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

SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 1,000,000
Max Cl/Cd: 94.86 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd5060-il-1000000-n5.txt
Download as CSV file: xf-sd5060-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD5060 (9.5%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.8407   0.09568   0.09369  -0.0110   1.0000   0.0056
 -14.250  -0.9158   0.07786   0.07573  -0.0223   1.0000   0.0054
 -14.000  -0.9889   0.06162   0.05934  -0.0330   1.0000   0.0052
 -13.750  -1.0742   0.04044   0.03782  -0.0505   1.0000   0.0050
 -13.500  -1.1111   0.03338   0.03051  -0.0555   1.0000   0.0050
 -13.250  -1.1067   0.03121   0.02821  -0.0556   1.0000   0.0051
 -13.000  -1.0981   0.02926   0.02611  -0.0554   1.0000   0.0052
 -12.750  -1.0852   0.02762   0.02433  -0.0552   1.0000   0.0053
 -12.500  -1.0701   0.02612   0.02269  -0.0550   1.0000   0.0054
 -12.250  -1.0528   0.02480   0.02124  -0.0547   1.0000   0.0056
 -12.000  -1.0343   0.02353   0.01985  -0.0545   1.0000   0.0057
 -11.750  -1.0137   0.02252   0.01872  -0.0542   1.0000   0.0058
 -11.500  -0.9928   0.02149   0.01755  -0.0540   1.0000   0.0059
 -11.250  -0.9713   0.02046   0.01641  -0.0538   1.0000   0.0060
 -11.000  -0.9498   0.01938   0.01521  -0.0535   1.0000   0.0063
 -10.750  -0.9259   0.01872   0.01451  -0.0534   1.0000   0.0066
 -10.500  -0.9013   0.01818   0.01391  -0.0532   1.0000   0.0068
 -10.250  -0.8762   0.01770   0.01340  -0.0530   1.0000   0.0070
 -10.000  -0.8513   0.01715   0.01279  -0.0529   1.0000   0.0073
  -9.750  -0.8223   0.01662   0.01218  -0.0535   0.9874   0.0076
  -9.500  -0.7910   0.01607   0.01156  -0.0546   0.9740   0.0080
  -9.250  -0.7627   0.01554   0.01094  -0.0551   0.9602   0.0083
  -9.000  -0.7376   0.01504   0.01033  -0.0547   0.9462   0.0085
  -8.750  -0.7132   0.01460   0.00979  -0.0541   0.9337   0.0087
  -8.500  -0.6885   0.01421   0.00931  -0.0536   0.9225   0.0088
  -8.250  -0.6652   0.01340   0.00835  -0.0530   0.9116   0.0092
  -8.000  -0.6398   0.01293   0.00781  -0.0526   0.9014   0.0096
  -7.750  -0.6137   0.01259   0.00742  -0.0523   0.8920   0.0100
  -7.500  -0.5875   0.01229   0.00705  -0.0520   0.8829   0.0104
  -7.250  -0.5609   0.01195   0.00663  -0.0518   0.8736   0.0108
  -7.000  -0.5342   0.01159   0.00619  -0.0515   0.8649   0.0112
  -6.750  -0.5075   0.01126   0.00577  -0.0513   0.8559   0.0116
  -6.500  -0.4803   0.01094   0.00539  -0.0511   0.8473   0.0119
  -6.250  -0.4531   0.01070   0.00507  -0.0509   0.8387   0.0122
  -6.000  -0.4256   0.01045   0.00476  -0.0508   0.8299   0.0125
  -5.750  -0.3987   0.00998   0.00418  -0.0506   0.8216   0.0131
  -5.500  -0.3712   0.00965   0.00379  -0.0505   0.8126   0.0136
  -5.250  -0.3435   0.00938   0.00347  -0.0504   0.8042   0.0142
  -4.750  -0.2879   0.00895   0.00292  -0.0502   0.7866   0.0154
  -4.500  -0.2599   0.00877   0.00268  -0.0501   0.7780   0.0161
  -4.250  -0.2318   0.00861   0.00247  -0.0500   0.7687   0.0168
  -4.000  -0.2037   0.00844   0.00225  -0.0499   0.7598   0.0178
  -3.750  -0.1757   0.00828   0.00205  -0.0498   0.7506   0.0198
  -3.500  -0.1474   0.00812   0.00187  -0.0498   0.7411   0.0234
  -3.250  -0.1196   0.00783   0.00166  -0.0498   0.7317   0.0467
  -3.000  -0.0917   0.00764   0.00151  -0.0497   0.7218   0.0653
  -2.750  -0.0635   0.00746   0.00137  -0.0497   0.7115   0.0873
  -2.500  -0.0354   0.00729   0.00127  -0.0497   0.7012   0.1107
  -2.250  -0.0072   0.00718   0.00117  -0.0497   0.6903   0.1302
  -2.000   0.0209   0.00707   0.00109  -0.0497   0.6786   0.1506
  -1.750   0.0492   0.00698   0.00103  -0.0497   0.6661   0.1706
  -1.500   0.0775   0.00692   0.00097  -0.0497   0.6533   0.1866
  -1.250   0.1057   0.00684   0.00092  -0.0496   0.6394   0.2090
  -1.000   0.1338   0.00674   0.00088  -0.0497   0.6242   0.2434
  -0.750   0.1618   0.00667   0.00085  -0.0496   0.6076   0.2757
  -0.500   0.1899   0.00665   0.00083  -0.0496   0.5903   0.2980
  -0.250   0.2181   0.00662   0.00082  -0.0496   0.5728   0.3253
   0.000   0.2462   0.00660   0.00082  -0.0496   0.5551   0.3516
   0.250   0.2742   0.00658   0.00083  -0.0496   0.5366   0.3840
   0.500   0.3021   0.00658   0.00085  -0.0496   0.5170   0.4170
   0.750   0.3300   0.00658   0.00087  -0.0496   0.4958   0.4545
   1.000   0.3577   0.00660   0.00092  -0.0495   0.4726   0.4940
   1.250   0.3854   0.00663   0.00097  -0.0495   0.4475   0.5366
   1.500   0.4129   0.00665   0.00104  -0.0494   0.4246   0.5821
   1.750   0.4402   0.00669   0.00112  -0.0493   0.3997   0.6315
   2.000   0.4673   0.00673   0.00121  -0.0492   0.3738   0.6825
   2.250   0.4940   0.00678   0.00132  -0.0490   0.3475   0.7378
   2.500   0.5199   0.00681   0.00144  -0.0485   0.3210   0.8015
   2.750   0.5439   0.00680   0.00157  -0.0476   0.3001   0.8744
   3.000   0.5704   0.00680   0.00167  -0.0470   0.2796   0.9640
   3.250   0.6037   0.00704   0.00179  -0.0483   0.2536   1.0000
   3.500   0.6310   0.00726   0.00193  -0.0481   0.2333   1.0000
   3.750   0.6582   0.00747   0.00206  -0.0480   0.2173   1.0000
   4.000   0.6854   0.00770   0.00221  -0.0479   0.2008   1.0000
   4.250   0.7125   0.00794   0.00237  -0.0478   0.1844   1.0000
   4.500   0.7396   0.00816   0.00253  -0.0477   0.1717   1.0000
   4.750   0.7667   0.00837   0.00269  -0.0476   0.1599   1.0000
   5.000   0.7937   0.00860   0.00287  -0.0474   0.1476   1.0000
   5.250   0.8207   0.00883   0.00306  -0.0473   0.1378   1.0000
   5.500   0.8475   0.00908   0.00326  -0.0471   0.1272   1.0000
   5.750   0.8743   0.00932   0.00346  -0.0470   0.1188   1.0000
   6.000   0.9010   0.00955   0.00367  -0.0468   0.1112   1.0000
   6.250   0.9274   0.00983   0.00392  -0.0466   0.1015   1.0000
   6.500   0.9540   0.01007   0.00415  -0.0464   0.0953   1.0000
   6.750   0.9803   0.01035   0.00439  -0.0462   0.0885   1.0000
   7.000   1.0065   0.01061   0.00465  -0.0460   0.0823   1.0000
   7.250   1.0324   0.01092   0.00493  -0.0457   0.0748   1.0000
   7.500   1.0578   0.01128   0.00525  -0.0455   0.0657   1.0000
   7.750   1.0836   0.01158   0.00554  -0.0452   0.0599   1.0000
   8.000   1.1086   0.01197   0.00589  -0.0448   0.0524   1.0000
   8.250   1.1330   0.01241   0.00628  -0.0444   0.0437   1.0000
   8.500   1.1574   0.01285   0.00669  -0.0440   0.0365   1.0000
   8.750   1.1817   0.01328   0.00711  -0.0436   0.0311   1.0000
   9.000   1.2054   0.01376   0.00756  -0.0431   0.0259   1.0000
   9.250   1.2294   0.01419   0.00800  -0.0426   0.0228   1.0000
   9.500   1.2525   0.01469   0.00849  -0.0421   0.0192   1.0000
   9.750   1.2758   0.01515   0.00898  -0.0416   0.0166   1.0000
  10.000   1.2981   0.01571   0.00953  -0.0409   0.0136   1.0000
  10.250   1.3197   0.01631   0.01013  -0.0402   0.0106   1.0000
  10.500   1.3408   0.01693   0.01077  -0.0394   0.0080   1.0000
  10.750   1.3612   0.01760   0.01145  -0.0385   0.0059   1.0000
  11.000   1.3814   0.01824   0.01213  -0.0376   0.0050   1.0000
  11.250   1.4011   0.01889   0.01283  -0.0367   0.0044   1.0000
  11.500   1.4200   0.01956   0.01356  -0.0356   0.0040   1.0000
  11.750   1.4375   0.02032   0.01438  -0.0344   0.0036   1.0000
  12.000   1.4545   0.02105   0.01517  -0.0332   0.0033   1.0000
  12.250   1.4705   0.02177   0.01597  -0.0318   0.0033   1.0000
  12.500   1.4839   0.02253   0.01680  -0.0300   0.0032   1.0000
  12.750   1.4936   0.02332   0.01766  -0.0277   0.0030   1.0000
  13.000   1.5018   0.02422   0.01864  -0.0254   0.0029   1.0000
  13.250   1.5092   0.02523   0.01974  -0.0233   0.0028   1.0000
  13.500   1.5165   0.02634   0.02094  -0.0214   0.0028   1.0000
  13.750   1.5221   0.02765   0.02233  -0.0196   0.0027   1.0000
  14.000   1.5267   0.02912   0.02389  -0.0181   0.0026   1.0000
  14.250   1.5307   0.03074   0.02561  -0.0167   0.0025   1.0000
  14.500   1.5331   0.03261   0.02757  -0.0156   0.0025   1.0000
  14.750   1.5343   0.03471   0.02977  -0.0147   0.0024   1.0000
  15.000   1.5336   0.03715   0.03233  -0.0140   0.0024   1.0000
  15.250   1.5311   0.03992   0.03521  -0.0138   0.0023   1.0000
  15.500   1.5262   0.04316   0.03857  -0.0139   0.0023   1.0000
  15.750   1.5212   0.04663   0.04216  -0.0144   0.0022   1.0000
  16.000   1.5110   0.05098   0.04666  -0.0156   0.0022   1.0000
  16.250   1.5004   0.05570   0.05151  -0.0172   0.0022   1.0000
  16.500   1.4867   0.06117   0.05713  -0.0194   0.0021   1.0000
  16.750   1.4682   0.06785   0.06397  -0.0226   0.0021   1.0000
  17.000   1.4499   0.07491   0.07119  -0.0263   0.0021   1.0000
  17.250   1.4305   0.08258   0.07901  -0.0304   0.0021   1.0000
  17.500   1.4065   0.09148   0.08807  -0.0353   0.0021   1.0000
  17.750   1.3802   0.10121   0.09797  -0.0408   0.0021   1.0000
  18.000   1.3545   0.11107   0.10798  -0.0464   0.0022   1.0000
  18.250   1.3222   0.12263   0.11971  -0.0531   0.0022   1.0000
<< Back to SD5060 (9.5%) (sd5060-il)

Polar data table (+)

Polar graphs


<< Back to SD5060 (9.5%) (sd5060-il)