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STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: STRAND AIRFOIL (strand-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.13 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-strand-il-1000000-n5.txt
Download as CSV file: xf-strand-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: STRAND AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5336   0.09236   0.08867   0.0268   0.3626   0.0167
  -9.000  -0.5805   0.07220   0.06851   0.0126   0.3629   0.0167
  -8.750  -0.6205   0.05405   0.05015  -0.0131   0.3631   0.0166
  -8.500  -0.6197   0.04681   0.04259  -0.0234   0.3630   0.0166
  -8.250  -0.6084   0.04219   0.03768  -0.0276   0.3628   0.0167
  -8.000  -0.5914   0.03861   0.03385  -0.0301   0.3626   0.0167
  -7.750  -0.5713   0.03556   0.03055  -0.0320   0.3624   0.0167
  -7.500  -0.5490   0.03287   0.02761  -0.0334   0.3621   0.0167
  -7.250  -0.5247   0.03042   0.02489  -0.0344   0.3619   0.0169
  -7.000  -0.4996   0.02830   0.02255  -0.0353   0.3618   0.0169
  -6.750  -0.4735   0.02638   0.02041  -0.0360   0.3617   0.0170
  -6.500  -0.4466   0.02474   0.01856  -0.0365   0.3616   0.0170
  -6.250  -0.4199   0.02275   0.01637  -0.0372   0.3616   0.0171
  -6.000  -0.3921   0.02166   0.01517  -0.0376   0.3615   0.0172
  -5.750  -0.3639   0.02082   0.01424  -0.0379   0.3614   0.0173
  -5.500  -0.3355   0.02010   0.01343  -0.0381   0.3613   0.0174
  -5.250  -0.3069   0.01943   0.01269  -0.0383   0.3612   0.0175
  -5.000  -0.2781   0.01881   0.01200  -0.0385   0.3611   0.0176
  -4.750  -0.2493   0.01824   0.01137  -0.0386   0.3610   0.0178
  -4.500  -0.2203   0.01768   0.01075  -0.0388   0.3610   0.0179
  -4.250  -0.1912   0.01714   0.01015  -0.0389   0.3609   0.0180
  -4.000  -0.1621   0.01660   0.00956  -0.0390   0.3608   0.0182
  -3.750  -0.1328   0.01608   0.00899  -0.0391   0.3607   0.0184
  -3.500  -0.1036   0.01559   0.00846  -0.0392   0.3606   0.0185
  -3.250  -0.0742   0.01512   0.00795  -0.0393   0.3605   0.0187
  -3.000  -0.0449   0.01467   0.00747  -0.0394   0.3604   0.0188
  -2.750  -0.0154   0.01426   0.00703  -0.0396   0.3603   0.0190
  -2.500   0.0141   0.01388   0.00663  -0.0397   0.3602   0.0191
  -2.250   0.0437   0.01352   0.00626  -0.0398   0.3601   0.0192
  -2.000   0.0734   0.01322   0.00594  -0.0400   0.3599   0.0194
  -1.750   0.1032   0.01298   0.00568  -0.0401   0.3597   0.0197
  -1.500   0.1330   0.01276   0.00545  -0.0403   0.3596   0.0199
  -1.250   0.1628   0.01254   0.00522  -0.0405   0.3594   0.0200
  -1.000   0.1927   0.01237   0.00504  -0.0407   0.3593   0.0201
  -0.750   0.2228   0.01210   0.00476  -0.0409   0.3592   0.0204
  -0.500   0.2528   0.01193   0.00459  -0.0412   0.3591   0.0206
  -0.250   0.2828   0.01182   0.00449  -0.0414   0.3590   0.0209
   0.000   0.3127   0.01175   0.00442  -0.0416   0.3589   0.0213
   0.250   0.3425   0.01168   0.00436  -0.0417   0.3588   0.0216
   0.500   0.3724   0.01164   0.00431  -0.0419   0.3587   0.0220
   0.750   0.4023   0.01160   0.00428  -0.0421   0.3585   0.0225
   1.000   0.4321   0.01158   0.00426  -0.0422   0.3584   0.0229
   1.250   0.4619   0.01157   0.00427  -0.0424   0.3583   0.0232
   1.500   0.4917   0.01158   0.00429  -0.0425   0.3582   0.0236
   1.750   0.5215   0.01157   0.00429  -0.0427   0.3581   0.0244
   2.000   0.5512   0.01159   0.00433  -0.0429   0.3580   0.0253
   2.250   0.5809   0.01163   0.00438  -0.0430   0.3579   0.0260
   2.500   0.6105   0.01168   0.00445  -0.0432   0.3578   0.0268
   2.750   0.6401   0.01175   0.00453  -0.0433   0.3576   0.0276
   3.000   0.6697   0.01182   0.00462  -0.0435   0.3575   0.0289
   3.250   0.6991   0.01190   0.00472  -0.0436   0.3574   0.0306
   3.500   0.7286   0.01199   0.00485  -0.0437   0.3573   0.0349
   3.750   0.7601   0.01143   0.00498  -0.0448   0.3572   0.3381
   4.000   0.7899   0.01133   0.00517  -0.0453   0.3571   0.4390
   4.250   0.8195   0.01137   0.00537  -0.0455   0.3570   0.4899
   4.500   0.8489   0.01142   0.00557  -0.0458   0.3569   0.5412
   4.750   0.8783   0.01148   0.00578  -0.0460   0.3568   0.5896
   5.000   0.9076   0.01149   0.00597  -0.0463   0.3566   0.6428
   5.250   0.9368   0.01142   0.00614  -0.0464   0.3562   0.7244
   5.500   0.9659   0.01141   0.00626  -0.0465   0.3557   0.7665
   5.750   0.9945   0.01140   0.00637  -0.0465   0.3553   0.8074
   6.000   1.0206   0.01130   0.00651  -0.0459   0.3550   0.8839
   6.250   1.0465   0.01125   0.00660  -0.0453   0.3547   1.0000
   6.500   1.0757   0.01139   0.00675  -0.0454   0.3544   1.0000
   6.750   1.1048   0.01156   0.00694  -0.0456   0.3542   1.0000
   7.000   1.1338   0.01174   0.00715  -0.0458   0.3540   1.0000
   7.250   1.1628   0.01189   0.00732  -0.0460   0.3538   1.0000
   7.500   1.1919   0.01200   0.00744  -0.0461   0.3534   1.0000
   7.750   1.2209   0.01209   0.00755  -0.0463   0.3530   1.0000
   8.000   1.2500   0.01216   0.00764  -0.0464   0.3526   1.0000
   8.250   1.2794   0.01207   0.00754  -0.0466   0.3518   1.0000
   8.500   1.3089   0.01191   0.00735  -0.0467   0.3504   1.0000
   8.750   1.3382   0.01177   0.00727  -0.0468   0.3488   1.0000
   9.000   1.3676   0.01165   0.00721  -0.0470   0.3471   1.0000
   9.250   1.3974   0.01138   0.00699  -0.0472   0.3443   1.0000
   9.500   1.4281   0.01083   0.00641  -0.0473   0.3403   1.0000
   9.750   1.4576   0.01070   0.00634  -0.0475   0.3354   1.0000
  10.000   1.4870   0.01061   0.00630  -0.0477   0.3290   1.0000
  10.250   1.5169   0.01031   0.00581  -0.0480   0.2927   1.0000
  10.500   1.5397   0.01190   0.00716  -0.0486   0.2501   1.0000
  10.750   1.5634   0.01320   0.00837  -0.0491   0.2240   1.0000
  11.000   1.5856   0.01475   0.00981  -0.0498   0.1944   1.0000
  11.250   1.6060   0.01665   0.01159  -0.0506   0.1655   1.0000
  11.500   1.6248   0.01875   0.01361  -0.0518   0.1418   1.0000
  11.750   1.6420   0.02117   0.01600  -0.0533   0.1223   1.0000
  12.000   1.6503   0.02633   0.02123  -0.0573   0.1062   1.0000
  12.250   1.5762   0.04543   0.04090  -0.0747   0.1186   1.0000
  12.500   1.5406   0.05206   0.04761  -0.0766   0.1179   1.0000
  12.750   1.5174   0.05731   0.05289  -0.0778   0.1141   1.0000
  13.000   1.5037   0.06168   0.05726  -0.0786   0.1075   1.0000
  13.250   1.4957   0.06545   0.06100  -0.0792   0.1003   1.0000
  13.500   1.4880   0.06922   0.06472  -0.0798   0.0920   1.0000
  13.750   1.4815   0.07295   0.06843  -0.0804   0.0840   1.0000
  14.000   1.4766   0.07648   0.07193  -0.0810   0.0765   1.0000
  14.250   1.4733   0.07985   0.07525  -0.0814   0.0690   1.0000
  14.750   1.4719   0.08600   0.08134  -0.0823   0.0568   1.0000
  15.000   1.4701   0.08930   0.08463  -0.0828   0.0524   1.0000
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