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N-11 (n11-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 200,000
Max Cl/Cd: 72.03 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n11-il-200000-n5.txt
Download as CSV file: xf-n11-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-11                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3435   0.09521   0.09167  -0.0387   1.0000   0.0284
 -10.250  -0.3501   0.09242   0.08895  -0.0383   1.0000   0.0290
 -10.000  -0.3605   0.08971   0.08630  -0.0373   1.0000   0.0293
  -9.750  -0.3565   0.08482   0.08143  -0.0418   0.9960   0.0295
  -9.500  -0.3477   0.07882   0.07543  -0.0490   0.9884   0.0296
  -9.250  -0.3351   0.07143   0.06802  -0.0594   0.9791   0.0299
  -9.000  -0.3225   0.05974   0.05621  -0.0757   0.9681   0.0310
  -8.750  -0.3242   0.03846   0.03401  -0.0944   0.9538   0.0317
  -8.500  -0.3046   0.03202   0.02684  -0.0985   0.9478   0.0326
  -8.250  -0.2836   0.03002   0.02467  -0.0988   0.9391   0.0334
  -8.000  -0.2556   0.02799   0.02237  -0.1003   0.9341   0.0343
  -7.750  -0.2321   0.02592   0.01996  -0.1005   0.9261   0.0349
  -7.500  -0.2046   0.02400   0.01771  -0.1012   0.9199   0.0355
  -7.250  -0.1776   0.02247   0.01588  -0.1015   0.9131   0.0362
  -7.000  -0.1498   0.02125   0.01440  -0.1017   0.9061   0.0374
  -6.750  -0.1202   0.02005   0.01292  -0.1022   0.9002   0.0383
  -6.500  -0.0924   0.01898   0.01161  -0.1022   0.8926   0.0387
  -6.250  -0.0615   0.01800   0.01043  -0.1028   0.8870   0.0392
  -6.000  -0.0336   0.01722   0.00949  -0.1027   0.8790   0.0397
  -5.500   0.0249   0.01579   0.00782  -0.1031   0.8648   0.0407
  -5.250   0.0544   0.01505   0.00703  -0.1034   0.8583   0.0422
  -5.000   0.0819   0.01459   0.00654  -0.1032   0.8499   0.0436
  -4.750   0.1109   0.01416   0.00603  -0.1033   0.8421   0.0447
  -4.500   0.1387   0.01378   0.00558  -0.1031   0.8323   0.0458
  -4.250   0.1665   0.01346   0.00518  -0.1029   0.8223   0.0470
  -4.000   0.1947   0.01319   0.00480  -0.1027   0.8125   0.0485
  -3.750   0.2218   0.01296   0.00450  -0.1024   0.8015   0.0502
  -3.500   0.2489   0.01272   0.00423  -0.1021   0.7911   0.0537
  -3.250   0.2764   0.01254   0.00400  -0.1018   0.7810   0.0595
  -3.000   0.3030   0.01231   0.00383  -0.1015   0.7693   0.0776
  -2.750   0.3294   0.01208   0.00369  -0.1011   0.7569   0.1106
  -2.500   0.3560   0.01190   0.00358  -0.1008   0.7442   0.1455
  -2.250   0.3827   0.01175   0.00350  -0.1005   0.7325   0.1832
  -2.000   0.4094   0.01161   0.00343  -0.1002   0.7210   0.2187
  -1.750   0.4357   0.01144   0.00337  -0.0999   0.7084   0.2642
  -1.500   0.4616   0.01119   0.00333  -0.0996   0.6954   0.3443
  -1.250   0.4833   0.01047   0.00338  -0.0985   0.6826   0.5904
  -1.000   0.5299   0.00968   0.00339  -0.1015   0.6693   1.0000
  -0.750   0.5555   0.00979   0.00334  -0.1009   0.6564   1.0000
  -0.500   0.5810   0.00991   0.00332  -0.1004   0.6429   1.0000
  -0.250   0.6065   0.01004   0.00332  -0.0998   0.6291   1.0000
   0.000   0.6319   0.01019   0.00334  -0.0993   0.6152   1.0000
   0.250   0.6574   0.01034   0.00338  -0.0988   0.6018   1.0000
   0.500   0.6829   0.01050   0.00344  -0.0983   0.5890   1.0000
   0.750   0.7084   0.01067   0.00351  -0.0978   0.5760   1.0000
   1.000   0.7335   0.01085   0.00360  -0.0972   0.5613   1.0000
   1.250   0.7582   0.01105   0.00370  -0.0966   0.5442   1.0000
   1.500   0.7827   0.01127   0.00380  -0.0960   0.5261   1.0000
   1.750   0.8070   0.01149   0.00393  -0.0954   0.5079   1.0000
   2.000   0.8309   0.01174   0.00407  -0.0947   0.4887   1.0000
   2.250   0.8548   0.01199   0.00423  -0.0940   0.4684   1.0000
   2.500   0.8785   0.01226   0.00440  -0.0933   0.4478   1.0000
   2.750   0.9020   0.01255   0.00460  -0.0926   0.4292   1.0000
   3.000   0.9254   0.01285   0.00482  -0.0919   0.4123   1.0000
   3.250   0.9487   0.01317   0.00505  -0.0911   0.3965   1.0000
   3.500   0.9717   0.01350   0.00532  -0.0904   0.3818   1.0000
   3.750   0.9947   0.01385   0.00560  -0.0897   0.3679   1.0000
   4.000   1.0177   0.01420   0.00590  -0.0890   0.3554   1.0000
   4.250   1.0407   0.01455   0.00622  -0.0883   0.3450   1.0000
   4.500   1.0635   0.01492   0.00655  -0.0876   0.3359   1.0000
   4.750   1.0872   0.01524   0.00689  -0.0871   0.3283   1.0000
   5.000   1.1100   0.01561   0.00726  -0.0864   0.3211   1.0000
   5.250   1.1332   0.01595   0.00763  -0.0858   0.3137   1.0000
   5.500   1.1555   0.01633   0.00801  -0.0851   0.3054   1.0000
   5.750   1.1782   0.01668   0.00840  -0.0845   0.2975   1.0000
   6.000   1.2000   0.01708   0.00882  -0.0837   0.2894   1.0000
   6.250   1.2217   0.01744   0.00923  -0.0829   0.2787   1.0000
   6.500   1.2423   0.01784   0.00964  -0.0819   0.2661   1.0000
   6.750   1.2621   0.01826   0.01007  -0.0809   0.2525   1.0000
   7.000   1.2817   0.01870   0.01053  -0.0798   0.2397   1.0000
   7.250   1.3005   0.01917   0.01101  -0.0786   0.2263   1.0000
   7.500   1.3174   0.01970   0.01153  -0.0771   0.2100   1.0000
   7.750   1.3309   0.02035   0.01211  -0.0752   0.1912   1.0000
   8.000   1.3434   0.02112   0.01281  -0.0731   0.1746   1.0000
   8.250   1.3557   0.02194   0.01361  -0.0711   0.1595   1.0000
   8.500   1.3683   0.02277   0.01443  -0.0693   0.1450   1.0000
   8.750   1.3801   0.02367   0.01531  -0.0674   0.1255   1.0000
   9.000   1.3822   0.02525   0.01663  -0.0646   0.0909   1.0000
   9.250   1.3867   0.02673   0.01803  -0.0621   0.0757   1.0000
   9.500   1.3934   0.02810   0.01941  -0.0600   0.0620   1.0000
  10.000   1.3881   0.03248   0.02355  -0.0548   0.0229   1.0000
  10.250   1.3917   0.03432   0.02547  -0.0531   0.0206   1.0000
  10.500   1.3954   0.03620   0.02748  -0.0516   0.0192   1.0000
  10.750   1.3974   0.03832   0.02972  -0.0502   0.0181   1.0000
  11.000   1.3970   0.04074   0.03227  -0.0489   0.0171   1.0000
  11.250   1.3970   0.04323   0.03490  -0.0479   0.0164   1.0000
  11.500   1.3978   0.04573   0.03755  -0.0471   0.0159   1.0000
  11.750   1.3967   0.04851   0.04049  -0.0464   0.0154   1.0000
  12.000   1.3939   0.05160   0.04376  -0.0460   0.0150   1.0000
  12.250   1.3899   0.05498   0.04729  -0.0458   0.0147   1.0000
  12.500   1.3844   0.05867   0.05113  -0.0459   0.0144   1.0000
  12.750   1.3776   0.06269   0.05531  -0.0462   0.0142   1.0000
  13.000   1.3696   0.06704   0.05981  -0.0468   0.0140   1.0000
  13.250   1.3604   0.07169   0.06460  -0.0477   0.0138   1.0000
  13.500   1.3506   0.07657   0.06963  -0.0487   0.0136   1.0000
  13.750   1.3398   0.08175   0.07494  -0.0500   0.0134   1.0000
  14.000   1.3283   0.08712   0.08045  -0.0515   0.0133   1.0000
  14.250   1.3167   0.09258   0.08603  -0.0530   0.0131   1.0000
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