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S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S9026 (9.5%) (s9026-il)
Reynolds number: 50,000
Max Cl/Cd: 25.37 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9026-il-50000-n5.txt
Download as CSV file: xf-s9026-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9026 (9.5%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7264   0.09430   0.08699  -0.0035   1.0000   0.0646
 -10.750  -0.7523   0.08363   0.07639  -0.0109   1.0000   0.0639
 -10.500  -0.7865   0.07377   0.06649  -0.0186   1.0000   0.0628
 -10.250  -0.8185   0.06693   0.05953  -0.0223   1.0000   0.0622
 -10.000  -0.8427   0.06199   0.05440  -0.0226   1.0000   0.0620
  -9.750  -0.8570   0.05740   0.04952  -0.0223   1.0000   0.0625
  -9.500  -0.8640   0.05316   0.04491  -0.0216   1.0000   0.0636
  -9.250  -0.8654   0.04925   0.04054  -0.0206   1.0000   0.0656
  -9.000  -0.8636   0.04547   0.03611  -0.0193   1.0000   0.0683
  -8.750  -0.8478   0.04359   0.03429  -0.0186   1.0000   0.0719
  -8.500  -0.8339   0.04111   0.03153  -0.0176   1.0000   0.0754
  -8.250  -0.8189   0.03831   0.02819  -0.0164   1.0000   0.0794
  -8.000  -0.8013   0.03644   0.02622  -0.0155   1.0000   0.0848
  -7.750  -0.7828   0.03466   0.02416  -0.0146   1.0000   0.0919
  -7.500  -0.7628   0.03287   0.02226  -0.0136   1.0000   0.0984
  -7.250  -0.7426   0.03133   0.02044  -0.0127   1.0000   0.1083
  -7.000  -0.7222   0.03002   0.01914  -0.0118   1.0000   0.1179
  -6.750  -0.7014   0.02873   0.01776  -0.0108   1.0000   0.1296
  -6.500  -0.6802   0.02753   0.01650  -0.0099   1.0000   0.1431
  -6.250  -0.6586   0.02637   0.01529  -0.0089   1.0000   0.1580
  -6.000  -0.6370   0.02533   0.01419  -0.0080   1.0000   0.1769
  -5.750  -0.6154   0.02432   0.01323  -0.0070   1.0000   0.1958
  -5.500  -0.5939   0.02342   0.01231  -0.0061   1.0000   0.2202
  -5.250  -0.5726   0.02257   0.01155  -0.0051   1.0000   0.2469
  -5.000  -0.5511   0.02179   0.01084  -0.0041   1.0000   0.2778
  -4.750  -0.5298   0.02106   0.01025  -0.0030   1.0000   0.3118
  -4.500  -0.5084   0.02039   0.00966  -0.0019   1.0000   0.3488
  -4.250  -0.4872   0.01977   0.00919  -0.0006   1.0000   0.3879
  -4.000  -0.4665   0.01922   0.00877   0.0008   1.0000   0.4292
  -3.750  -0.4462   0.01872   0.00843   0.0024   1.0000   0.4720
  -3.500  -0.4261   0.01828   0.00813   0.0042   1.0000   0.5161
  -3.250  -0.4061   0.01790   0.00790   0.0061   1.0000   0.5610
  -3.000  -0.3860   0.01758   0.00773   0.0082   1.0000   0.6058
  -2.750  -0.3658   0.01731   0.00760   0.0103   1.0000   0.6500
  -2.500  -0.3453   0.01710   0.00748   0.0124   1.0000   0.6935
  -2.250  -0.3240   0.01693   0.00741   0.0145   1.0000   0.7366
  -2.000  -0.3012   0.01682   0.00737   0.0163   1.0000   0.7793
  -1.750  -0.2743   0.01677   0.00736   0.0173   1.0000   0.8205
  -1.500  -0.2403   0.01677   0.00735   0.0169   1.0000   0.8597
  -1.250  -0.2003   0.01680   0.00734   0.0150   1.0000   0.8967
  -1.000  -0.1510   0.01685   0.00730   0.0111   1.0000   0.9285
  -0.750  -0.0972   0.01685   0.00723   0.0060   1.0000   0.9567
  -0.500  -0.0422   0.01676   0.00709   0.0003   1.0000   0.9827
  -0.250  -0.0008   0.01660   0.00690  -0.0035   1.0000   1.0000
   0.000   0.0000   0.01655   0.00687   0.0000   1.0000   1.0000
   0.250   0.0008   0.01660   0.00691   0.0035   1.0000   1.0000
   0.500   0.0423   0.01676   0.00709  -0.0003   0.9826   1.0000
   0.750   0.0973   0.01685   0.00723  -0.0060   0.9567   1.0000
   1.000   0.1510   0.01685   0.00730  -0.0111   0.9285   1.0000
   1.250   0.2003   0.01680   0.00734  -0.0150   0.8967   1.0000
   1.500   0.2403   0.01677   0.00735  -0.0169   0.8597   1.0000
   1.750   0.2744   0.01677   0.00736  -0.0173   0.8206   1.0000
   2.000   0.3013   0.01682   0.00737  -0.0163   0.7792   1.0000
   2.250   0.3241   0.01693   0.00741  -0.0145   0.7365   1.0000
   2.500   0.3453   0.01710   0.00748  -0.0124   0.6934   1.0000
   2.750   0.3659   0.01731   0.00760  -0.0103   0.6499   1.0000
   3.000   0.3861   0.01758   0.00773  -0.0082   0.6058   1.0000
   3.250   0.4062   0.01790   0.00791  -0.0062   0.5610   1.0000
   3.500   0.4262   0.01828   0.00813  -0.0042   0.5162   1.0000
   3.750   0.4463   0.01872   0.00843  -0.0025   0.4721   1.0000
   4.000   0.4665   0.01922   0.00877  -0.0008   0.4291   1.0000
   4.250   0.4873   0.01977   0.00919   0.0006   0.3878   1.0000
   4.500   0.5085   0.02039   0.00966   0.0018   0.3487   1.0000
   4.750   0.5299   0.02106   0.01025   0.0030   0.3117   1.0000
   5.000   0.5511   0.02179   0.01084   0.0040   0.2778   1.0000
   5.250   0.5726   0.02257   0.01155   0.0051   0.2469   1.0000
   5.500   0.5939   0.02342   0.01231   0.0061   0.2203   1.0000
   5.750   0.6155   0.02432   0.01323   0.0070   0.1958   1.0000
   6.000   0.6370   0.02533   0.01419   0.0080   0.1769   1.0000
   6.250   0.6585   0.02637   0.01529   0.0089   0.1580   1.0000
   6.500   0.6801   0.02753   0.01650   0.0099   0.1431   1.0000
   6.750   0.7013   0.02873   0.01776   0.0108   0.1295   1.0000
   7.000   0.7221   0.03002   0.01913   0.0118   0.1180   1.0000
   7.250   0.7426   0.03134   0.02043   0.0127   0.1082   1.0000
   7.500   0.7627   0.03287   0.02226   0.0137   0.0983   1.0000
   7.750   0.7827   0.03465   0.02415   0.0146   0.0919   1.0000
   8.000   0.8012   0.03643   0.02621   0.0156   0.0847   1.0000
   8.250   0.8188   0.03831   0.02819   0.0165   0.0794   1.0000
   8.500   0.8338   0.04111   0.03152   0.0176   0.0754   1.0000
   8.750   0.8477   0.04357   0.03427   0.0186   0.0718   1.0000
   9.000   0.8634   0.04545   0.03610   0.0194   0.0684   1.0000
   9.250   0.8653   0.04923   0.04051   0.0206   0.0656   1.0000
   9.500   0.8638   0.05315   0.04490   0.0216   0.0636   1.0000
   9.750   0.8570   0.05739   0.04950   0.0223   0.0625   1.0000
  10.000   0.8428   0.06197   0.05438   0.0226   0.0621   1.0000
  10.250   0.8184   0.06693   0.05953   0.0223   0.0621   1.0000
  10.500   0.7868   0.07376   0.06648   0.0186   0.0628   1.0000
  10.750   0.7526   0.08364   0.07640   0.0109   0.0639   1.0000
  11.000   0.7266   0.09434   0.08702   0.0034   0.0645   1.0000
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