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NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il)
Reynolds number: 200,000
Max Cl/Cd: 35.25 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20414-il-200000.txt
Download as CSV file: xf-sc20414-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0414 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7666   0.10341   0.09887  -0.0374   1.0000   0.0585
 -14.000  -0.8024   0.09182   0.08720  -0.0440   1.0000   0.0577
 -13.750  -0.8590   0.07899   0.07414  -0.0519   1.0000   0.0568
 -13.500  -0.9071   0.06969   0.06457  -0.0566   1.0000   0.0562
 -13.250  -0.9445   0.06281   0.05742  -0.0588   1.0000   0.0558
 -13.000  -0.9727   0.05754   0.05188  -0.0594   1.0000   0.0558
 -12.750  -0.9940   0.05333   0.04741  -0.0591   1.0000   0.0559
 -12.500  -1.0104   0.04989   0.04372  -0.0580   1.0000   0.0562
 -12.250  -1.0243   0.04710   0.04070  -0.0560   1.0000   0.0566
 -12.000  -1.0331   0.04449   0.03782  -0.0544   1.0000   0.0572
 -11.750  -1.0364   0.04206   0.03506  -0.0529   1.0000   0.0579
 -11.500  -1.0370   0.04009   0.03271  -0.0512   1.0000   0.0587
 -11.250  -1.0218   0.03775   0.03036  -0.0503   1.0000   0.0597
 -11.000  -1.0063   0.03644   0.02904  -0.0493   1.0000   0.0608
 -10.750  -0.9909   0.03518   0.02771  -0.0482   1.0000   0.0618
 -10.500  -0.9761   0.03384   0.02626  -0.0470   1.0000   0.0631
 -10.250  -0.9615   0.03249   0.02473  -0.0457   1.0000   0.0645
 -10.000  -0.9473   0.03133   0.02330  -0.0445   1.0000   0.0660
  -9.750  -0.9293   0.02982   0.02180  -0.0433   1.0000   0.0677
  -9.500  -0.9110   0.02897   0.02099  -0.0422   1.0000   0.0694
  -9.250  -0.8932   0.02810   0.02007  -0.0410   1.0000   0.0712
  -9.000  -0.8752   0.02721   0.01907  -0.0397   1.0000   0.0732
  -8.750  -0.8571   0.02643   0.01811  -0.0386   1.0000   0.0751
  -8.500  -0.8388   0.02533   0.01715  -0.0371   1.0000   0.0774
  -8.250  -0.8202   0.02470   0.01655  -0.0360   1.0000   0.0800
  -8.000  -0.8012   0.02408   0.01585  -0.0349   1.0000   0.0828
  -7.750  -0.7820   0.02335   0.01504  -0.0337   1.0000   0.0853
  -7.500  -0.7635   0.02257   0.01439  -0.0325   1.0000   0.0883
  -7.250  -0.7436   0.02205   0.01388  -0.0317   1.0000   0.0918
  -7.000  -0.7226   0.02162   0.01335  -0.0309   1.0000   0.0954
  -6.750  -0.7032   0.02079   0.01267  -0.0300   1.0000   0.0994
  -6.500  -0.6813   0.02032   0.01223  -0.0296   1.0000   0.1042
  -6.250  -0.6588   0.01977   0.01167  -0.0292   1.0000   0.1094
  -6.000  -0.6354   0.01922   0.01122  -0.0293   1.0000   0.1156
  -5.750  -0.6108   0.01874   0.01076  -0.0294   1.0000   0.1228
  -5.500  -0.5852   0.01824   0.01035  -0.0300   1.0000   0.1321
  -5.250  -0.5577   0.01764   0.00986  -0.0310   1.0000   0.1440
  -5.000  -0.5285   0.01705   0.00941  -0.0324   1.0000   0.1616
  -4.750  -0.4914   0.01625   0.00887  -0.0356   0.9991   0.1963
  -4.500  -0.4421   0.01457   0.00802  -0.0426   0.9989   0.3284
  -4.250  -0.3985   0.01378   0.00847  -0.0467   0.9979   0.5487
  -4.000  -0.3607   0.01428   0.00903  -0.0483   0.9941   0.5969
  -3.750  -0.3258   0.01485   0.00957  -0.0493   0.9899   0.6211
  -3.500  -0.2929   0.01548   0.01018  -0.0497   0.9851   0.6366
  -3.250  -0.2568   0.01610   0.01078  -0.0508   0.9816   0.6495
  -3.000  -0.2263   0.01662   0.01127  -0.0508   0.9759   0.6600
  -2.750  -0.1961   0.01723   0.01189  -0.0505   0.9711   0.6674
  -2.500  -0.1632   0.01794   0.01262  -0.0504   0.9679   0.6752
  -2.250  -0.1370   0.01833   0.01300  -0.0497   0.9610   0.6840
  -2.000  -0.1095   0.01902   0.01373  -0.0483   0.9564   0.6889
  -1.750  -0.0671   0.01926   0.01392  -0.0513   0.9540   0.7005
  -1.500  -0.0529   0.01994   0.01468  -0.0469   0.9453   0.7044
  -1.250  -0.0254   0.02065   0.01543  -0.0450   0.9410   0.7120
  -1.000   0.0156   0.02087   0.01565  -0.0468   0.9384   0.7219
  -0.750   0.0337   0.02112   0.01594  -0.0438   0.9286   0.7260
  -0.500   0.0782   0.02095   0.01578  -0.0463   0.9249   0.7308
  -0.250   0.1413   0.02024   0.01502  -0.0541   0.9224   0.7382
   0.000   0.1638   0.02004   0.01486  -0.0517   0.9108   0.7404
   0.250   0.2005   0.01952   0.01436  -0.0516   0.9006   0.7431
   0.500   0.2354   0.01896   0.01380  -0.0517   0.8892   0.7462
   0.750   0.2659   0.01854   0.01339  -0.0520   0.8765   0.7492
   1.000   0.3036   0.01806   0.01289  -0.0540   0.8662   0.7532
   1.250   0.3390   0.01759   0.01242  -0.0557   0.8534   0.7567
   1.500   0.3631   0.01733   0.01218  -0.0542   0.8387   0.7584
   1.750   0.3885   0.01709   0.01195  -0.0529   0.8227   0.7606
   2.000   0.4147   0.01685   0.01173  -0.0519   0.8035   0.7634
   2.250   0.4438   0.01660   0.01144  -0.0517   0.7799   0.7663
   2.500   0.4746   0.01634   0.01112  -0.0522   0.7483   0.7688
   2.750   0.5075   0.01616   0.01079  -0.0533   0.7012   0.7716
   3.000   0.5351   0.01619   0.01047  -0.0531   0.6116   0.7738
   3.250   0.5468   0.01701   0.01046  -0.0495   0.4523   0.7755
   3.500   0.5599   0.01807   0.01081  -0.0470   0.3192   0.7776
   3.750   0.5791   0.01894   0.01117  -0.0459   0.2327   0.7798
   4.000   0.6025   0.01961   0.01152  -0.0456   0.1907   0.7819
   4.250   0.6291   0.02010   0.01187  -0.0458   0.1669   0.7841
   4.500   0.6575   0.02060   0.01225  -0.0465   0.1508   0.7865
   4.750   0.6878   0.02116   0.01269  -0.0477   0.1384   0.7889
   5.000   0.7157   0.02156   0.01303  -0.0481   0.1286   0.7909
   5.250   0.7377   0.02202   0.01350  -0.0469   0.1212   0.7927
   5.500   0.7609   0.02248   0.01391  -0.0461   0.1146   0.7948
   5.750   0.7856   0.02309   0.01451  -0.0456   0.1087   0.7971
   6.000   0.8125   0.02354   0.01495  -0.0457   0.1031   0.7993
   6.250   0.8399   0.02438   0.01572  -0.0460   0.0984   0.8020
   6.500   0.8700   0.02489   0.01628  -0.0468   0.0937   0.8050
   6.750   0.9002   0.02560   0.01690  -0.0479   0.0897   0.8073
   7.000   0.9247   0.02644   0.01779  -0.0473   0.0864   0.8089
   7.250   0.9489   0.02698   0.01844  -0.0467   0.0830   0.8107
   7.500   0.9740   0.02763   0.01904  -0.0464   0.0800   0.8128
   7.750   1.0008   0.02887   0.02029  -0.0465   0.0773   0.8149
   8.000   1.0270   0.02966   0.02126  -0.0464   0.0748   0.8174
   8.250   1.0539   0.03049   0.02216  -0.0466   0.0722   0.8203
   8.500   1.0835   0.03151   0.02309  -0.0476   0.0700   0.8233
   8.750   1.1067   0.03280   0.02455  -0.0471   0.0680   0.8253
   9.000   1.1278   0.03389   0.02588  -0.0460   0.0661   0.8274
   9.250   1.1497   0.03503   0.02716  -0.0453   0.0645   0.8296
   9.500   1.1723   0.03608   0.02830  -0.0448   0.0630   0.8320
   9.750   1.1970   0.03746   0.02963  -0.0449   0.0616   0.8346
  10.000   1.2150   0.03946   0.03195  -0.0440   0.0603   0.8373
  10.250   1.2307   0.04144   0.03431  -0.0429   0.0589   0.8399
  10.500   1.2429   0.04334   0.03651  -0.0411   0.0578   0.8423
  10.750   1.2539   0.04522   0.03862  -0.0391   0.0569   0.8449
  11.000   1.2665   0.04694   0.04049  -0.0376   0.0560   0.8478
  11.250   1.2820   0.04855   0.04218  -0.0366   0.0553   0.8508
  11.500   1.2966   0.05063   0.04433  -0.0358   0.0546   0.8535
  11.750   1.2995   0.05415   0.04807  -0.0342   0.0540   0.8561
  12.000   1.2828   0.05728   0.05164  -0.0299   0.0537   0.8583
  12.250   1.2585   0.06037   0.05509  -0.0250   0.0535   0.8607
  12.500   1.2323   0.06441   0.05947  -0.0216   0.0534   0.8632
  12.750   1.2037   0.06919   0.06457  -0.0197   0.0534   0.8655
  13.000   1.1720   0.07495   0.07062  -0.0196   0.0535   0.8676
  13.250   1.1398   0.08167   0.07758  -0.0212   0.0536   0.8694
  13.500   1.1072   0.08952   0.08564  -0.0247   0.0538   0.8710
  13.750   1.0774   0.09825   0.09453  -0.0295   0.0541   0.8724
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