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STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: STRAND AIRFOIL (strand-il)
Reynolds number: 500,000
Max Cl/Cd: 92.4 at α=13°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-strand-il-500000.txt
Download as CSV file: xf-strand-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4729   0.10358   0.09949   0.0282   0.4013   0.0287
  -8.750  -0.4689   0.09979   0.09572   0.0262   0.4012   0.0290
  -8.500  -0.4658   0.09571   0.09166   0.0237   0.4012   0.0293
  -8.250  -0.4082   0.06978   0.06588  -0.0001   0.4018   0.0319
  -8.000  -0.4349   0.05989   0.05593  -0.0091   0.4019   0.0319
  -7.750  -0.4523   0.05335   0.04932  -0.0164   0.4019   0.0317
  -7.500  -0.4727   0.04518   0.04059  -0.0282   0.4019   0.0320
  -7.250  -0.4667   0.04050   0.03541  -0.0320   0.4019   0.0321
  -7.000  -0.4530   0.03482   0.02967  -0.0335   0.4019   0.0325
  -6.750  -0.4335   0.03184   0.02673  -0.0340   0.4018   0.0328
  -6.500  -0.4127   0.02940   0.02427  -0.0348   0.4017   0.0330
  -6.250  -0.3908   0.02712   0.02192  -0.0356   0.4016   0.0334
  -6.000  -0.3680   0.02499   0.01968  -0.0365   0.4016   0.0339
  -5.750  -0.3442   0.02302   0.01757  -0.0373   0.4016   0.0346
  -5.500  -0.3188   0.02130   0.01564  -0.0381   0.4015   0.0357
  -5.250  -0.2915   0.01930   0.01301  -0.0391   0.4015   0.0377
  -5.000  -0.2669   0.01758   0.01137  -0.0396   0.4015   0.0383
  -4.750  -0.2410   0.01639   0.01018  -0.0400   0.4015   0.0391
  -4.500  -0.2140   0.01542   0.00913  -0.0404   0.4015   0.0402
  -4.250  -0.1834   0.01600   0.00932  -0.0403   0.4017   0.0430
  -4.000  -0.1586   0.01349   0.00684  -0.0413   0.4017   0.0446
  -3.750  -0.1314   0.01278   0.00613  -0.0416   0.4017   0.0461
  -3.500  -0.1025   0.01234   0.00542  -0.0420   0.4018   0.0511
  -3.250  -0.0757   0.01155   0.00476  -0.0424   0.4019   0.0529
  -3.000  -0.0474   0.01116   0.00422  -0.0429   0.4019   0.0598
  -2.750  -0.0200   0.01059   0.00379  -0.0432   0.4017   0.0632
  -1.250   0.1666   0.02897   0.02255  -0.0531   0.4404   0.0570
  -1.000   0.1954   0.02894   0.02248  -0.0529   0.4399   0.0479
  -0.750   0.2240   0.02926   0.02270  -0.0528   0.4394   0.0440
  -0.500   0.2520   0.02954   0.02301  -0.0530   0.4389   0.0423
  -0.250   0.2801   0.02974   0.02322  -0.0532   0.4385   0.0406
   0.000   0.3079   0.03026   0.02370  -0.0534   0.4380   0.0392
   0.250   0.3347   0.03122   0.02460  -0.0534   0.4374   0.0385
   0.500   0.3693   0.03160   0.02531  -0.0580   0.4259   0.0383
   0.750   0.3973   0.03178   0.02548  -0.0581   0.4249   0.0385
   1.000   0.4251   0.03197   0.02564  -0.0580   0.4241   0.0389
   1.250   0.4528   0.03227   0.02592  -0.0580   0.4235   0.0395
   1.500   0.4802   0.03271   0.02634  -0.0581   0.4231   0.0402
   1.750   0.5074   0.03322   0.02682  -0.0580   0.4226   0.0419
   2.000   0.5342   0.03380   0.02736  -0.0579   0.4221   0.0431
   2.250   0.5608   0.03446   0.02797  -0.0576   0.4217   0.0447
   2.500   0.5867   0.03543   0.02889  -0.0573   0.4212   0.0476
   2.750   0.6166   0.03697   0.03114  -0.0640   0.4084   0.2143
   3.000   0.6445   0.03687   0.03166  -0.0645   0.4077   0.4184
   3.250   0.6712   0.03697   0.03210  -0.0643   0.4072   0.5364
   3.500   0.6977   0.03707   0.03241  -0.0637   0.4067   0.6110
   3.750   0.7235   0.03711   0.03272  -0.0628   0.4063   0.7008
   4.000   0.7474   0.03720   0.03306  -0.0614   0.4058   0.7958
   4.250   0.7646   0.03723   0.03338  -0.0584   0.4054   1.0000
   4.500   0.7941   0.03627   0.03249  -0.0600   0.3920   1.0000
   4.750   0.8259   0.03410   0.03015  -0.0569   0.3913   1.0000
   5.000   0.8563   0.03289   0.02879  -0.0550   0.3907   1.0000
   5.250   0.8856   0.03238   0.02816  -0.0538   0.3902   1.0000
   5.500   0.8987   0.03809   0.03429  -0.0613   0.3787   1.0000
   5.750   0.9268   0.03773   0.03389  -0.0603   0.3782   1.0000
   6.000   0.9550   0.03734   0.03345  -0.0593   0.3777   1.0000
   6.250   0.9834   0.03697   0.03304  -0.0584   0.3773   1.0000
   6.500   1.0117   0.03664   0.03268  -0.0576   0.3769   1.0000
   6.750   1.0399   0.03645   0.03245  -0.0568   0.3765   1.0000
   7.000   1.0679   0.03634   0.03232  -0.0562   0.3762   1.0000
   7.250   1.0960   0.03626   0.03221  -0.0556   0.3759   1.0000
   7.500   1.1239   0.03629   0.03221  -0.0550   0.3756   1.0000
   7.750   1.1112   0.04606   0.04247  -0.0673   0.3548   1.0000
   8.000   1.1385   0.04568   0.04210  -0.0663   0.3540   1.0000
   8.250   1.1670   0.04500   0.04141  -0.0651   0.3536   1.0000
   8.500   1.1957   0.04427   0.04069  -0.0638   0.3532   1.0000
   8.750   1.2244   0.04358   0.04001  -0.0627   0.3529   1.0000
   9.000   1.2538   0.04274   0.03917  -0.0615   0.3527   1.0000
   9.250   1.2844   0.04169   0.03813  -0.0602   0.3526   1.0000
   9.500   1.3160   0.04047   0.03691  -0.0588   0.3525   1.0000
   9.750   1.3478   0.03928   0.03571  -0.0576   0.3524   1.0000
  10.000   1.3816   0.03771   0.03414  -0.0562   0.3524   1.0000
  10.250   1.4228   0.03467   0.03101  -0.0541   0.3527   1.0000
  10.500   1.4682   0.03072   0.02692  -0.0518   0.3528   1.0000
  10.750   1.5078   0.02799   0.02406  -0.0506   0.3523   1.0000
  11.000   1.5430   0.02626   0.02226  -0.0499   0.3516   1.0000
  11.250   1.5782   0.02456   0.02047  -0.0493   0.3508   1.0000
  11.500   1.6010   0.02520   0.02134  -0.0498   0.3463   1.0000
  11.750   1.6319   0.02428   0.02047  -0.0497   0.3430   1.0000
  12.000   1.6676   0.02244   0.01859  -0.0493   0.3409   1.0000
  12.250   1.6980   0.02170   0.01794  -0.0493   0.3363   1.0000
  12.500   1.6501   0.03726   0.03438  -0.0596   0.3056   1.0000
  12.750   1.7609   0.02020   0.01661  -0.0498   0.3005   1.0000
  13.000   1.7889   0.01936   0.01504  -0.0502   0.2503   1.0000
  13.250   1.7921   0.02374   0.01941  -0.0527   0.2187   1.0000
  13.500   1.7241   0.04194   0.03811  -0.0686   0.2173   1.0000
  13.750   1.6660   0.05117   0.04742  -0.0716   0.2160   1.0000
  14.000   1.6240   0.05837   0.05461  -0.0734   0.2092   1.0000
  14.250   1.5955   0.06427   0.06045  -0.0746   0.1978   1.0000
  14.500   1.5736   0.06969   0.06580  -0.0758   0.1854   1.0000
  14.750   1.5579   0.07446   0.07049  -0.0767   0.1728   1.0000
  15.000   1.5447   0.07901   0.07497  -0.0776   0.1609   1.0000
  15.250   1.5326   0.08350   0.07939  -0.0785   0.1496   1.0000
  15.500   1.5229   0.08773   0.08355  -0.0793   0.1382   1.0000
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