.0930
   1.500   0.5695   0.02045   0.00808  -0.0717   0.7144   0.1007
   1.750   0.5977   0.02017   0.00787  -0.0712   0.6938   0.1328
   2.250   0.6589   0.01882   0.00762  -0.0713   0.6529   1.0000
   2.500   0.6845   0.01914   0.00769  -0.0705   0.6331   1.0000
   2.750   0.7102   0.01949   0.00784  -0.0698   0.6142   1.0000
   3.000   0.7358   0.01986   0.00804  -0.0691   0.5965   1.0000
   3.250   0.7613   0.02026   0.00829  -0.0684   0.5796   1.0000
   3.500   0.7861   0.02068   0.00865  -0.0678   0.5628   1.0000
   3.750   0.8107   0.02111   0.00903  -0.0671   0.5467   1.0000
   4.000   0.8353   0.02155   0.00944  -0.0665   0.5311   1.0000
   4.250   0.8598   0.02199   0.00986  -0.0658   0.5163   1.0000
   4.500   0.8841   0.02245   0.01036  -0.0651   0.5017   1.0000
   4.750   0.9083   0.02291   0.01083  -0.0644   0.4875   1.0000
   5.000   0.9319   0.02338   0.01132  -0.0636   0.4723   1.0000
   5.250   0.9548   0.02384   0.01185  -0.0626   0.4555   1.0000
   5.500   0.9772   0.02429   0.01231  -0.0615   0.4378   1.0000
   5.750   0.9995   0.02477   0.01279  -0.0605   0.4205   1.0000
   6.000   1.0218   0.02530   0.01336  -0.0595   0.4042   1.0000
   6.250   1.0438   0.02591   0.01414  -0.0585   0.3885   1.0000
   6.500   1.0656   0.02654   0.01492  -0.0576   0.3734   1.0000
   6.750   1.0870   0.02720   0.01576  -0.0566   0.3582   1.0000
   7.000   1.1077   0.02788   0.01664  -0.0555   0.3424   1.0000
   7.250   1.1279   0.02859   0.01755  -0.0544   0.3265   1.0000
   7.500   1.1478   0.02933   0.01856  -0.0532   0.3110   1.0000
   7.750   1.1679   0.03016   0.01960  -0.0521   0.2969   1.0000
   8.000   1.1856   0.03089   0.02053  -0.0506   0.2800   1.0000
   8.250   1.1985   0.03136   0.02104  -0.0486   0.2572   1.0000
   8.500   1.2120   0.03214   0.02201  -0.0469   0.2365   1.0000
   9.000   1.2315   0.03398   0.02404  -0.0429   0.1879   1.0000
   9.250   1.2419   0.03519   0.02543  -0.0411   0.1662   1.0000
   9.500   1.2499   0.03661   0.02698  -0.0391   0.1467   1.0000
   9.750   1.2521   0.03845   0.02883  -0.0368   0.1201   1.0000
  10.000   1.2491   0.04076   0.03108  -0.0343   0.0761   1.0000
  10.250   1.2354   0.04414   0.03406  -0.0321   0.0474   1.0000
  10.500   1.2252   0.04759   0.03747  -0.0307   0.0394   1.0000
  10.750   1.2157   0.05130   0.04128  -0.0300   0.0356   1.0000
  11.000   1.2060   0.05534   0.04546  -0.0301   0.0339   1.0000
  11.250   1.1965   0.05972   0.05001  -0.0308   0.0328   1.0000
  11.500   1.1864   0.06454   0.05504  -0.0321   0.0317   1.0000
  11.750   1.1767   0.06954   0.06024  -0.0337   0.0310   1.0000
  12.000   1.1674   0.07466   0.06556  -0.0354   0.0305   1.0000
  12.250   1.1577   0.07997   0.07105  -0.0373   0.0300   1.0000
  12.500   1.1484   0.08535   0.07659  -0.0393   0.0295   1.0000
  12.750   1.1391   0.09078   0.08217  -0.0413   0.0289   1.0000
  13.000   1.1303   0.09618   0.08771  -0.0433   0.0284   1.0000
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