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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.27 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9000-il-1000000-n5.txt
Download as CSV file: xf-s9000-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9000 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4551   0.08397   0.08235  -0.0272   1.0000   0.0042
  -8.000  -0.5522   0.02681   0.02412  -0.0653   0.9892   0.0029
  -7.750  -0.5302   0.02144   0.01810  -0.0678   0.9860   0.0028
  -7.500  -0.5018   0.01857   0.01482  -0.0695   0.9842   0.0028
  -7.250  -0.4765   0.01654   0.01247  -0.0699   0.9808   0.0028
  -7.000  -0.4496   0.01508   0.01077  -0.0703   0.9770   0.0028
  -6.750  -0.4199   0.01382   0.00928  -0.0711   0.9742   0.0028
  -6.500  -0.3887   0.01275   0.00803  -0.0721   0.9717   0.0028
  -6.250  -0.3621   0.01194   0.00709  -0.0720   0.9658   0.0028
  -6.000  -0.3327   0.01118   0.00622  -0.0725   0.9595   0.0029
  -5.750  -0.3027   0.01052   0.00546  -0.0730   0.9527   0.0029
  -5.500  -0.2715   0.00994   0.00478  -0.0738   0.9450   0.0029
  -5.250  -0.2406   0.00946   0.00422  -0.0745   0.9357   0.0030
  -5.000  -0.2101   0.00904   0.00370  -0.0750   0.9243   0.0030
  -4.750  -0.1811   0.00871   0.00328  -0.0752   0.9093   0.0031
  -4.500  -0.1535   0.00837   0.00282  -0.0750   0.8910   0.0033
  -4.250  -0.1265   0.00814   0.00247  -0.0747   0.8721   0.0039
  -4.000  -0.0996   0.00798   0.00221  -0.0744   0.8536   0.0047
  -3.750  -0.0728   0.00781   0.00198  -0.0741   0.8359   0.0074
  -3.500  -0.0460   0.00765   0.00179  -0.0738   0.8196   0.0139
  -3.250  -0.0190   0.00753   0.00163  -0.0736   0.8037   0.0213
  -3.000   0.0079   0.00738   0.00148  -0.0733   0.7877   0.0351
  -2.750   0.0346   0.00716   0.00134  -0.0731   0.7694   0.0695
  -2.500   0.0612   0.00699   0.00121  -0.0729   0.7488   0.1056
  -2.250   0.0881   0.00686   0.00111  -0.0727   0.7297   0.1394
  -1.750   0.1423   0.00661   0.00096  -0.0725   0.6939   0.2186
  -1.500   0.1692   0.00646   0.00090  -0.0724   0.6748   0.2736
  -1.250   0.1963   0.00637   0.00086  -0.0723   0.6552   0.3205
  -1.000   0.2233   0.00631   0.00083  -0.0721   0.6321   0.3651
  -0.750   0.2502   0.00622   0.00082  -0.0720   0.6087   0.4236
  -0.500   0.2773   0.00616   0.00081  -0.0719   0.5882   0.4727
  -0.250   0.3044   0.00606   0.00082  -0.0718   0.5698   0.5343
   0.000   0.3316   0.00598   0.00084  -0.0717   0.5506   0.5936
   0.250   0.3586   0.00594   0.00088  -0.0716   0.5309   0.6512
   0.500   0.3856   0.00597   0.00093  -0.0714   0.5090   0.6927
   0.750   0.4122   0.00606   0.00099  -0.0711   0.4819   0.7265
   1.000   0.4390   0.00616   0.00106  -0.0708   0.4573   0.7519
   1.250   0.4661   0.00625   0.00113  -0.0706   0.4368   0.7706
   1.500   0.4930   0.00634   0.00120  -0.0704   0.4184   0.7904
   1.750   0.5197   0.00645   0.00128  -0.0701   0.3995   0.8088
   2.000   0.5464   0.00657   0.00137  -0.0698   0.3788   0.8260
   2.250   0.5729   0.00669   0.00146  -0.0695   0.3610   0.8425
   2.500   0.5989   0.00683   0.00156  -0.0691   0.3393   0.8594
   2.750   0.6241   0.00702   0.00168  -0.0686   0.3116   0.8780
   3.000   0.6491   0.00717   0.00181  -0.0679   0.2904   0.8973
   3.250   0.6732   0.00729   0.00192  -0.0671   0.2744   0.9192
   3.500   0.6960   0.00741   0.00203  -0.0659   0.2561   0.9487
   3.750   0.7271   0.00756   0.00214  -0.0666   0.2377   1.0000
   4.000   0.7541   0.00776   0.00229  -0.0665   0.2229   1.0000
   4.500   0.8062   0.00836   0.00266  -0.0660   0.1762   1.0000
   4.750   0.8325   0.00863   0.00285  -0.0658   0.1593   1.0000
   5.000   0.8589   0.00888   0.00305  -0.0657   0.1462   1.0000
   5.500   0.9115   0.00938   0.00347  -0.0652   0.1229   1.0000
   5.750   0.9377   0.00964   0.00371  -0.0650   0.1120   1.0000
   6.000   0.9633   0.00995   0.00396  -0.0647   0.0990   1.0000
   6.250   0.9889   0.01027   0.00423  -0.0644   0.0870   1.0000
   6.500   1.0145   0.01058   0.00451  -0.0641   0.0779   1.0000
   6.750   1.0394   0.01095   0.00484  -0.0637   0.0661   1.0000
   7.000   1.0641   0.01134   0.00518  -0.0633   0.0545   1.0000
   7.250   1.0887   0.01175   0.00553  -0.0629   0.0449   1.0000
   7.500   1.1136   0.01209   0.00587  -0.0625   0.0397   1.0000
   7.750   1.1382   0.01247   0.00624  -0.0621   0.0344   1.0000
   8.000   1.1627   0.01284   0.00662  -0.0616   0.0304   1.0000
   8.250   1.1867   0.01326   0.00704  -0.0611   0.0257   1.0000
   8.500   1.2105   0.01368   0.00746  -0.0606   0.0211   1.0000
   8.750   1.2333   0.01420   0.00795  -0.0599   0.0157   1.0000
   9.000   1.2559   0.01473   0.00847  -0.0592   0.0119   1.0000
   9.250   1.2782   0.01528   0.00902  -0.0585   0.0093   1.0000
   9.500   1.3009   0.01576   0.00954  -0.0578   0.0079   1.0000
   9.750   1.3227   0.01630   0.01012  -0.0571   0.0066   1.0000
  10.000   1.3444   0.01684   0.01070  -0.0563   0.0058   1.0000
  10.250   1.3660   0.01737   0.01128  -0.0555   0.0051   1.0000
  10.500   1.3867   0.01795   0.01191  -0.0545   0.0045   1.0000
  10.750   1.4064   0.01859   0.01260  -0.0535   0.0039   1.0000
  11.000   1.4265   0.01917   0.01324  -0.0525   0.0035   1.0000
  11.250   1.4455   0.01980   0.01393  -0.0514   0.0030   1.0000
  11.500   1.4630   0.02053   0.01473  -0.0501   0.0025   1.0000
  11.750   1.4798   0.02126   0.01553  -0.0487   0.0021   1.0000
  12.000   1.4956   0.02202   0.01636  -0.0472   0.0017   1.0000
  12.250   1.5081   0.02285   0.01726  -0.0451   0.0014   1.0000
  12.500   1.5174   0.02375   0.01823  -0.0426   0.0011   1.0000
  12.750   1.5267   0.02462   0.01919  -0.0401   0.0011   1.0000
  13.000   1.5336   0.02567   0.02034  -0.0376   0.0009   1.0000
  13.250   1.5403   0.02677   0.02153  -0.0352   0.0008   1.0000
  13.500   1.5450   0.02806   0.02292  -0.0328   0.0008   1.0000
  13.750   1.5482   0.02952   0.02448  -0.0306   0.0007   1.0000
  14.000   1.5505   0.03114   0.02623  -0.0287   0.0006   1.0000
  14.250   1.5505   0.03308   0.02829  -0.0269   0.0006   1.0000
  14.500   1.5504   0.03517   0.03051  -0.0255   0.0006   1.0000
  14.750   1.5436   0.03810   0.03359  -0.0244   0.0005   1.0000
  15.000   1.5425   0.04067   0.03628  -0.0238   0.0005   1.0000
  15.250   1.5339   0.04432   0.04008  -0.0238   0.0005   1.0000
  15.500   1.5231   0.04859   0.04451  -0.0245   0.0005   1.0000
  15.750   1.5144   0.05291   0.04897  -0.0257   0.0005   1.0000
  16.000   1.5027   0.05801   0.05422  -0.0275   0.0005   1.0000
  16.250   1.4886   0.06385   0.06022  -0.0301   0.0005   1.0000
  16.500   1.4723   0.07043   0.06695  -0.0334   0.0005   1.0000
  16.750   1.4516   0.07822   0.07490  -0.0375   0.0005   1.0000
  17.000   1.4319   0.08618   0.08301  -0.0418   0.0005   1.0000
  17.250   1.4020   0.09660   0.09361  -0.0477   0.0005   1.0000
  17.500   1.3775   0.10621   0.10337  -0.0531   0.0005   1.0000
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