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N-13 (n13-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-13 (n13-il)
Reynolds number: 50,000
Max Cl/Cd: 27.72 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n13-il-50000-n5.txt
Download as CSV file: xf-n13-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-13                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6916   0.10027   0.09268  -0.0313   1.0000   0.0567
 -12.500  -0.7211   0.09000   0.08240  -0.0373   1.0000   0.0557
 -12.250  -0.7538   0.08085   0.07317  -0.0427   1.0000   0.0546
 -12.000  -0.7858   0.07338   0.06556  -0.0464   1.0000   0.0538
 -11.750  -0.8132   0.06766   0.05965  -0.0478   1.0000   0.0534
 -11.500  -0.8351   0.06322   0.05504  -0.0475   1.0000   0.0535
 -11.250  -0.8545   0.05943   0.05102  -0.0458   1.0000   0.0541
 -11.000  -0.8709   0.05615   0.04749  -0.0430   1.0000   0.0551
 -10.750  -0.8853   0.05317   0.04419  -0.0394   1.0000   0.0565
 -10.500  -0.8969   0.05018   0.04072  -0.0356   1.0000   0.0583
 -10.250  -0.8912   0.04830   0.03893  -0.0335   1.0000   0.0611
 -10.000  -0.8874   0.04644   0.03697  -0.0309   1.0000   0.0643
  -9.750  -0.8831   0.04394   0.03411  -0.0282   1.0000   0.0682
  -9.500  -0.8762   0.04245   0.03258  -0.0257   1.0000   0.0727
  -9.250  -0.8687   0.04086   0.03077  -0.0231   1.0000   0.0788
  -9.000  -0.8597   0.03957   0.02940  -0.0207   1.0000   0.0849
  -8.750  -0.8508   0.03811   0.02761  -0.0180   1.0000   0.0932
  -8.500  -0.8406   0.03699   0.02643  -0.0156   1.0000   0.1018
  -8.250  -0.8258   0.03547   0.02474  -0.0138   1.0000   0.1101
  -8.000  -0.8103   0.03410   0.02315  -0.0119   1.0000   0.1197
  -7.750  -0.7910   0.03264   0.02171  -0.0106   1.0000   0.1281
  -7.500  -0.7723   0.03132   0.02026  -0.0090   1.0000   0.1386
  -7.250  -0.7562   0.03021   0.01910  -0.0072   1.0000   0.1513
  -7.000  -0.7404   0.02915   0.01803  -0.0052   1.0000   0.1646
  -6.750  -0.7247   0.02816   0.01698  -0.0033   1.0000   0.1790
  -6.500  -0.7095   0.02724   0.01607  -0.0012   1.0000   0.1950
  -6.250  -0.6952   0.02635   0.01522   0.0009   1.0000   0.2135
  -6.000  -0.6813   0.02547   0.01442   0.0031   1.0000   0.2361
  -5.750  -0.6677   0.02461   0.01369   0.0054   1.0000   0.2612
  -5.500  -0.6553   0.02378   0.01306   0.0079   1.0000   0.2944
  -5.250  -0.6437   0.02301   0.01252   0.0106   1.0000   0.3393
  -5.000  -0.6317   0.02235   0.01206   0.0135   1.0000   0.3926
  -4.750  -0.6190   0.02178   0.01173   0.0164   1.0000   0.4453
  -4.500  -0.6049   0.02136   0.01152   0.0192   1.0000   0.4970
  -4.250  -0.5894   0.02108   0.01135   0.0219   1.0000   0.5439
  -4.000  -0.5726   0.02089   0.01119   0.0244   1.0000   0.5853
  -3.750  -0.5559   0.02074   0.01102   0.0269   1.0000   0.6222
  -3.500  -0.5381   0.02061   0.01088   0.0292   1.0000   0.6555
  -3.250  -0.5183   0.02053   0.01078   0.0311   1.0000   0.6884
  -3.000  -0.4959   0.02054   0.01081   0.0328   1.0000   0.7224
  -2.750  -0.4696   0.02067   0.01096   0.0339   1.0000   0.7573
  -2.500  -0.4393   0.02095   0.01126   0.0343   1.0000   0.7940
  -2.250  -0.3994   0.02151   0.01177   0.0333   1.0000   0.8291
  -2.000  -0.3575   0.02208   0.01225   0.0315   1.0000   0.8586
  -1.750  -0.3164   0.02244   0.01248   0.0292   1.0000   0.8791
  -1.500  -0.2786   0.02263   0.01257   0.0270   1.0000   0.8966
  -1.250  -0.2413   0.02279   0.01262   0.0247   1.0000   0.9130
  -1.000  -0.2035   0.02293   0.01268   0.0221   1.0000   0.9292
  -0.750  -0.1645   0.02305   0.01274   0.0192   1.0000   0.9449
  -0.500  -0.1243   0.02316   0.01281   0.0158   1.0000   0.9603
  -0.250  -0.0809   0.02324   0.01285   0.0116   1.0000   0.9747
   0.000  -0.0356   0.02329   0.01290   0.0069   1.0000   0.9892
   0.250   0.0033   0.02336   0.01296   0.0031   0.9988   1.0000
   0.500   0.0586   0.02331   0.01294  -0.0036   0.9822   1.0000
   0.750   0.1040   0.02319   0.01287  -0.0081   0.9659   1.0000
   1.000   0.1473   0.02308   0.01281  -0.0121   0.9508   1.0000
   1.250   0.1885   0.02294   0.01273  -0.0155   0.9351   1.0000
   1.500   0.2322   0.02276   0.01266  -0.0190   0.9197   1.0000
   1.750   0.2787   0.02251   0.01254  -0.0229   0.9037   1.0000
   2.000   0.3271   0.02222   0.01239  -0.0268   0.8856   1.0000
   2.250   0.3705   0.02188   0.01219  -0.0294   0.8630   1.0000
   2.500   0.4016   0.02160   0.01205  -0.0297   0.8341   1.0000
   2.750   0.4263   0.02135   0.01190  -0.0286   0.8011   1.0000
   3.000   0.4590   0.02096   0.01162  -0.0286   0.7666   1.0000
   3.250   0.4948   0.02061   0.01129  -0.0290   0.7290   1.0000
   3.500   0.5271   0.02042   0.01105  -0.0288   0.6863   1.0000
   3.750   0.5486   0.02050   0.01107  -0.0268   0.6380   1.0000
   4.000   0.5648   0.02068   0.01116  -0.0240   0.5825   1.0000
   4.250   0.5799   0.02096   0.01123  -0.0211   0.5193   1.0000
   4.500   0.5938   0.02142   0.01133  -0.0180   0.4567   1.0000
   4.750   0.6069   0.02205   0.01168  -0.0152   0.4027   1.0000
   5.000   0.6198   0.02275   0.01216  -0.0125   0.3540   1.0000
   5.250   0.6326   0.02348   0.01272  -0.0099   0.3101   1.0000
   5.500   0.6451   0.02426   0.01331  -0.0073   0.2715   1.0000
   5.750   0.6583   0.02511   0.01399  -0.0049   0.2393   1.0000
   6.000   0.6721   0.02600   0.01476  -0.0026   0.2113   1.0000
   6.250   0.6876   0.02694   0.01567  -0.0006   0.1884   1.0000
   6.500   0.7042   0.02793   0.01662   0.0012   0.1709   1.0000
   6.750   0.7208   0.02892   0.01761   0.0031   0.1559   1.0000
   7.000   0.7386   0.02997   0.01869   0.0047   0.1441   1.0000
   7.250   0.7570   0.03110   0.01975   0.0062   0.1351   1.0000
   7.500   0.7753   0.03222   0.02111   0.0078   0.1252   1.0000
   7.750   0.7931   0.03346   0.02241   0.0094   0.1173   1.0000
   8.000   0.8124   0.03487   0.02401   0.0108   0.1110   1.0000
   8.250   0.8302   0.03635   0.02551   0.0122   0.1052   1.0000
   8.500   0.8437   0.03784   0.02730   0.0144   0.0984   1.0000
   8.750   0.8601   0.03938   0.02880   0.0158   0.0934   1.0000
   9.000   0.8696   0.04142   0.03128   0.0184   0.0884   1.0000
   9.250   0.8783   0.04306   0.03315   0.0209   0.0831   1.0000
   9.500   0.8895   0.04487   0.03494   0.0229   0.0789   1.0000
   9.750   0.8879   0.04737   0.03796   0.0265   0.0754   1.0000
  10.000   0.8873   0.04954   0.04041   0.0297   0.0717   1.0000
  10.250   0.8899   0.05148   0.04246   0.0324   0.0687   1.0000
  10.500   0.8950   0.05373   0.04468   0.0345   0.0663   1.0000
  10.750   0.8766   0.05679   0.04816   0.0389   0.0651   1.0000
  11.000   0.8551   0.05974   0.05139   0.0431   0.0642   1.0000
  11.250   0.8318   0.06309   0.05497   0.0462   0.0636   1.0000
  11.500   0.8066   0.06713   0.05921   0.0476   0.0633   1.0000
  11.750   0.7797   0.07211   0.06436   0.0474   0.0637   1.0000
  12.000   0.7509   0.07826   0.07062   0.0452   0.0642   1.0000
  12.250   0.7209   0.08587   0.07829   0.0411   0.0649   1.0000
  12.500   0.6913   0.09508   0.08752   0.0355   0.0654   1.0000
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