Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S9033 (7.5%) (s9033-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.02 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9033-il-1000000-n5.txt
Download as CSV file: xf-s9033-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -1.1604   0.09247   0.09011   0.0100   1.0000   0.0031
 -15.750  -1.2507   0.07112   0.06851  -0.0033   1.0000   0.0026
 -15.500  -1.3270   0.05132   0.04838  -0.0177   1.0000   0.0024
 -15.250  -1.3568   0.04229   0.03912  -0.0252   1.0000   0.0024
 -15.000  -1.3765   0.03730   0.03395  -0.0277   1.0000   0.0024
 -14.750  -1.3886   0.03444   0.03095  -0.0270   1.0000   0.0024
 -14.500  -1.3971   0.03241   0.02878  -0.0245   1.0000   0.0025
 -14.250  -1.3967   0.03070   0.02694  -0.0223   1.0000   0.0025
 -14.000  -1.3895   0.02910   0.02520  -0.0209   1.0000   0.0026
 -13.750  -1.3807   0.02745   0.02341  -0.0196   1.0000   0.0029
 -13.500  -1.3678   0.02608   0.02192  -0.0184   1.0000   0.0031
 -13.250  -1.3529   0.02483   0.02056  -0.0174   1.0000   0.0034
 -13.000  -1.3362   0.02371   0.01933  -0.0165   1.0000   0.0036
 -12.750  -1.3180   0.02270   0.01821  -0.0157   1.0000   0.0040
 -12.500  -1.2988   0.02177   0.01717  -0.0150   1.0000   0.0043
 -12.250  -1.2787   0.02090   0.01624  -0.0143   1.0000   0.0049
 -12.000  -1.2575   0.02014   0.01542  -0.0137   1.0000   0.0055
 -11.750  -1.2357   0.01944   0.01465  -0.0131   1.0000   0.0060
 -11.500  -1.2133   0.01878   0.01391  -0.0125   1.0000   0.0064
 -11.250  -1.1908   0.01811   0.01317  -0.0120   1.0000   0.0069
 -11.000  -1.1676   0.01753   0.01256  -0.0115   1.0000   0.0075
 -10.750  -1.1440   0.01701   0.01197  -0.0110   1.0000   0.0080
 -10.500  -1.1200   0.01651   0.01142  -0.0105   1.0000   0.0085
 -10.250  -1.0958   0.01603   0.01088  -0.0101   1.0000   0.0090
 -10.000  -1.0713   0.01557   0.01036  -0.0097   1.0000   0.0093
  -9.750  -1.0466   0.01515   0.00987  -0.0092   1.0000   0.0096
  -9.500  -1.0216   0.01476   0.00942  -0.0088   1.0000   0.0097
  -9.250  -0.9977   0.01411   0.00871  -0.0083   1.0000   0.0105
  -9.000  -0.9729   0.01364   0.00819  -0.0079   1.0000   0.0113
  -8.750  -0.9476   0.01329   0.00784  -0.0076   1.0000   0.0122
  -8.500  -0.9220   0.01296   0.00748  -0.0072   1.0000   0.0129
  -8.250  -0.8965   0.01258   0.00706  -0.0068   1.0000   0.0134
  -8.000  -0.8708   0.01226   0.00669  -0.0064   1.0000   0.0138
  -7.750  -0.8450   0.01193   0.00632  -0.0060   1.0000   0.0140
  -7.500  -0.8196   0.01149   0.00581  -0.0056   1.0000   0.0145
  -7.250  -0.7942   0.01104   0.00530  -0.0051   1.0000   0.0153
  -7.000  -0.7684   0.01067   0.00490  -0.0047   1.0000   0.0163
  -6.750  -0.7426   0.01034   0.00456  -0.0042   1.0000   0.0174
  -6.500  -0.7166   0.01004   0.00424  -0.0038   1.0000   0.0185
  -6.250  -0.6905   0.00978   0.00395  -0.0034   1.0000   0.0197
  -6.000  -0.6645   0.00949   0.00365  -0.0030   1.0000   0.0226
  -5.750  -0.6386   0.00920   0.00339  -0.0025   1.0000   0.0263
  -5.500  -0.6127   0.00893   0.00314  -0.0021   1.0000   0.0313
  -5.250  -0.5867   0.00869   0.00293  -0.0016   1.0000   0.0366
  -5.000  -0.5608   0.00847   0.00271  -0.0011   1.0000   0.0415
  -4.750  -0.5350   0.00826   0.00252  -0.0006   1.0000   0.0467
  -4.500  -0.5091   0.00808   0.00235  -0.0001   1.0000   0.0511
  -4.250  -0.4835   0.00787   0.00218   0.0005   1.0000   0.0575
  -4.000  -0.4578   0.00770   0.00202   0.0011   1.0000   0.0635
  -3.750  -0.4298   0.00750   0.00187   0.0011   0.9989   0.0728
  -3.500  -0.3956   0.00725   0.00172  -0.0003   0.9944   0.0920
  -3.250  -0.3626   0.00702   0.00159  -0.0014   0.9875   0.1115
  -3.000  -0.3278   0.00684   0.00146  -0.0028   0.9742   0.1272
  -2.500  -0.2641   0.00665   0.00122  -0.0040   0.8825   0.1585
  -2.250  -0.2394   0.00668   0.00112  -0.0031   0.8284   0.1738
  -2.000  -0.2142   0.00674   0.00103  -0.0023   0.7694   0.1906
  -1.750  -0.1883   0.00676   0.00096  -0.0018   0.7147   0.2144
  -1.250  -0.1350   0.00672   0.00083  -0.0011   0.6273   0.2699
  -1.000  -0.1082   0.00666   0.00078  -0.0009   0.5886   0.3081
  -0.750  -0.0811   0.00663   0.00074  -0.0007   0.5552   0.3393
  -0.500  -0.0540   0.00665   0.00072  -0.0004   0.5142   0.3647
  -0.250  -0.0271   0.00670   0.00070  -0.0002   0.4657   0.3919
   0.000   0.0000   0.00671   0.00069   0.0000   0.4269   0.4270
   0.250   0.0270   0.00671   0.00070   0.0002   0.3918   0.4654
   0.500   0.0540   0.00665   0.00072   0.0004   0.3646   0.5135
   0.750   0.0811   0.00663   0.00074   0.0007   0.3391   0.5552
   1.000   0.1082   0.00666   0.00078   0.0009   0.3080   0.5887
   1.250   0.1350   0.00672   0.00083   0.0011   0.2700   0.6275
   1.750   0.1882   0.00676   0.00096   0.0018   0.2143   0.7145
   2.000   0.2142   0.00674   0.00103   0.0023   0.1905   0.7694
   2.250   0.2394   0.00667   0.00112   0.0031   0.1738   0.8290
   2.500   0.2641   0.00665   0.00122   0.0040   0.1585   0.8826
   2.750   0.2906   0.00668   0.00134   0.0047   0.1436   0.9397
   3.000   0.3277   0.00684   0.00146   0.0028   0.1272   0.9742
   3.250   0.3624   0.00702   0.00159   0.0014   0.1117   0.9873
   3.500   0.3954   0.00725   0.00172   0.0003   0.0922   0.9943
   3.750   0.4296   0.00750   0.00187  -0.0010   0.0730   0.9987
   4.000   0.4580   0.00770   0.00202  -0.0011   0.0635   1.0000
   4.250   0.4837   0.00787   0.00218  -0.0005   0.0576   1.0000
   4.500   0.5093   0.00807   0.00235   0.0000   0.0512   1.0000
   4.750   0.5351   0.00826   0.00252   0.0006   0.0468   1.0000
   5.000   0.5609   0.00847   0.00271   0.0011   0.0416   1.0000
   5.250   0.5868   0.00869   0.00293   0.0016   0.0366   1.0000
   5.500   0.6127   0.00893   0.00314   0.0021   0.0313   1.0000
   5.750   0.6386   0.00920   0.00339   0.0025   0.0263   1.0000
   6.000   0.6645   0.00949   0.00365   0.0030   0.0226   1.0000
   6.250   0.6905   0.00978   0.00395   0.0034   0.0197   1.0000
   6.500   0.7165   0.01004   0.00424   0.0038   0.0186   1.0000
   6.750   0.7425   0.01034   0.00456   0.0043   0.0174   1.0000
   7.000   0.7684   0.01067   0.00490   0.0047   0.0163   1.0000
   7.250   0.7941   0.01104   0.00530   0.0051   0.0154   1.0000
   7.500   0.8195   0.01148   0.00580   0.0056   0.0145   1.0000
   7.750   0.8449   0.01192   0.00631   0.0061   0.0140   1.0000
   8.000   0.8707   0.01225   0.00669   0.0065   0.0138   1.0000
   8.250   0.8963   0.01259   0.00707   0.0068   0.0134   1.0000
   8.500   0.9218   0.01295   0.00747   0.0072   0.0129   1.0000
   8.750   0.9474   0.01328   0.00783   0.0076   0.0122   1.0000
   9.000   0.9727   0.01363   0.00818   0.0079   0.0112   1.0000
   9.250   0.9974   0.01411   0.00871   0.0084   0.0104   1.0000
   9.500   1.0213   0.01476   0.00942   0.0089   0.0097   1.0000
   9.750   1.0463   0.01515   0.00987   0.0093   0.0096   1.0000
  10.000   1.0710   0.01558   0.01036   0.0097   0.0093   1.0000
  10.250   1.0954   0.01603   0.01088   0.0102   0.0090   1.0000
  10.500   1.1196   0.01651   0.01142   0.0106   0.0085   1.0000
  10.750   1.1436   0.01700   0.01196   0.0111   0.0080   1.0000
  11.000   1.1672   0.01753   0.01255   0.0116   0.0075   1.0000
  11.250   1.1903   0.01811   0.01318   0.0121   0.0069   1.0000
  11.500   1.2129   0.01877   0.01390   0.0126   0.0064   1.0000
  11.750   1.2352   0.01943   0.01464   0.0132   0.0060   1.0000
  12.000   1.2570   0.02013   0.01542   0.0138   0.0055   1.0000
  12.250   1.2781   0.02089   0.01623   0.0144   0.0049   1.0000
  12.500   1.2982   0.02176   0.01716   0.0151   0.0043   1.0000
  12.750   1.3174   0.02269   0.01820   0.0158   0.0040   1.0000
  13.000   1.3355   0.02371   0.01934   0.0167   0.0036   1.0000
  13.250   1.3522   0.02484   0.02057   0.0176   0.0033   1.0000
  13.500   1.3669   0.02610   0.02194   0.0186   0.0030   1.0000
  13.750   1.3801   0.02744   0.02340   0.0197   0.0029   1.0000
  14.000   1.3891   0.02908   0.02518   0.0210   0.0026   1.0000
  14.250   1.3959   0.03071   0.02695   0.0224   0.0025   1.0000
  14.500   1.3966   0.03238   0.02875   0.0246   0.0024   1.0000
  14.750   1.3890   0.03437   0.03087   0.0270   0.0025   1.0000
  15.000   1.3762   0.03729   0.03395   0.0278   0.0024   1.0000
  15.250   1.3567   0.04225   0.03909   0.0252   0.0024   1.0000
  15.500   1.3240   0.05192   0.04899   0.0172   0.0025   1.0000
  15.750   1.2533   0.07063   0.06802   0.0035   0.0026   1.0000
  16.000   1.1588   0.09283   0.09048  -0.0103   0.0031   1.0000
<< Back to S9033 (7.5%) (s9033-il)

Polar data table (+)

Polar graphs


<< Back to S9033 (7.5%) (s9033-il)