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NACA 1412 (naca1412-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 1412 (naca1412-il)
Reynolds number: 50,000
Max Cl/Cd: 31.15 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1412-il-50000-n5.txt
Download as CSV file: xf-naca1412-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1412                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6491   0.09164   0.08382  -0.0263   1.0000   0.0810
 -10.750  -0.7098   0.07546   0.06759  -0.0390   1.0000   0.0789
 -10.500  -0.7844   0.06482   0.05664  -0.0434   1.0000   0.0766
 -10.250  -0.7911   0.06154   0.05324  -0.0426   1.0000   0.0777
  -9.750  -0.8008   0.05474   0.04598  -0.0403   1.0000   0.0799
  -9.500  -0.8019   0.05135   0.04227  -0.0388   1.0000   0.0811
  -9.250  -0.7994   0.04821   0.03879  -0.0372   1.0000   0.0829
  -9.000  -0.7949   0.04525   0.03537  -0.0355   1.0000   0.0854
  -8.750  -0.7860   0.04263   0.03235  -0.0339   1.0000   0.0880
  -8.500  -0.7699   0.04091   0.03062  -0.0327   1.0000   0.0906
  -8.250  -0.7543   0.03902   0.02854  -0.0314   1.0000   0.0933
  -8.000  -0.7383   0.03709   0.02631  -0.0299   1.0000   0.0966
  -7.750  -0.7217   0.03528   0.02415  -0.0285   1.0000   0.1010
  -7.500  -0.7033   0.03402   0.02296  -0.0273   1.0000   0.1054
  -7.250  -0.6846   0.03262   0.02140  -0.0259   1.0000   0.1108
  -7.000  -0.6650   0.03120   0.01981  -0.0246   1.0000   0.1161
  -6.750  -0.6463   0.03011   0.01873  -0.0233   1.0000   0.1233
  -6.500  -0.6271   0.02900   0.01756  -0.0220   1.0000   0.1322
  -6.250  -0.6076   0.02799   0.01644  -0.0206   1.0000   0.1431
  -6.000  -0.5890   0.02704   0.01557  -0.0192   1.0000   0.1557
  -5.750  -0.5700   0.02615   0.01469  -0.0179   1.0000   0.1712
  -5.500  -0.5510   0.02533   0.01391  -0.0166   1.0000   0.1905
  -5.250  -0.5325   0.02455   0.01326  -0.0152   1.0000   0.2122
  -5.000  -0.5133   0.02384   0.01261  -0.0140   1.0000   0.2388
  -4.750  -0.4939   0.02318   0.01204  -0.0127   1.0000   0.2688
  -4.500  -0.4745   0.02256   0.01156  -0.0115   1.0000   0.3015
  -4.250  -0.4549   0.02199   0.01114  -0.0102   1.0000   0.3362
  -4.000  -0.4357   0.02148   0.01078  -0.0089   1.0000   0.3737
  -3.750  -0.4167   0.02104   0.01048  -0.0074   1.0000   0.4147
  -3.500  -0.3978   0.02064   0.01028  -0.0059   1.0000   0.4578
  -3.250  -0.3789   0.02030   0.01012  -0.0042   1.0000   0.5039
  -3.000  -0.3600   0.02002   0.01003  -0.0025   1.0000   0.5524
  -2.750  -0.3411   0.01981   0.01001  -0.0006   1.0000   0.6023
  -2.500  -0.3222   0.01967   0.01005   0.0014   1.0000   0.6532
  -2.250  -0.3033   0.01961   0.01015   0.0036   1.0000   0.7046
  -2.000  -0.2839   0.01963   0.01030   0.0057   1.0000   0.7569
  -1.750  -0.2554   0.01977   0.01052   0.0061   0.9967   0.8124
  -1.500  -0.2068   0.02006   0.01079   0.0028   0.9880   0.8674
  -1.250  -0.1493   0.02038   0.01100  -0.0027   0.9802   0.9144
  -1.000  -0.0843   0.02064   0.01113  -0.0100   0.9730   0.9517
  -0.750  -0.0159   0.02077   0.01113  -0.0183   0.9651   0.9798
  -0.500   0.0536   0.02078   0.01103  -0.0272   0.9574   1.0000
  -0.250   0.0954   0.02070   0.01086  -0.0308   0.9421   1.0000
   0.000   0.1386   0.02062   0.01072  -0.0345   0.9274   1.0000
   0.250   0.1777   0.02052   0.01057  -0.0371   0.9112   1.0000
   0.500   0.2129   0.02043   0.01045  -0.0388   0.8937   1.0000
   0.750   0.2458   0.02035   0.01035  -0.0399   0.8754   1.0000
   1.000   0.2772   0.02028   0.01026  -0.0405   0.8568   1.0000
   1.250   0.3076   0.02021   0.01018  -0.0408   0.8380   1.0000
   1.500   0.3371   0.02014   0.01009  -0.0408   0.8191   1.0000
   1.750   0.3659   0.02008   0.01001  -0.0405   0.8001   1.0000
   2.000   0.3912   0.02009   0.01001  -0.0396   0.7794   1.0000
   2.250   0.4157   0.02013   0.01003  -0.0386   0.7582   1.0000
   2.500   0.4408   0.02016   0.01005  -0.0375   0.7377   1.0000
   2.750   0.4662   0.02020   0.01005  -0.0364   0.7175   1.0000
   3.000   0.4884   0.02035   0.01019  -0.0350   0.6951   1.0000
   3.250   0.5122   0.02049   0.01031  -0.0337   0.6730   1.0000
   3.500   0.5363   0.02062   0.01040  -0.0324   0.6511   1.0000
   3.750   0.5583   0.02084   0.01062  -0.0309   0.6269   1.0000
   4.000   0.5817   0.02103   0.01076  -0.0295   0.6038   1.0000
   4.250   0.6033   0.02130   0.01103  -0.0280   0.5785   1.0000
   4.500   0.6261   0.02155   0.01122  -0.0265   0.5543   1.0000
   4.750   0.6470   0.02188   0.01157  -0.0250   0.5275   1.0000
   5.000   0.6683   0.02221   0.01186  -0.0234   0.5006   1.0000
   5.250   0.6891   0.02257   0.01215  -0.0217   0.4728   1.0000
   5.500   0.7088   0.02299   0.01255  -0.0201   0.4425   1.0000
   5.750   0.7280   0.02345   0.01298  -0.0184   0.4115   1.0000
   6.000   0.7467   0.02397   0.01344  -0.0166   0.3797   1.0000
   6.250   0.7646   0.02456   0.01395  -0.0149   0.3470   1.0000
   6.500   0.7816   0.02524   0.01453  -0.0131   0.3136   1.0000
   6.750   0.7977   0.02604   0.01518  -0.0113   0.2804   1.0000
   7.000   0.8132   0.02696   0.01597  -0.0096   0.2478   1.0000
   7.250   0.8281   0.02800   0.01686  -0.0078   0.2185   1.0000
   7.750   0.8578   0.03033   0.01899  -0.0047   0.1720   1.0000
   8.000   0.8732   0.03160   0.02023  -0.0032   0.1542   1.0000
   8.250   0.8884   0.03292   0.02151  -0.0017   0.1404   1.0000
   8.500   0.9038   0.03427   0.02284  -0.0003   0.1292   1.0000
   8.750   0.9214   0.03570   0.02441   0.0010   0.1198   1.0000
   9.000   0.9379   0.03715   0.02582   0.0022   0.1127   1.0000
   9.250   0.9550   0.03866   0.02751   0.0034   0.1056   1.0000
   9.500   0.9725   0.04019   0.02895   0.0044   0.1007   1.0000
   9.750   0.9911   0.04210   0.03117   0.0055   0.0965   1.0000
  10.000   1.0071   0.04397   0.03325   0.0066   0.0925   1.0000
  10.250   1.0230   0.04567   0.03497   0.0076   0.0890   1.0000
  10.500   1.0356   0.04784   0.03733   0.0088   0.0859   1.0000
  10.750   1.0426   0.05034   0.04020   0.0104   0.0832   1.0000
  11.000   1.0483   0.05299   0.04314   0.0120   0.0813   1.0000
  11.250   1.0502   0.05558   0.04597   0.0138   0.0797   1.0000
  11.500   1.0515   0.05811   0.04869   0.0155   0.0780   1.0000
  11.750   1.0560   0.06049   0.05114   0.0167   0.0763   1.0000
  12.000   1.0505   0.06367   0.05447   0.0179   0.0750   1.0000
  12.250   1.0301   0.06792   0.05907   0.0188   0.0745   1.0000
  12.500   1.0061   0.07302   0.06447   0.0182   0.0741   1.0000
  12.750   0.9779   0.07931   0.07101   0.0160   0.0741   1.0000
  13.000   0.9449   0.08725   0.07917   0.0119   0.0743   1.0000
  13.250   0.9069   0.09739   0.08944   0.0057   0.0748   1.0000
  13.500   0.8669   0.10976   0.10191  -0.0021   0.0752   1.0000
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