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

S3010-103-84 (s3010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.54 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3010-il-1000000.txt
Download as CSV file: xf-s3010-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4445   0.08466   0.08308  -0.0214   1.0000   0.0144
  -9.000  -0.4441   0.08071   0.07915  -0.0236   1.0000   0.0147
  -8.750  -0.4478   0.07588   0.07434  -0.0264   1.0000   0.0147
  -8.500  -0.4522   0.07126   0.06976  -0.0293   1.0000   0.0149
  -8.250  -0.4644   0.06582   0.06437  -0.0331   1.0000   0.0151
  -8.000  -0.4846   0.05204   0.05052  -0.0483   1.0000   0.0150
  -7.750  -0.4802   0.03780   0.03573  -0.0608   0.9569   0.0157
  -7.500  -0.4739   0.03343   0.03065  -0.0605   0.9293   0.0171
  -7.250  -0.4883   0.01976   0.01578  -0.0593   0.9084   0.0122
  -7.000  -0.4688   0.01695   0.01250  -0.0583   0.8960   0.0117
  -6.750  -0.4451   0.01565   0.01097  -0.0576   0.8845   0.0119
  -6.500  -0.4201   0.01464   0.00979  -0.0572   0.8735   0.0121
  -6.250  -0.3946   0.01384   0.00884  -0.0567   0.8630   0.0124
  -6.000  -0.3687   0.01315   0.00801  -0.0563   0.8523   0.0127
  -5.750  -0.3423   0.01248   0.00723  -0.0559   0.8418   0.0129
  -5.500  -0.3156   0.01195   0.00659  -0.0556   0.8316   0.0131
  -5.250  -0.2889   0.01144   0.00597  -0.0553   0.8212   0.0132
  -5.000  -0.2616   0.01103   0.00549  -0.0551   0.8108   0.0134
  -4.750  -0.2348   0.01043   0.00479  -0.0548   0.8007   0.0136
  -4.500  -0.2082   0.00976   0.00402  -0.0545   0.7901   0.0141
  -4.250  -0.1807   0.00938   0.00360  -0.0544   0.7796   0.0148
  -4.000  -0.1529   0.00910   0.00326  -0.0543   0.7693   0.0155
  -3.500  -0.0969   0.00861   0.00263  -0.0540   0.7476   0.0169
  -3.250  -0.0689   0.00833   0.00228  -0.0538   0.7368   0.0183
  -3.000  -0.0407   0.00814   0.00204  -0.0537   0.7258   0.0201
  -2.750  -0.0125   0.00795   0.00182  -0.0536   0.7141   0.0247
  -2.500   0.0153   0.00755   0.00159  -0.0536   0.7027   0.0688
  -2.250   0.0432   0.00729   0.00146  -0.0536   0.6911   0.1140
  -2.000   0.0712   0.00708   0.00135  -0.0536   0.6790   0.1582
  -1.750   0.0992   0.00688   0.00126  -0.0536   0.6666   0.2052
  -1.500   0.1272   0.00667   0.00119  -0.0537   0.6542   0.2615
  -1.250   0.1552   0.00648   0.00114  -0.0537   0.6418   0.3198
  -1.000   0.1830   0.00624   0.00110  -0.0537   0.6294   0.4007
  -0.750   0.2108   0.00605   0.00108  -0.0537   0.6165   0.4744
  -0.500   0.2385   0.00589   0.00107  -0.0536   0.6034   0.5452
  -0.250   0.2661   0.00573   0.00108  -0.0535   0.5898   0.6192
   0.250   0.3211   0.00554   0.00112  -0.0531   0.5624   0.7330
   0.500   0.3480   0.00546   0.00115  -0.0527   0.5488   0.7896
   0.750   0.3738   0.00539   0.00119  -0.0521   0.5357   0.8470
   1.000   0.3980   0.00533   0.00123  -0.0509   0.5229   0.9024
   1.250   0.4249   0.00531   0.00125  -0.0503   0.5096   0.9593
   1.500   0.4654   0.00538   0.00125  -0.0530   0.4949   1.0000
   2.000   0.5211   0.00560   0.00133  -0.0528   0.4681   1.0000
   2.250   0.5490   0.00572   0.00138  -0.0528   0.4545   1.0000
   2.500   0.5769   0.00585   0.00144  -0.0527   0.4411   1.0000
   2.750   0.6048   0.00598   0.00151  -0.0527   0.4275   1.0000
   3.000   0.6326   0.00612   0.00158  -0.0526   0.4140   1.0000
   3.250   0.6604   0.00627   0.00167  -0.0526   0.4006   1.0000
   3.500   0.6881   0.00642   0.00176  -0.0525   0.3869   1.0000
   3.750   0.7157   0.00658   0.00186  -0.0525   0.3732   1.0000
   4.000   0.7433   0.00675   0.00198  -0.0524   0.3586   1.0000
   4.250   0.7708   0.00693   0.00209  -0.0524   0.3442   1.0000
   4.500   0.7983   0.00712   0.00222  -0.0523   0.3291   1.0000
   4.750   0.8256   0.00732   0.00236  -0.0522   0.3142   1.0000
   5.000   0.8528   0.00753   0.00251  -0.0521   0.2990   1.0000
   5.250   0.8799   0.00775   0.00267  -0.0520   0.2837   1.0000
   5.500   0.9069   0.00799   0.00285  -0.0519   0.2688   1.0000
   5.750   0.9337   0.00823   0.00304  -0.0518   0.2535   1.0000
   6.000   0.9604   0.00849   0.00324  -0.0517   0.2390   1.0000
   6.250   0.9869   0.00876   0.00345  -0.0515   0.2242   1.0000
   6.500   1.0133   0.00904   0.00368  -0.0514   0.2097   1.0000
   6.750   1.0394   0.00934   0.00392  -0.0512   0.1950   1.0000
   7.000   1.0654   0.00966   0.00417  -0.0510   0.1816   1.0000
   7.250   1.0912   0.00998   0.00445  -0.0508   0.1685   1.0000
   7.500   1.1169   0.01031   0.00473  -0.0506   0.1560   1.0000
   7.750   1.1426   0.01062   0.00501  -0.0503   0.1451   1.0000
   8.000   1.1680   0.01096   0.00532  -0.0501   0.1344   1.0000
   8.250   1.1929   0.01135   0.00566  -0.0497   0.1224   1.0000
   8.500   1.2174   0.01176   0.00602  -0.0494   0.1106   1.0000
   8.750   1.2415   0.01219   0.00640  -0.0490   0.0997   1.0000
   9.000   1.2654   0.01264   0.00680  -0.0486   0.0897   1.0000
   9.250   1.2895   0.01303   0.00718  -0.0481   0.0822   1.0000
   9.500   1.3129   0.01349   0.00761  -0.0477   0.0738   1.0000
   9.750   1.3354   0.01401   0.00809  -0.0471   0.0652   1.0000
  10.000   1.3581   0.01449   0.00855  -0.0465   0.0586   1.0000
  10.250   1.3805   0.01497   0.00903  -0.0459   0.0530   1.0000
  10.500   1.4017   0.01553   0.00957  -0.0452   0.0474   1.0000
  10.750   1.4235   0.01601   0.01007  -0.0445   0.0434   1.0000
  11.000   1.4435   0.01661   0.01066  -0.0436   0.0390   1.0000
  11.250   1.4640   0.01713   0.01120  -0.0428   0.0356   1.0000
  11.500   1.4823   0.01779   0.01185  -0.0417   0.0317   1.0000
  11.750   1.5009   0.01837   0.01247  -0.0406   0.0285   1.0000
  12.000   1.5161   0.01915   0.01323  -0.0392   0.0242   1.0000
  12.250   1.5294   0.01996   0.01404  -0.0375   0.0199   1.0000
  12.500   1.5355   0.02092   0.01500  -0.0346   0.0153   1.0000
  13.000   1.5450   0.02310   0.01724  -0.0295   0.0106   1.0000
  13.250   1.5493   0.02438   0.01858  -0.0273   0.0097   1.0000
  13.500   1.5540   0.02576   0.02004  -0.0255   0.0091   1.0000
  13.750   1.5594   0.02720   0.02156  -0.0241   0.0085   1.0000
  14.000   1.5643   0.02877   0.02322  -0.0228   0.0083   1.0000
  14.250   1.5655   0.03078   0.02530  -0.0217   0.0078   1.0000
  14.500   1.5674   0.03285   0.02746  -0.0209   0.0076   1.0000
  14.750   1.5637   0.03562   0.03034  -0.0202   0.0073   1.0000
  15.000   1.5577   0.03882   0.03366  -0.0200   0.0070   1.0000
  15.250   1.5571   0.04160   0.03655  -0.0201   0.0069   1.0000
  15.500   1.5556   0.04462   0.03967  -0.0204   0.0068   1.0000
  15.750   1.5509   0.04817   0.04334  -0.0210   0.0068   1.0000
  16.000   1.5444   0.05212   0.04741  -0.0220   0.0067   1.0000
  16.250   1.5378   0.05624   0.05165  -0.0232   0.0065   1.0000
  16.500   1.5270   0.06116   0.05669  -0.0249   0.0065   1.0000
  16.750   1.5177   0.06610   0.06175  -0.0268   0.0065   1.0000
  17.000   1.5059   0.07161   0.06739  -0.0292   0.0064   1.0000
  17.250   1.4919   0.07769   0.07360  -0.0319   0.0064   1.0000
  17.500   1.4761   0.08427   0.08032  -0.0350   0.0063   1.0000
  17.750   1.4614   0.09086   0.08703  -0.0382   0.0063   1.0000
  18.000   1.4441   0.09812   0.09442  -0.0418   0.0063   1.0000
  18.250   1.4267   0.10556   0.10199  -0.0456   0.0063   1.0000
  18.500   1.4087   0.11332   0.10988  -0.0498   0.0062   1.0000
<< Back to S3010-103-84 (s3010-il)

Polar data table (+)

Polar graphs


<< Back to S3010-103-84 (s3010-il)