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N-10 (n10-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 200,000
Max Cl/Cd: 68.87 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n10-il-200000-n5.txt
Download as CSV file: xf-n10-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-10                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4132   0.08818   0.08455  -0.0409   0.9999   0.0269
 -11.000  -0.4255   0.08294   0.07938  -0.0428   0.9999   0.0273
 -10.750  -0.4464   0.07725   0.07378  -0.0446   0.9999   0.0277
 -10.250  -0.5547   0.04024   0.03583  -0.0706   0.9889   0.0288
 -10.000  -0.5315   0.03676   0.03206  -0.0737   0.9845   0.0298
  -9.750  -0.5062   0.03491   0.03005  -0.0752   0.9786   0.0306
  -9.500  -0.4777   0.03279   0.02768  -0.0773   0.9746   0.0317
  -9.250  -0.4532   0.03051   0.02507  -0.0784   0.9681   0.0332
  -9.000  -0.4256   0.02770   0.02173  -0.0800   0.9636   0.0347
  -8.750  -0.3987   0.02559   0.01913  -0.0808   0.9577   0.0358
  -8.500  -0.3701   0.02374   0.01697  -0.0817   0.9523   0.0370
  -8.250  -0.3380   0.02251   0.01563  -0.0831   0.9486   0.0381
  -8.000  -0.3112   0.02148   0.01444  -0.0831   0.9406   0.0390
  -7.750  -0.2795   0.02041   0.01319  -0.0841   0.9357   0.0400
  -7.500  -0.2500   0.01952   0.01213  -0.0845   0.9292   0.0411
  -7.250  -0.2195   0.01871   0.01117  -0.0851   0.9228   0.0426
  -7.000  -0.1871   0.01787   0.01016  -0.0859   0.9173   0.0438
  -6.750  -0.1576   0.01711   0.00927  -0.0861   0.9083   0.0445
  -6.500  -0.1261   0.01643   0.00846  -0.0867   0.8997   0.0452
  -6.250  -0.0958   0.01555   0.00755  -0.0871   0.8900   0.0465
  -6.000  -0.0666   0.01497   0.00693  -0.0873   0.8792   0.0479
  -5.750  -0.0369   0.01454   0.00644  -0.0875   0.8693   0.0500
  -5.500  -0.0075   0.01414   0.00597  -0.0876   0.8591   0.0524
  -5.250   0.0204   0.01379   0.00553  -0.0874   0.8477   0.0545
  -5.000   0.0483   0.01342   0.00509  -0.0872   0.8367   0.0568
  -4.750   0.0762   0.01310   0.00472  -0.0871   0.8261   0.0608
  -4.500   0.1037   0.01287   0.00442  -0.0868   0.8148   0.0663
  -4.250   0.1309   0.01261   0.00416  -0.0866   0.8034   0.0760
  -4.000   0.1581   0.01238   0.00392  -0.0863   0.7916   0.0928
  -3.750   0.1850   0.01210   0.00368  -0.0860   0.7794   0.1177
  -3.500   0.2113   0.01177   0.00358  -0.0857   0.7663   0.1787
  -3.250   0.2382   0.01162   0.00347  -0.0854   0.7527   0.2180
  -3.000   0.2650   0.01145   0.00336  -0.0852   0.7401   0.2524
  -2.750   0.2910   0.01112   0.00329  -0.0849   0.7274   0.3263
  -2.500   0.3155   0.01061   0.00326  -0.0844   0.7140   0.4685
  -2.250   0.3388   0.01016   0.00323  -0.0834   0.7001   0.6060
  -2.000   0.3588   0.00969   0.00328  -0.0810   0.6864   0.7786
  -1.750   0.3923   0.00955   0.00328  -0.0813   0.6719   0.9161
  -1.500   0.4382   0.00959   0.00319  -0.0849   0.6567   0.9871
  -1.250   0.4706   0.00969   0.00313  -0.0859   0.6423   1.0001
  -1.000   0.4957   0.00981   0.00312  -0.0853   0.6282   1.0001
  -0.750   0.5208   0.00995   0.00313  -0.0847   0.6138   1.0001
  -0.500   0.5460   0.01009   0.00316  -0.0842   0.5984   1.0001
  -0.250   0.5710   0.01025   0.00320  -0.0836   0.5813   1.0001
   0.000   0.5961   0.01040   0.00325  -0.0830   0.5614   1.0001
   0.250   0.6209   0.01058   0.00331  -0.0824   0.5372   1.0001
   0.500   0.6451   0.01079   0.00337  -0.0817   0.5070   1.0001
   1.000   0.6910   0.01141   0.00358  -0.0800   0.4446   1.0001
   1.250   0.7145   0.01175   0.00375  -0.0792   0.4234   1.0001
   1.500   0.7384   0.01206   0.00394  -0.0786   0.4074   1.0001
   1.750   0.7627   0.01237   0.00415  -0.0781   0.3956   1.0001
   2.000   0.7877   0.01263   0.00436  -0.0777   0.3858   1.0001
   2.250   0.8126   0.01291   0.00458  -0.0773   0.3770   1.0001
   2.500   0.8375   0.01319   0.00482  -0.0769   0.3686   1.0001
   2.750   0.8625   0.01346   0.00506  -0.0765   0.3614   1.0001
   3.000   0.8876   0.01373   0.00531  -0.0762   0.3540   1.0001
   3.250   0.9124   0.01403   0.00558  -0.0758   0.3481   1.0001
   3.500   0.9379   0.01426   0.00585  -0.0756   0.3424   1.0001
   3.750   0.9628   0.01455   0.00613  -0.0752   0.3366   1.0001
   4.000   0.9876   0.01484   0.00644  -0.0749   0.3311   1.0001
   4.250   1.0127   0.01509   0.00674  -0.0746   0.3249   1.0001
   4.500   1.0369   0.01541   0.00706  -0.0742   0.3188   1.0001
   4.750   1.0618   0.01567   0.00739  -0.0739   0.3128   1.0001
   5.000   1.0862   0.01595   0.00773  -0.0735   0.3067   1.0001
   5.250   1.1100   0.01628   0.00808  -0.0731   0.3010   1.0001
   5.500   1.1345   0.01653   0.00844  -0.0727   0.2940   1.0001
   5.750   1.1573   0.01687   0.00882  -0.0721   0.2861   1.0001
   6.000   1.1804   0.01714   0.00917  -0.0716   0.2739   1.0001
   6.250   1.2021   0.01747   0.00952  -0.0708   0.2573   1.0001
   6.500   1.2230   0.01784   0.00990  -0.0700   0.2324   1.0001
   6.750   1.2395   0.01850   0.01038  -0.0685   0.1948   1.0001
   7.000   1.2535   0.01938   0.01108  -0.0668   0.1683   1.0001
   7.250   1.2686   0.02020   0.01184  -0.0652   0.1534   1.0001
   7.500   1.2835   0.02100   0.01261  -0.0636   0.1421   1.0001
   7.750   1.2971   0.02177   0.01338  -0.0617   0.1322   1.0001
   8.000   1.3109   0.02249   0.01414  -0.0599   0.1220   1.0001
   8.250   1.3236   0.02330   0.01498  -0.0580   0.1131   1.0001
   8.500   1.3358   0.02416   0.01585  -0.0562   0.1022   1.0001
   8.750   1.3489   0.02500   0.01671  -0.0546   0.0839   1.0001
   9.000   1.3492   0.02673   0.01814  -0.0517   0.0498   1.0001
   9.250   1.3469   0.02872   0.02001  -0.0487   0.0302   1.0001
   9.500   1.3488   0.03051   0.02180  -0.0464   0.0237   1.0001
   9.750   1.3530   0.03221   0.02356  -0.0445   0.0211   1.0001
  10.000   1.3560   0.03409   0.02554  -0.0428   0.0194   1.0001
  10.250   1.3611   0.03586   0.02746  -0.0415   0.0185   1.0001
  10.500   1.3646   0.03785   0.02959  -0.0402   0.0177   1.0001
  10.750   1.3666   0.04006   0.03195  -0.0392   0.0170   1.0001
  11.000   1.3666   0.04255   0.03459  -0.0383   0.0164   1.0001
  11.250   1.3643   0.04541   0.03758  -0.0376   0.0159   1.0001
  11.500   1.3592   0.04870   0.04102  -0.0371   0.0154   1.0001
  11.750   1.3507   0.05257   0.04504  -0.0370   0.0149   1.0001
  12.000   1.3458   0.05618   0.04880  -0.0372   0.0146   1.0001
  12.250   1.3409   0.05990   0.05268  -0.0376   0.0143   1.0001
  12.500   1.3345   0.06396   0.05690  -0.0382   0.0140   1.0001
  12.750   1.3270   0.06834   0.06144  -0.0391   0.0138   1.0001
  13.000   1.3184   0.07300   0.06625  -0.0402   0.0136   1.0001
  13.250   1.3095   0.07787   0.07126  -0.0415   0.0134   1.0001
  13.500   1.3005   0.08289   0.07642  -0.0430   0.0132   1.0001
  13.750   1.2918   0.08795   0.08160  -0.0445   0.0131   1.0001
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