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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 500,000
Max Cl/Cd: 55.17 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1010-il-500000-n5.txt
Download as CSV file: xf-s1010-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1010 HPV airfoil                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.9494   0.07114   0.06889  -0.0018   1.0000   0.0037
 -11.750  -0.9820   0.05952   0.05725  -0.0110   1.0000   0.0035
 -11.500  -1.0046   0.04780   0.04530  -0.0198   1.0000   0.0034
 -11.000  -1.0405   0.03759   0.03449  -0.0188   1.0000   0.0034
 -10.750  -1.0453   0.03322   0.02970  -0.0176   1.0000   0.0035
 -10.500  -1.0420   0.02968   0.02576  -0.0162   1.0000   0.0036
 -10.250  -1.0319   0.02699   0.02273  -0.0150   1.0000   0.0037
 -10.000  -1.0172   0.02496   0.02043  -0.0140   1.0000   0.0039
  -9.750  -0.9989   0.02349   0.01876  -0.0132   1.0000   0.0041
  -9.500  -0.9788   0.02231   0.01742  -0.0125   1.0000   0.0044
  -9.250  -0.9572   0.02139   0.01636  -0.0119   1.0000   0.0048
  -9.000  -0.9358   0.02035   0.01516  -0.0112   1.0000   0.0051
  -8.750  -0.9137   0.01939   0.01404  -0.0105   1.0000   0.0056
  -8.500  -0.8917   0.01836   0.01280  -0.0098   1.0000   0.0060
  -8.250  -0.8693   0.01740   0.01166  -0.0091   1.0000   0.0064
  -8.000  -0.8477   0.01618   0.01027  -0.0082   1.0000   0.0071
  -7.750  -0.8242   0.01542   0.00943  -0.0076   1.0000   0.0081
  -7.500  -0.8000   0.01484   0.00876  -0.0071   1.0000   0.0093
  -7.250  -0.7756   0.01429   0.00811  -0.0065   1.0000   0.0105
  -7.000  -0.7507   0.01388   0.00760  -0.0060   1.0000   0.0113
  -6.750  -0.7270   0.01317   0.00682  -0.0053   1.0000   0.0136
  -6.500  -0.7023   0.01276   0.00636  -0.0048   1.0000   0.0154
  -6.250  -0.6775   0.01235   0.00589  -0.0043   1.0000   0.0167
  -6.000  -0.6529   0.01192   0.00539  -0.0036   1.0000   0.0183
  -5.750  -0.6286   0.01142   0.00486  -0.0029   1.0000   0.0212
  -5.500  -0.6041   0.01104   0.00445  -0.0023   1.0000   0.0238
  -5.250  -0.5796   0.01068   0.00406  -0.0016   1.0000   0.0282
  -5.000  -0.5553   0.01033   0.00373  -0.0009   1.0000   0.0358
  -4.750  -0.5311   0.01002   0.00340  -0.0001   1.0000   0.0430
  -4.500  -0.5066   0.00978   0.00315   0.0006   1.0000   0.0494
  -4.250  -0.4825   0.00951   0.00291   0.0014   1.0000   0.0576
  -4.000  -0.4583   0.00929   0.00270   0.0021   1.0000   0.0647
  -3.750  -0.4343   0.00908   0.00251   0.0029   1.0000   0.0733
  -3.500  -0.4106   0.00887   0.00234   0.0038   1.0000   0.0845
  -3.250  -0.3871   0.00866   0.00217   0.0046   1.0000   0.0990
  -2.750  -0.3299   0.00829   0.00190   0.0041   0.9968   0.1280
  -2.500  -0.2972   0.00811   0.00179   0.0030   0.9940   0.1430
  -2.250  -0.2659   0.00793   0.00167   0.0022   0.9907   0.1609
  -2.000  -0.2339   0.00773   0.00157   0.0012   0.9872   0.1872
  -1.750  -0.1937   0.00749   0.00147  -0.0015   0.9811   0.2230
  -1.500  -0.1534   0.00716   0.00134  -0.0041   0.9598   0.2754
  -1.250  -0.1196   0.00684   0.00121  -0.0053   0.9341   0.3377
  -1.000  -0.0923   0.00649   0.00111  -0.0051   0.9113   0.4191
  -0.750  -0.0678   0.00611   0.00103  -0.0043   0.8887   0.5153
  -0.500  -0.0453   0.00563   0.00096  -0.0031   0.8665   0.6397
  -0.250  -0.0235   0.00530   0.00097  -0.0014   0.8412   0.7525
   0.000   0.0000   0.00523   0.00099   0.0000   0.8082   0.8081
   0.250   0.0236   0.00530   0.00097   0.0014   0.7534   0.8410
   0.500   0.0454   0.00563   0.00096   0.0030   0.6404   0.8666
   0.750   0.0678   0.00611   0.00103   0.0043   0.5148   0.8885
   1.000   0.0923   0.00649   0.00111   0.0051   0.4192   0.9111
   1.250   0.1196   0.00683   0.00121   0.0053   0.3382   0.9341
   1.500   0.1534   0.00716   0.00134   0.0041   0.2754   0.9598
   1.750   0.1937   0.00749   0.00147   0.0015   0.2224   0.9813
   2.000   0.2340   0.00773   0.00157  -0.0013   0.1874   0.9873
   2.250   0.2660   0.00793   0.00166  -0.0022   0.1611   0.9908
   2.500   0.2974   0.00811   0.00179  -0.0031   0.1431   0.9941
   2.750   0.3300   0.00828   0.00190  -0.0042   0.1280   0.9969
   3.250   0.3868   0.00866   0.00216  -0.0046   0.0989   1.0000
   3.500   0.4103   0.00886   0.00234  -0.0037   0.0849   1.0000
   3.750   0.4340   0.00908   0.00251  -0.0029   0.0733   1.0000
   4.000   0.4580   0.00929   0.00270  -0.0021   0.0647   1.0000
   4.250   0.4822   0.00951   0.00291  -0.0013   0.0577   1.0000
   4.500   0.5063   0.00978   0.00315  -0.0005   0.0495   1.0000
   4.750   0.5307   0.01002   0.00340   0.0002   0.0432   1.0000
   5.000   0.5550   0.01033   0.00373   0.0009   0.0359   1.0000
   5.250   0.5794   0.01068   0.00406   0.0016   0.0282   1.0000
   5.500   0.6039   0.01104   0.00444   0.0023   0.0238   1.0000
   5.750   0.6285   0.01142   0.00486   0.0030   0.0211   1.0000
   6.000   0.6528   0.01192   0.00538   0.0037   0.0184   1.0000
   6.250   0.6774   0.01235   0.00588   0.0043   0.0167   1.0000
   6.500   0.7023   0.01276   0.00637   0.0048   0.0154   1.0000
   6.750   0.7271   0.01318   0.00686   0.0053   0.0136   1.0000
   7.000   0.7508   0.01388   0.00761   0.0060   0.0113   1.0000
   7.250   0.7757   0.01431   0.00813   0.0065   0.0105   1.0000
   7.500   0.8002   0.01484   0.00876   0.0070   0.0093   1.0000
   7.750   0.8244   0.01544   0.00945   0.0076   0.0081   1.0000
   8.000   0.8478   0.01621   0.01030   0.0082   0.0070   1.0000
   8.250   0.8695   0.01740   0.01167   0.0090   0.0064   1.0000
   8.500   0.8920   0.01837   0.01281   0.0097   0.0060   1.0000
   8.750   0.9141   0.01938   0.01403   0.0105   0.0056   1.0000
   9.000   0.9360   0.02039   0.01520   0.0112   0.0051   1.0000
   9.250   0.9579   0.02132   0.01628   0.0118   0.0047   1.0000
   9.500   0.9798   0.02218   0.01727   0.0123   0.0044   1.0000
   9.750   0.9999   0.02337   0.01862   0.0131   0.0041   1.0000
  10.000   1.0176   0.02497   0.02045   0.0139   0.0039   1.0000
  10.250   1.0324   0.02700   0.02274   0.0149   0.0037   1.0000
  10.500   1.0413   0.02989   0.02599   0.0162   0.0035   1.0000
  10.750   1.0439   0.03354   0.03005   0.0175   0.0034   1.0000
  11.000   1.0369   0.03823   0.03518   0.0187   0.0034   1.0000
  11.500   1.0051   0.04793   0.04543   0.0195   0.0034   1.0000
  11.750   0.9772   0.06116   0.05889   0.0092   0.0034   1.0000
  12.000   0.9483   0.07168   0.06942   0.0013   0.0037   1.0000
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