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STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: STRAND AIRFOIL (strand-il)
Reynolds number: 200,000
Max Cl/Cd: 26.52 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-strand-il-200000-n5.txt
Download as CSV file: xf-strand-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4720   0.12440   0.11887   0.0369   0.4011   0.0403
  -9.750  -0.4682   0.12045   0.11493   0.0347   0.4010   0.0412
  -9.250  -0.4898   0.10495   0.09949   0.0201   0.4010   0.0432
  -9.000  -0.4773   0.10321   0.09776   0.0217   0.4008   0.0436
  -8.750  -0.4675   0.10087   0.09543   0.0217   0.4006   0.0439
  -8.500  -0.4592   0.09813   0.09270   0.0210   0.4004   0.0444
  -8.250  -0.4529   0.09490   0.08948   0.0194   0.4003   0.0450
  -8.000  -0.4483   0.09111   0.08572   0.0170   0.4002   0.0457
  -7.750  -0.4457   0.08654   0.08117   0.0135   0.4000   0.0467
  -7.500  -0.5014   0.06342   0.05731  -0.0253   0.4005   0.0499
  -7.250  -0.4875   0.05845   0.05238  -0.0269   0.4003   0.0507
  -7.000  -0.4684   0.05581   0.04980  -0.0273   0.4000   0.0514
  -6.750  -0.4492   0.05346   0.04745  -0.0284   0.3998   0.0524
  -6.500  -0.4340   0.04964   0.04286  -0.0344   0.3996   0.0588
  -6.250  -0.4119   0.04688   0.04028  -0.0347   0.3993   0.0601
  -6.000  -0.3887   0.04494   0.03834  -0.0355   0.3989   0.0619
  -5.500  -0.3311   0.03660   0.02856  -0.0383   0.3981   0.0361
  -5.250  -0.3043   0.03463   0.02640  -0.0390   0.3977   0.0350
  -4.750  -0.2454   0.03221   0.02303  -0.0398   0.3972   0.0320
  -4.500  -0.2175   0.03085   0.02160  -0.0401   0.3969   0.0319
  -4.250  -0.1891   0.02975   0.02038  -0.0404   0.3967   0.0317
  -4.000  -0.1605   0.02880   0.01933  -0.0407   0.3964   0.0316
  -3.750  -0.1317   0.02800   0.01841  -0.0409   0.3962   0.0316
  -3.500  -0.1023   0.02761   0.01781  -0.0411   0.3960   0.0320
  -3.250  -0.0737   0.02673   0.01689  -0.0414   0.3957   0.0326
  -3.000  -0.0453   0.02599   0.01620  -0.0416   0.3955   0.0329
  -2.750  -0.0163   0.02550   0.01567  -0.0417   0.3953   0.0330
  -2.500   0.0127   0.02511   0.01523  -0.0418   0.3950   0.0328
  -2.250   0.0416   0.02474   0.01486  -0.0419   0.3948   0.0328
  -2.000   0.0704   0.02441   0.01455  -0.0421   0.3946   0.0328
  -1.750   0.0993   0.02411   0.01429  -0.0423   0.3944   0.0329
  -1.500   0.1281   0.02387   0.01410  -0.0425   0.3942   0.0331
  -1.250   0.1571   0.02368   0.01396  -0.0428   0.3940   0.0333
  -1.000   0.1862   0.02355   0.01389  -0.0431   0.3938   0.0336
  -0.750   0.2155   0.02347   0.01387  -0.0435   0.3936   0.0339
  -0.500   0.2448   0.02346   0.01389  -0.0440   0.3934   0.0344
  -0.250   0.2742   0.02347   0.01390  -0.0444   0.3930   0.0350
   0.000   0.3036   0.02354   0.01396  -0.0448   0.3926   0.0363
   0.250   0.3329   0.02368   0.01408  -0.0451   0.3923   0.0374
   0.500   0.3623   0.02382   0.01420  -0.0456   0.3921   0.0383
   0.750   0.3915   0.02406   0.01443  -0.0460   0.3918   0.0390
   1.000   0.4206   0.02435   0.01471  -0.0463   0.3916   0.0400
   1.250   0.4495   0.02469   0.01505  -0.0467   0.3914   0.0412
   1.500   0.4783   0.02508   0.01543  -0.0470   0.3912   0.0427
   1.750   0.5070   0.02547   0.01585  -0.0474   0.3909   0.0455
   2.000   0.5357   0.02587   0.01631  -0.0478   0.3907   0.0575
   2.250   0.5655   0.02540   0.01691  -0.0494   0.3905   0.3827
   2.500   0.5936   0.02580   0.01759  -0.0498   0.3902   0.4644
   2.750   0.6211   0.02625   0.01830  -0.0501   0.3900   0.5308
   3.000   0.6477   0.02662   0.01894  -0.0501   0.3896   0.6063
   3.250   0.6737   0.02705   0.01960  -0.0499   0.3891   0.6698
   3.500   0.6967   0.02814   0.02114  -0.0503   0.3882   0.7525
   3.750   0.7121   0.02935   0.02288  -0.0493   0.3870   0.8913
   4.000   0.7379   0.03145   0.02522  -0.0519   0.3836   1.0000
   4.250   0.7643   0.03248   0.02626  -0.0529   0.3814   1.0000
   4.500   0.7907   0.03339   0.02717  -0.0537   0.3800   1.0000
   4.750   0.8171   0.03412   0.02789  -0.0541   0.3790   1.0000
   5.000   0.8438   0.03464   0.02839  -0.0543   0.3781   1.0000
   5.250   0.8705   0.03509   0.02881  -0.0543   0.3773   1.0000
   5.500   0.8970   0.03561   0.02931  -0.0544   0.3767   1.0000
   5.750   0.9234   0.03613   0.02982  -0.0544   0.3762   1.0000
   6.000   0.9501   0.03652   0.03018  -0.0543   0.3758   1.0000
   6.250   0.9769   0.03683   0.03048  -0.0540   0.3753   1.0000
   7.250   1.0231   0.05222   0.04652  -0.0707   0.3522   1.0000
   7.500   1.0464   0.05271   0.04702  -0.0705   0.3513   1.0000
   7.750   1.0707   0.05297   0.04729  -0.0699   0.3507   1.0000
   8.000   1.0958   0.05303   0.04737  -0.0692   0.3502   1.0000
   9.000   1.0771   0.06823   0.06275  -0.0798   0.3201   1.0000
   9.500   1.1209   0.06873   0.06330  -0.0788   0.3176   1.0000
  10.000   1.1315   0.07317   0.06782  -0.0799   0.3073   1.0000
  10.500   1.1444   0.07741   0.07213  -0.0808   0.2972   1.0000
  11.000   1.1617   0.08112   0.07594  -0.0812   0.2879   1.0000
  11.250   1.1814   0.08149   0.07635  -0.0809   0.2857   1.0000
  11.500   1.2038   0.08148   0.07638  -0.0804   0.2842   1.0000
  11.750   1.2275   0.08128   0.07624  -0.0798   0.2830   1.0000
  12.000   1.2210   0.08528   0.08029  -0.0808   0.2743   1.0000
  12.250   1.2440   0.08514   0.08020  -0.0803   0.2722   1.0000
  12.500   1.2744   0.08394   0.07904  -0.0795   0.2703   1.0000
  12.750   1.2735   0.08716   0.08230  -0.0802   0.2615   1.0000
  13.000   1.3025   0.08615   0.08131  -0.0794   0.2580   1.0000
  13.250   1.3268   0.08580   0.08098  -0.0789   0.2530   1.0000
  13.500   1.3385   0.08722   0.08243  -0.0789   0.2444   1.0000
  13.750   1.3584   0.08746   0.08266  -0.0785   0.2363   1.0000
  14.000   1.3808   0.08728   0.08244  -0.0780   0.2269   1.0000
  14.250   1.3872   0.08945   0.08461  -0.0782   0.2163   1.0000
  14.500   1.4001   0.09058   0.08570  -0.0781   0.2052   1.0000
  14.750   1.4101   0.09211   0.08715  -0.0781   0.1930   1.0000
  15.000   1.4162   0.09420   0.08915  -0.0782   0.1805   1.0000
  15.250   1.4184   0.09686   0.09172  -0.0786   0.1683   1.0000
  15.500   1.4173   0.10007   0.09487  -0.0792   0.1567   1.0000
  15.750   1.4154   0.10345   0.09821  -0.0799   0.1456   1.0000
  16.000   1.4136   0.10685   0.10156  -0.0806   0.1352   1.0000
  16.250   1.4107   0.11047   0.10513  -0.0815   0.1253   1.0000
  16.500   1.4061   0.11438   0.10899  -0.0825   0.1159   1.0000
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