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S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S9033 (7.5%) (s9033-il)
Reynolds number: 100,000
Max Cl/Cd: 29.52 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9033-il-100000.txt
Download as CSV file: xf-s9033-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9033 (7.5%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.7012   0.09308   0.08824   0.0112   1.0000   0.1552
  -8.500  -0.7012   0.08788   0.08309   0.0101   1.0000   0.1573
  -8.250  -0.8014   0.05313   0.04719  -0.0142   1.0000   0.0735
  -8.000  -0.7970   0.04816   0.04170  -0.0142   1.0000   0.0739
  -7.750  -0.7884   0.04328   0.03632  -0.0138   1.0000   0.0744
  -7.500  -0.7748   0.03883   0.03138  -0.0132   1.0000   0.0745
  -7.250  -0.7585   0.03467   0.02682  -0.0125   1.0000   0.0754
  -7.000  -0.7384   0.03178   0.02369  -0.0119   1.0000   0.0775
  -6.750  -0.7165   0.02946   0.02110  -0.0111   1.0000   0.0807
  -6.500  -0.6940   0.02752   0.01858  -0.0101   1.0000   0.0865
  -6.250  -0.6711   0.02555   0.01659  -0.0096   1.0000   0.0934
  -6.000  -0.6465   0.02373   0.01437  -0.0086   1.0000   0.1013
  -5.750  -0.6223   0.02235   0.01296  -0.0080   1.0000   0.1129
  -5.500  -0.5980   0.02112   0.01168  -0.0073   1.0000   0.1268
  -5.250  -0.5734   0.01998   0.01049  -0.0066   1.0000   0.1423
  -5.000  -0.5491   0.01888   0.00950  -0.0059   1.0000   0.1596
  -4.750  -0.5246   0.01799   0.00864  -0.0052   1.0000   0.1810
  -4.500  -0.5003   0.01701   0.00779  -0.0045   1.0000   0.2046
  -4.250  -0.4761   0.01613   0.00705  -0.0037   1.0000   0.2342
  -4.000  -0.4523   0.01533   0.00641  -0.0029   1.0000   0.2716
  -3.750  -0.4288   0.01456   0.00588  -0.0020   1.0000   0.3149
  -3.500  -0.4055   0.01387   0.00544  -0.0010   1.0000   0.3677
  -3.250  -0.3830   0.01320   0.00511   0.0002   1.0000   0.4276
  -3.000  -0.3609   0.01260   0.00484   0.0016   1.0000   0.4960
  -2.750  -0.3394   0.01204   0.00463   0.0033   1.0000   0.5699
  -2.500  -0.3185   0.01155   0.00449   0.0054   1.0000   0.6460
  -2.250  -0.2977   0.01114   0.00438   0.0078   1.0000   0.7243
  -2.000  -0.2763   0.01083   0.00434   0.0105   1.0000   0.8044
  -1.750  -0.2410   0.01074   0.00436   0.0108   1.0000   0.8891
  -1.500  -0.1752   0.01084   0.00435   0.0044   1.0000   0.9566
  -1.250  -0.0918   0.01080   0.00408  -0.0066   1.0000   0.9979
  -1.000  -0.0728   0.01055   0.00377  -0.0059   1.0000   1.0000
  -0.750  -0.0557   0.01040   0.00356  -0.0044   1.0000   1.0000
  -0.500  -0.0374   0.01031   0.00343  -0.0030   1.0000   1.0000
  -0.250  -0.0187   0.01026   0.00335  -0.0015   1.0000   1.0000
   0.000   0.0000   0.01025   0.00333   0.0000   1.0000   1.0000
   0.250   0.0187   0.01026   0.00335   0.0015   1.0000   1.0000
   0.500   0.0374   0.01031   0.00343   0.0030   1.0000   1.0000
   0.750   0.0557   0.01040   0.00356   0.0044   1.0000   1.0000
   1.000   0.0727   0.01055   0.00377   0.0059   1.0000   1.0000
   1.250   0.0919   0.01080   0.00408   0.0066   0.9979   1.0000
   1.500   0.1752   0.01085   0.00435  -0.0044   0.9566   1.0000
   1.750   0.2411   0.01074   0.00436  -0.0108   0.8890   1.0000
   2.000   0.2763   0.01083   0.00434  -0.0105   0.8043   1.0000
   2.250   0.2978   0.01114   0.00438  -0.0078   0.7244   1.0000
   2.500   0.3186   0.01155   0.00449  -0.0054   0.6459   1.0000
   2.750   0.3395   0.01204   0.00463  -0.0033   0.5698   1.0000
   3.000   0.3609   0.01260   0.00484  -0.0016   0.4960   1.0000
   3.250   0.3830   0.01320   0.00511  -0.0002   0.4276   1.0000
   3.500   0.4056   0.01387   0.00544   0.0010   0.3676   1.0000
   3.750   0.4288   0.01456   0.00588   0.0020   0.3149   1.0000
   4.000   0.4523   0.01533   0.00641   0.0029   0.2716   1.0000
   4.250   0.4761   0.01613   0.00705   0.0037   0.2343   1.0000
   4.500   0.5003   0.01700   0.00779   0.0045   0.2046   1.0000
   4.750   0.5246   0.01799   0.00864   0.0052   0.1810   1.0000
   5.000   0.5491   0.01888   0.00950   0.0059   0.1596   1.0000
   5.250   0.5734   0.01998   0.01049   0.0066   0.1423   1.0000
   5.500   0.5980   0.02112   0.01168   0.0073   0.1267   1.0000
   5.750   0.6223   0.02235   0.01296   0.0080   0.1129   1.0000
   6.000   0.6465   0.02374   0.01437   0.0086   0.1013   1.0000
   6.250   0.6710   0.02555   0.01659   0.0096   0.0935   1.0000
   6.500   0.6939   0.02753   0.01858   0.0101   0.0865   1.0000
   6.750   0.7164   0.02946   0.02110   0.0111   0.0808   1.0000
   7.000   0.7384   0.03178   0.02369   0.0119   0.0775   1.0000
   7.250   0.7584   0.03466   0.02681   0.0126   0.0754   1.0000
   7.500   0.7747   0.03882   0.03136   0.0132   0.0745   1.0000
   7.750   0.7881   0.04332   0.03636   0.0138   0.0743   1.0000
   8.000   0.7969   0.04815   0.04169   0.0142   0.0739   1.0000
   8.250   0.8013   0.05311   0.04717   0.0142   0.0735   1.0000
   8.500   0.7019   0.08789   0.08309  -0.0100   0.1573   1.0000
   8.750   0.7014   0.09310   0.08826  -0.0113   0.1552   1.0000
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