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NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il)
Reynolds number: 50,000
Max Cl/Cd: 23.25 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20612-il-50000-n5.txt
Download as CSV file: xf-sc20612-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0612 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6129   0.09741   0.08891  -0.0415   1.0000   0.0755
 -11.500  -0.6443   0.08701   0.07850  -0.0480   1.0000   0.0748
 -11.250  -0.6821   0.07821   0.06965  -0.0530   1.0000   0.0740
 -11.000  -0.7174   0.07190   0.06324  -0.0550   1.0000   0.0735
 -10.750  -0.7489   0.06741   0.05867  -0.0545   1.0000   0.0732
 -10.500  -0.7702   0.06323   0.05431  -0.0545   1.0000   0.0734
 -10.250  -0.7828   0.05940   0.05024  -0.0541   1.0000   0.0740
 -10.000  -0.7887   0.05573   0.04625  -0.0535   1.0000   0.0749
  -9.750  -0.7889   0.05218   0.04233  -0.0530   1.0000   0.0760
  -9.500  -0.7850   0.04877   0.03843  -0.0526   1.0000   0.0779
  -9.250  -0.7731   0.04631   0.03578  -0.0520   1.0000   0.0802
  -9.000  -0.7577   0.04451   0.03391  -0.0513   1.0000   0.0829
  -8.750  -0.7418   0.04241   0.03158  -0.0507   1.0000   0.0858
  -8.500  -0.7245   0.04019   0.02896  -0.0502   1.0000   0.0890
  -8.250  -0.7060   0.03839   0.02700  -0.0495   1.0000   0.0927
  -8.000  -0.6867   0.03702   0.02560  -0.0486   1.0000   0.0968
  -7.750  -0.6664   0.03556   0.02389  -0.0478   1.0000   0.1017
  -7.500  -0.6463   0.03426   0.02253  -0.0467   1.0000   0.1066
  -7.250  -0.6261   0.03320   0.02145  -0.0455   1.0000   0.1121
  -7.000  -0.6051   0.03218   0.02025  -0.0443   1.0000   0.1187
  -6.750  -0.5856   0.03129   0.01948  -0.0427   1.0000   0.1249
  -6.500  -0.5649   0.03051   0.01853  -0.0412   1.0000   0.1329
  -6.250  -0.5456   0.02968   0.01785  -0.0398   1.0000   0.1407
  -6.000  -0.5255   0.02892   0.01706  -0.0385   1.0000   0.1503
  -5.750  -0.5051   0.02811   0.01631  -0.0375   1.0000   0.1625
  -5.500  -0.4841   0.02722   0.01553  -0.0369   1.0000   0.1771
  -5.250  -0.4616   0.02622   0.01473  -0.0369   1.0000   0.1990
  -5.000  -0.4365   0.02497   0.01386  -0.0379   1.0000   0.2387
  -4.750  -0.4097   0.02341   0.01308  -0.0397   1.0000   0.3357
  -4.500  -0.4020   0.02361   0.01437  -0.0338   1.0000   0.4607
  -4.250  -0.3899   0.02456   0.01554  -0.0287   1.0000   0.5487
  -3.750  -0.3431   0.02577   0.01640  -0.0264   1.0000   0.6398
  -3.500  -0.3275   0.02650   0.01706  -0.0228   1.0000   0.6632
  -3.250  -0.3083   0.02711   0.01756  -0.0205   1.0000   0.6892
  -3.000  -0.2971   0.02779   0.01822  -0.0158   1.0000   0.7099
  -2.750  -0.2865   0.02834   0.01874  -0.0110   1.0000   0.7306
  -2.500  -0.2743   0.02869   0.01906  -0.0069   1.0000   0.7502
  -2.250  -0.2586   0.02882   0.01913  -0.0041   1.0000   0.7670
  -2.000  -0.2370   0.02880   0.01903  -0.0033   1.0000   0.7805
  -1.750  -0.2203   0.02865   0.01883  -0.0011   1.0000   0.7891
  -1.500  -0.1971   0.02855   0.01866  -0.0010   1.0000   0.7989
  -1.250  -0.1781   0.02841   0.01848   0.0004   1.0000   0.8075
  -1.000  -0.1534   0.02833   0.01836   0.0000   1.0000   0.8152
  -0.750  -0.1320   0.02819   0.01820   0.0005   1.0000   0.8208
  -0.500  -0.1061   0.02817   0.01815  -0.0002   1.0000   0.8265
  -0.250  -0.0805   0.02817   0.01814  -0.0009   1.0000   0.8317
   0.000  -0.0515   0.02819   0.01817  -0.0021   0.9968   0.8363
   0.250  -0.0126   0.02836   0.01834  -0.0053   0.9902   0.8402
   0.500   0.0294   0.02860   0.01860  -0.0092   0.9832   0.8438
   0.750   0.0678   0.02875   0.01880  -0.0122   0.9745   0.8472
   1.000   0.1062   0.02885   0.01897  -0.0149   0.9648   0.8508
   1.250   0.1490   0.02900   0.01920  -0.0184   0.9548   0.8545
   1.500   0.1911   0.02908   0.01939  -0.0218   0.9424   0.8579
   1.750   0.2338   0.02912   0.01956  -0.0252   0.9285   0.8608
   2.000   0.2807   0.02883   0.01943  -0.0285   0.9108   0.8631
   2.250   0.3218   0.02820   0.01896  -0.0301   0.8844   0.8657
   2.500   0.3688   0.02718   0.01813  -0.0318   0.8531   0.8685
   2.750   0.4129   0.02602   0.01714  -0.0327   0.8180   0.8714
   3.000   0.4455   0.02518   0.01647  -0.0320   0.7753   0.8748
   3.250   0.4765   0.02436   0.01578  -0.0308   0.7144   0.8780
   3.500   0.5307   0.02333   0.01404  -0.0315   0.5239   0.8801
   3.750   0.5480   0.02457   0.01413  -0.0292   0.3543   0.8833
   4.000   0.5648   0.02589   0.01480  -0.0280   0.2624   0.8868
   4.250   0.5869   0.02705   0.01559  -0.0277   0.2141   0.8902
   4.500   0.6096   0.02798   0.01633  -0.0272   0.1876   0.8936
   4.750   0.6347   0.02881   0.01710  -0.0270   0.1681   0.8973
   5.000   0.6626   0.02972   0.01795  -0.0274   0.1538   0.9009
   5.250   0.6935   0.03070   0.01889  -0.0282   0.1416   0.9043
   5.500   0.7243   0.03159   0.01990  -0.0288   0.1312   0.9076
   5.750   0.7542   0.03265   0.02092  -0.0292   0.1230   0.9114
   6.000   0.7841   0.03373   0.02216  -0.0298   0.1148   0.9156
   6.250   0.8142   0.03508   0.02352  -0.0305   0.1083   0.9196
   6.500   0.8410   0.03632   0.02500  -0.0304   0.1018   0.9239
   6.750   0.8678   0.03771   0.02632  -0.0308   0.0969   0.9284
   7.250   0.9171   0.04116   0.03045  -0.0305   0.0879   0.9383
   7.500   0.9409   0.04276   0.03207  -0.0306   0.0844   0.9440
   7.750   0.9596   0.04511   0.03492  -0.0297   0.0810   0.9499
   8.000   0.9768   0.04775   0.03803  -0.0289   0.0785   0.9564
   8.250   0.9933   0.05024   0.04086  -0.0283   0.0761   0.9639
   8.500   1.0116   0.05237   0.04314  -0.0281   0.0738   0.9755
   8.750   1.0250   0.05527   0.04632  -0.0277   0.0717   1.0000
   9.000   1.0252   0.05942   0.05111  -0.0262   0.0702   1.0000
   9.250   1.0220   0.06374   0.05593  -0.0249   0.0694   1.0000
   9.500   1.0131   0.06826   0.06086  -0.0235   0.0689   1.0000
   9.750   0.9965   0.07282   0.06578  -0.0220   0.0686   1.0000
  10.000   0.9741   0.07796   0.07122  -0.0215   0.0686   1.0000
  10.250   0.9461   0.08424   0.07775  -0.0228   0.0688   1.0000
  10.500   0.9132   0.09236   0.08609  -0.0269   0.0693   1.0000
  10.750   0.8806   0.10276   0.09663  -0.0343   0.0700   1.0000
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