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NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il)
Reynolds number: 200,000
Max Cl/Cd: 35.07 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20412-il-200000.txt
Download as CSV file: xf-sc20412-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0412 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7652   0.08736   0.08303  -0.0383   1.0000   0.0524
 -12.250  -0.7841   0.08016   0.07577  -0.0422   1.0000   0.0518
 -12.000  -0.8113   0.07273   0.06823  -0.0462   1.0000   0.0512
 -11.750  -0.8435   0.06577   0.06110  -0.0493   1.0000   0.0504
 -11.500  -0.8756   0.05980   0.05491  -0.0507   1.0000   0.0498
 -11.250  -0.9040   0.05501   0.04988  -0.0503   1.0000   0.0494
 -11.000  -0.9243   0.05067   0.04524  -0.0497   1.0000   0.0493
 -10.750  -0.9332   0.04664   0.04088  -0.0489   1.0000   0.0494
 -10.500  -0.9347   0.04297   0.03686  -0.0479   1.0000   0.0497
 -10.250  -0.9301   0.03973   0.03324  -0.0469   1.0000   0.0503
 -10.000  -0.9208   0.03688   0.03002  -0.0459   1.0000   0.0511
  -9.750  -0.9080   0.03446   0.02720  -0.0450   1.0000   0.0521
  -9.500  -0.8925   0.03215   0.02455  -0.0443   1.0000   0.0534
  -9.250  -0.8728   0.03066   0.02312  -0.0437   1.0000   0.0550
  -9.000  -0.8524   0.02963   0.02205  -0.0430   1.0000   0.0568
  -8.750  -0.8321   0.02835   0.02060  -0.0423   1.0000   0.0588
  -8.500  -0.8111   0.02710   0.01910  -0.0416   1.0000   0.0606
  -8.250  -0.7908   0.02545   0.01736  -0.0407   1.0000   0.0626
  -8.000  -0.7694   0.02459   0.01656  -0.0400   1.0000   0.0650
  -7.750  -0.7476   0.02380   0.01571  -0.0393   1.0000   0.0677
  -7.500  -0.7253   0.02303   0.01479  -0.0385   1.0000   0.0703
  -7.250  -0.7046   0.02182   0.01361  -0.0375   1.0000   0.0731
  -7.000  -0.6826   0.02117   0.01301  -0.0368   1.0000   0.0764
  -6.750  -0.6601   0.02056   0.01235  -0.0361   1.0000   0.0798
  -6.500  -0.6381   0.01972   0.01148  -0.0352   1.0000   0.0833
  -6.250  -0.6159   0.01902   0.01088  -0.0347   1.0000   0.0875
  -6.000  -0.5925   0.01851   0.01034  -0.0342   1.0000   0.0923
  -5.750  -0.5692   0.01771   0.00961  -0.0338   1.0000   0.0974
  -5.500  -0.5447   0.01717   0.00912  -0.0338   1.0000   0.1040
  -5.250  -0.5191   0.01651   0.00850  -0.0340   1.0000   0.1118
  -5.000  -0.4927   0.01602   0.00805  -0.0343   1.0000   0.1220
  -4.750  -0.4641   0.01537   0.00752  -0.0353   1.0000   0.1377
  -4.500  -0.4321   0.01456   0.00697  -0.0372   1.0000   0.1684
  -4.250  -0.3882   0.01289   0.00615  -0.0427   1.0000   0.3079
  -4.000  -0.3491   0.01186   0.00650  -0.0459   1.0000   0.5723
  -3.750  -0.3257   0.01229   0.00697  -0.0448   1.0000   0.6184
  -3.500  -0.3019   0.01273   0.00738  -0.0438   1.0000   0.6439
  -3.250  -0.2799   0.01324   0.00786  -0.0424   1.0000   0.6610
  -3.000  -0.2605   0.01381   0.00844  -0.0404   1.0000   0.6739
  -2.750  -0.2426   0.01438   0.00904  -0.0381   1.0000   0.6834
  -2.500  -0.2188   0.01479   0.00940  -0.0374   1.0000   0.6954
  -2.250  -0.1985   0.01541   0.01008  -0.0353   0.9981   0.7023
  -2.000  -0.1604   0.01582   0.01044  -0.0372   0.9943   0.7139
  -1.750  -0.1346   0.01646   0.01115  -0.0357   0.9886   0.7209
  -1.500  -0.1011   0.01700   0.01169  -0.0362   0.9840   0.7333
  -1.250  -0.0776   0.01762   0.01237  -0.0339   0.9776   0.7416
  -1.000  -0.0453   0.01795   0.01271  -0.0344   0.9727   0.7519
  -0.750  -0.0152   0.01823   0.01302  -0.0340   0.9672   0.7581
  -0.500   0.0295   0.01811   0.01288  -0.0378   0.9603   0.7663
  -0.250   0.0672   0.01801   0.01280  -0.0388   0.9535   0.7692
   0.000   0.1040   0.01784   0.01266  -0.0401   0.9455   0.7725
   0.250   0.1555   0.01741   0.01225  -0.0442   0.9385   0.7761
   0.500   0.2095   0.01672   0.01157  -0.0487   0.9278   0.7797
   0.750   0.2491   0.01628   0.01115  -0.0509   0.9169   0.7832
   1.000   0.2820   0.01586   0.01077  -0.0508   0.9059   0.7852
   1.250   0.3138   0.01544   0.01038  -0.0506   0.8918   0.7875
   1.500   0.3422   0.01513   0.01009  -0.0500   0.8744   0.7902
   1.750   0.3715   0.01484   0.00982  -0.0498   0.8532   0.7931
   2.000   0.4030   0.01456   0.00951  -0.0501   0.8273   0.7957
   2.250   0.4370   0.01436   0.00925  -0.0513   0.7934   0.7991
   2.500   0.4608   0.01420   0.00901  -0.0496   0.7504   0.8007
   2.750   0.4846   0.01422   0.00879  -0.0480   0.6765   0.8024
   3.000   0.5012   0.01498   0.00868  -0.0454   0.4915   0.8044
   3.250   0.5170   0.01631   0.00904  -0.0437   0.3065   0.8066
   3.500   0.5392   0.01732   0.00943  -0.0433   0.2026   0.8089
   3.750   0.5657   0.01803   0.00984  -0.0436   0.1628   0.8113
   4.000   0.5947   0.01869   0.01034  -0.0444   0.1415   0.8142
   4.250   0.6209   0.01926   0.01080  -0.0444   0.1279   0.8165
   4.500   0.6456   0.01958   0.01114  -0.0438   0.1182   0.8184
   4.750   0.6698   0.02017   0.01169  -0.0431   0.1104   0.8207
   5.000   0.6961   0.02059   0.01211  -0.0429   0.1034   0.8232
   5.250   0.7230   0.02135   0.01282  -0.0431   0.0975   0.8257
   5.500   0.7522   0.02180   0.01331  -0.0436   0.0917   0.8281
   5.750   0.7814   0.02286   0.01423  -0.0444   0.0865   0.8304
   6.000   0.8093   0.02327   0.01477  -0.0445   0.0822   0.8324
   6.250   0.8343   0.02379   0.01530  -0.0440   0.0780   0.8344
   6.500   0.8598   0.02496   0.01647  -0.0438   0.0744   0.8365
   6.750   0.8862   0.02558   0.01723  -0.0435   0.0708   0.8389
   7.000   0.9129   0.02626   0.01792  -0.0436   0.0674   0.8418
   7.250   0.9409   0.02785   0.01952  -0.0441   0.0646   0.8448
   7.500   0.9682   0.02880   0.02070  -0.0442   0.0618   0.8474
   7.750   0.9916   0.02957   0.02158  -0.0435   0.0593   0.8496
   8.000   1.0158   0.03063   0.02259  -0.0432   0.0572   0.8520
   8.250   1.0381   0.03248   0.02472  -0.0425   0.0554   0.8549
   8.500   1.0600   0.03421   0.02681  -0.0417   0.0538   0.8581
   8.750   1.0824   0.03610   0.02898  -0.0413   0.0522   0.8612
   9.000   1.1038   0.03742   0.03041  -0.0407   0.0509   0.8637
   9.250   1.1241   0.03867   0.03167  -0.0400   0.0496   0.8663
   9.500   1.1377   0.04160   0.03489  -0.0387   0.0485   0.8691
   9.750   1.1447   0.04465   0.03851  -0.0364   0.0477   0.8722
  10.000   1.1471   0.04864   0.04303  -0.0340   0.0472   0.8755
  10.250   1.1424   0.05308   0.04795  -0.0312   0.0471   0.8785
  10.500   1.1302   0.05761   0.05290  -0.0280   0.0472   0.8815
  10.750   1.1134   0.06227   0.05790  -0.0250   0.0474   0.8846
  11.000   1.0918   0.06639   0.06228  -0.0218   0.0477   0.8881
  11.250   1.0704   0.07113   0.06722  -0.0204   0.0480   0.8914
  11.500   1.0500   0.07596   0.07222  -0.0200   0.0483   0.8943
  11.750   1.0390   0.08086   0.07720  -0.0204   0.0487   0.8973
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