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SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7062 (14%) (sd7062-il)
Reynolds number: 50,000
Max Cl/Cd: 12.09 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7062-il-50000.txt
Download as CSV file: xf-sd7062-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7062 (14%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2564   0.11919   0.11235  -0.0305   1.0000   0.2289
  -9.500  -0.2373   0.11508   0.10827  -0.0295   1.0000   0.2361
  -9.250  -0.2607   0.11580   0.10916  -0.0303   1.0000   0.2439
  -9.000  -0.2381   0.11046   0.10386  -0.0291   1.0000   0.2490
  -8.750  -0.2381   0.10865   0.10215  -0.0282   1.0000   0.2585
  -8.500  -0.2513   0.10731   0.10098  -0.0276   1.0000   0.2638
  -8.250  -0.2367   0.10411   0.09785  -0.0257   1.0000   0.2741
  -8.000  -0.2791   0.10619   0.10018  -0.0234   1.0000   0.2792
  -7.750  -0.2480   0.10088   0.09488  -0.0212   1.0000   0.2887
  -7.500  -0.2800   0.10191   0.09611  -0.0175   1.0000   0.2955
  -7.250  -0.2907   0.10031   0.09464  -0.0143   1.0000   0.3002
  -7.000  -0.2915   0.09874   0.09315  -0.0110   1.0000   0.3089
  -6.750  -0.3383   0.10069   0.09531  -0.0065   1.0000   0.3141
  -6.500  -0.3241   0.09711   0.09177  -0.0044   1.0000   0.3213
  -6.250  -0.3511   0.09742   0.09222  -0.0005   1.0000   0.3301
  -6.000  -0.3832   0.09727   0.09223   0.0033   1.0000   0.3347
  -5.750  -0.3703   0.09451   0.08950   0.0053   1.0000   0.3440
  -5.500  -0.4210   0.09556   0.09074   0.0093   1.0000   0.3519
  -5.250  -0.4031   0.09234   0.08753   0.0118   1.0000   0.3597
  -5.000  -0.4320   0.09168   0.08700   0.0142   1.0000   0.3711
  -4.750  -0.4509   0.06286   0.05685  -0.0352   0.9989   0.1589
  -4.500  -0.4097   0.05494   0.04829  -0.0438   0.9909   0.1419
  -4.250  -0.3675   0.05017   0.04311  -0.0497   0.9817   0.1363
  -4.000  -0.3236   0.04540   0.03748  -0.0556   0.9723   0.1319
  -3.750  -0.2845   0.04298   0.03461  -0.0592   0.9620   0.1345
  -3.500  -0.2423   0.04097   0.03205  -0.0627   0.9516   0.1396
  -3.250  -0.1965   0.03904   0.02959  -0.0663   0.9415   0.1452
  -3.000  -0.1637   0.03798   0.02842  -0.0677   0.9299   0.1555
  -2.750  -0.1247   0.03698   0.02728  -0.0698   0.9191   0.1735
  -2.500  -0.0833   0.03598   0.02632  -0.0721   0.9086   0.2097
  -2.250  -0.0563   0.03508   0.02592  -0.0723   0.8969   0.2715
  -2.000  -0.0202   0.03413   0.02596  -0.0731   0.8870   0.4345
  -1.750  -0.0015   0.03401   0.02652  -0.0702   0.8752   0.5731
  -1.500   0.0116   0.03422   0.02708  -0.0660   0.8638   0.6723
  -1.250   0.0313   0.03434   0.02745  -0.0617   0.8540   0.7719
  -1.000   0.0323   0.03438   0.02768  -0.0556   0.8419   0.8520
  -0.750   0.1248   0.03455   0.02753  -0.0674   0.8282   1.0000
  -0.500   0.1732   0.03488   0.02736  -0.0729   0.8169   1.0000
  -0.250   0.1930   0.03557   0.02773  -0.0734   0.8031   1.0000
   0.000   0.2168   0.03638   0.02826  -0.0742   0.7904   1.0000
   0.250   0.2584   0.03697   0.02854  -0.0767   0.7791   1.0000
   0.500   0.2842   0.03776   0.02911  -0.0772   0.7667   1.0000
   0.750   0.3027   0.03875   0.02991  -0.0768   0.7537   1.0000
   1.000   0.3383   0.03941   0.03036  -0.0781   0.7425   1.0000
   1.250   0.3672   0.04016   0.03095  -0.0787   0.7307   1.0000
   1.500   0.3802   0.04140   0.03206  -0.0776   0.7177   1.0000
   1.750   0.4131   0.04212   0.03263  -0.0784   0.7070   1.0000
   2.000   0.4416   0.04287   0.03326  -0.0787   0.6954   1.0000
   2.250   0.4501   0.04441   0.03470  -0.0773   0.6825   1.0000
   2.500   0.4823   0.04513   0.03532  -0.0778   0.6722   1.0000
   2.750   0.5075   0.04601   0.03611  -0.0777   0.6606   1.0000
   3.000   0.5116   0.04793   0.03797  -0.0762   0.6481   1.0000
   3.250   0.5515   0.04826   0.03821  -0.0770   0.6387   1.0000
   3.500   0.5621   0.04989   0.03979  -0.0759   0.6264   1.0000
   3.750   0.5652   0.05211   0.04197  -0.0747   0.6146   1.0000
   4.000   0.6211   0.05137   0.04117  -0.0758   0.6063   1.0000
   4.250   0.6040   0.05483   0.04461  -0.0738   0.5932   1.0000
   4.500   0.6134   0.05689   0.04663  -0.0731   0.5826   1.0000
   4.750   0.6515   0.05711   0.04683  -0.0732   0.5731   1.0000
   5.000   0.6365   0.06083   0.05053  -0.0719   0.5616   1.0000
   5.250   0.6769   0.06097   0.05065  -0.0719   0.5529   1.0000
   5.500   0.6644   0.06468   0.05436  -0.0710   0.5419   1.0000
   5.750   0.6744   0.06699   0.05666  -0.0706   0.5325   1.0000
   6.000   0.6905   0.06886   0.05854  -0.0703   0.5232   1.0000
   6.250   0.6861   0.07234   0.06202  -0.0699   0.5143   1.0000
   6.500   0.7113   0.07363   0.06332  -0.0696   0.5053   1.0000
   6.750   0.6995   0.07792   0.06761  -0.0696   0.4979   1.0000
   7.000   0.7150   0.08004   0.06975  -0.0694   0.4892   1.0000
   7.250   0.7148   0.08361   0.07333  -0.0695   0.4822   1.0000
   7.500   0.7044   0.08806   0.07781  -0.0700   0.4775   1.0000
   7.750   0.7364   0.08910   0.07888  -0.0695   0.4673   1.0000
   8.000   0.7193   0.09437   0.08418  -0.0705   0.4652   1.0000
   8.250   0.7127   0.09904   0.08890  -0.0716   0.4647   1.0000
   8.500   0.7115   0.10354   0.09344  -0.0727   0.4658   1.0000
   8.750   0.7260   0.10790   0.09786  -0.0742   0.4696   1.0000
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