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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 500,000
Max Cl/Cd: 92.99 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9000-il-500000.txt
Download as CSV file: xf-s9000-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4407   0.08732   0.08507  -0.0300   1.0000   0.0162
  -8.750  -0.4409   0.08411   0.08189  -0.0305   1.0000   0.0164
  -8.500  -0.4416   0.08105   0.07886  -0.0311   1.0000   0.0166
  -8.250  -0.4446   0.07778   0.07563  -0.0318   1.0000   0.0168
  -8.000  -0.4511   0.07455   0.07244  -0.0322   1.0000   0.0170
  -7.750  -0.4643   0.07116   0.06911  -0.0326   1.0000   0.0170
  -7.500  -0.4722   0.06570   0.06367  -0.0375   1.0000   0.0170
  -7.250  -0.4767   0.06106   0.05900  -0.0399   1.0000   0.0172
  -7.000  -0.4801   0.05659   0.05448  -0.0411   1.0000   0.0173
  -6.750  -0.4815   0.05265   0.05046  -0.0413   1.0000   0.0176
  -6.500  -0.4803   0.04880   0.04650  -0.0413   0.9999   0.0180
  -6.250  -0.4506   0.04274   0.04017  -0.0474   0.9966   0.0190
  -6.000  -0.4168   0.03712   0.03412  -0.0521   0.9936   0.0212
  -5.750  -0.3809   0.03508   0.03157  -0.0547   0.9897   0.0222
  -5.500  -0.3570   0.02046   0.01559  -0.0574   0.9861   0.0113
  -5.250  -0.3222   0.01760   0.01243  -0.0593   0.9843   0.0103
  -5.000  -0.2899   0.01527   0.00975  -0.0602   0.9809   0.0098
  -4.750  -0.2569   0.01374   0.00802  -0.0612   0.9770   0.0096
  -4.500  -0.2214   0.01256   0.00670  -0.0627   0.9741   0.0098
  -4.250  -0.1843   0.01165   0.00568  -0.0646   0.9718   0.0105
  -4.000  -0.1509   0.01072   0.00465  -0.0658   0.9676   0.0121
  -3.750  -0.1167   0.01003   0.00393  -0.0670   0.9627   0.0183
  -3.500  -0.0789   0.00936   0.00338  -0.0691   0.9595   0.0455
  -3.250  -0.0408   0.00874   0.00300  -0.0715   0.9570   0.0995
  -3.000  -0.0118   0.00817   0.00272  -0.0718   0.9484   0.1749
  -2.750   0.0235   0.00763   0.00246  -0.0735   0.9437   0.2605
  -2.500   0.0532   0.00718   0.00227  -0.0740   0.9342   0.3442
  -2.250   0.0854   0.00674   0.00208  -0.0750   0.9256   0.4346
  -2.000   0.1167   0.00627   0.00193  -0.0757   0.9152   0.5398
  -1.750   0.1449   0.00590   0.00185  -0.0756   0.9014   0.6425
  -1.500   0.1723   0.00574   0.00181  -0.0751   0.8864   0.7114
  -1.250   0.1989   0.00566   0.00179  -0.0744   0.8708   0.7587
  -1.000   0.2250   0.00563   0.00177  -0.0737   0.8546   0.7918
  -0.750   0.2507   0.00563   0.00175  -0.0728   0.8377   0.8195
  -0.500   0.2763   0.00565   0.00173  -0.0720   0.8203   0.8430
  -0.250   0.3010   0.00568   0.00171  -0.0709   0.8022   0.8631
   0.000   0.3254   0.00571   0.00170  -0.0698   0.7832   0.8827
   0.250   0.3489   0.00575   0.00169  -0.0685   0.7642   0.9028
   0.500   0.3716   0.00578   0.00168  -0.0670   0.7458   0.9226
   1.000   0.4233   0.00586   0.00163  -0.0655   0.7063   0.9641
   1.500   0.4941   0.00606   0.00160  -0.0686   0.6575   1.0000
   1.750   0.5193   0.00620   0.00163  -0.0682   0.6335   1.0000
   2.000   0.5452   0.00636   0.00169  -0.0678   0.6105   1.0000
   2.250   0.5713   0.00653   0.00175  -0.0675   0.5878   1.0000
   2.500   0.5975   0.00671   0.00183  -0.0672   0.5637   1.0000
   2.750   0.6237   0.00690   0.00192  -0.0669   0.5394   1.0000
   3.000   0.6497   0.00712   0.00204  -0.0665   0.5142   1.0000
   3.250   0.6755   0.00735   0.00216  -0.0662   0.4851   1.0000
   3.500   0.7013   0.00761   0.00229  -0.0658   0.4567   1.0000
   3.750   0.7273   0.00784   0.00244  -0.0655   0.4310   1.0000
   4.000   0.7532   0.00810   0.00262  -0.0652   0.4045   1.0000
   4.250   0.7789   0.00838   0.00280  -0.0648   0.3778   1.0000
   4.500   0.8046   0.00867   0.00300  -0.0645   0.3538   1.0000
   4.750   0.8301   0.00898   0.00322  -0.0642   0.3277   1.0000
   5.000   0.8551   0.00934   0.00346  -0.0638   0.2961   1.0000
   5.250   0.8801   0.00971   0.00371  -0.0634   0.2687   1.0000
   5.500   0.9052   0.01007   0.00398  -0.0630   0.2452   1.0000
   5.750   0.9305   0.01041   0.00428  -0.0626   0.2235   1.0000
   6.250   0.9802   0.01118   0.00492  -0.0618   0.1829   1.0000
   6.500   1.0045   0.01162   0.00528  -0.0613   0.1623   1.0000
   6.750   1.0288   0.01205   0.00566  -0.0609   0.1433   1.0000
   7.000   1.0528   0.01251   0.00608  -0.0604   0.1257   1.0000
   7.250   1.0760   0.01305   0.00653  -0.0597   0.1071   1.0000
   7.500   1.0996   0.01355   0.00699  -0.0592   0.0910   1.0000
   7.750   1.1226   0.01410   0.00749  -0.0585   0.0770   1.0000
   8.000   1.1453   0.01467   0.00804  -0.0578   0.0658   1.0000
   8.250   1.1672   0.01531   0.00867  -0.0570   0.0563   1.0000
   8.500   1.1901   0.01582   0.00921  -0.0564   0.0497   1.0000
   8.750   1.2119   0.01643   0.00985  -0.0555   0.0434   1.0000
   9.000   1.2326   0.01715   0.01056  -0.0546   0.0366   1.0000
   9.250   1.2541   0.01774   0.01123  -0.0537   0.0314   1.0000
   9.500   1.2713   0.01878   0.01229  -0.0523   0.0255   1.0000
   9.750   1.2922   0.01939   0.01297  -0.0513   0.0216   1.0000
  10.000   1.3077   0.02049   0.01413  -0.0497   0.0181   1.0000
  10.250   1.3283   0.02104   0.01473  -0.0488   0.0157   1.0000
  10.500   1.3413   0.02225   0.01599  -0.0469   0.0133   1.0000
  10.750   1.3588   0.02299   0.01682  -0.0456   0.0120   1.0000
  11.000   1.3743   0.02383   0.01775  -0.0441   0.0107   1.0000
  11.250   1.3834   0.02498   0.01897  -0.0417   0.0096   1.0000
  11.500   1.3833   0.02661   0.02074  -0.0381   0.0087   1.0000
  11.750   1.3930   0.02761   0.02187  -0.0359   0.0080   1.0000
  12.000   1.4003   0.02878   0.02316  -0.0336   0.0072   1.0000
  12.250   1.4027   0.03034   0.02482  -0.0312   0.0065   1.0000
  12.500   1.3892   0.03326   0.02789  -0.0279   0.0059   1.0000
  12.750   1.3896   0.03529   0.03008  -0.0262   0.0057   1.0000
  13.000   1.3921   0.03728   0.03223  -0.0250   0.0049   1.0000
  13.250   1.3888   0.03998   0.03506  -0.0241   0.0048   1.0000
  13.500   1.3857   0.04286   0.03807  -0.0237   0.0045   1.0000
  13.750   1.3795   0.04636   0.04170  -0.0239   0.0042   1.0000
  14.000   1.3701   0.05059   0.04608  -0.0247   0.0042   1.0000
  14.250   1.3543   0.05607   0.05173  -0.0264   0.0040   1.0000
  14.500   1.3427   0.06137   0.05719  -0.0285   0.0040   1.0000
  14.750   1.3158   0.06945   0.06547  -0.0321   0.0038   1.0000
  15.000   1.3098   0.07454   0.07069  -0.0347   0.0039   1.0000
  15.250   1.2885   0.08249   0.07883  -0.0387   0.0038   1.0000
  15.500   1.2701   0.09030   0.08680  -0.0429   0.0038   1.0000
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