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N-22 (n22-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 200,000
Max Cl/Cd: 71.69 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n22-il-200000.txt
Download as CSV file: xf-n22-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-22                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3569   0.08899   0.08558  -0.0364   0.9999   0.0806
 -10.000  -0.3844   0.08772   0.08442  -0.0334   0.9999   0.0819
  -9.750  -0.4371   0.07700   0.07363  -0.0551   0.9914   0.0846
  -9.500  -0.4129   0.07552   0.07228  -0.0499   0.9900   0.0857
  -9.250  -0.3870   0.07366   0.07042  -0.0491   0.9867   0.0871
  -9.000  -0.3588   0.07024   0.06696  -0.0533   0.9830   0.0897
  -8.750  -0.3417   0.05780   0.05409  -0.0738   0.9714   0.0986
  -8.500  -0.3381   0.03946   0.03463  -0.0837   0.9613   0.0742
  -8.250  -0.3064   0.03449   0.02932  -0.0869   0.9575   0.0692
  -8.000  -0.2720   0.02938   0.02354  -0.0905   0.9550   0.0679
  -7.750  -0.2458   0.02691   0.02065  -0.0910   0.9464   0.0687
  -7.500  -0.2082   0.02444   0.01775  -0.0934   0.9430   0.0693
  -7.250  -0.1690   0.02257   0.01551  -0.0957   0.9403   0.0705
  -7.000  -0.1404   0.02152   0.01418  -0.0957   0.9318   0.0720
  -6.750  -0.1053   0.01998   0.01247  -0.0970   0.9271   0.0743
  -6.500  -0.0685   0.01895   0.01141  -0.0986   0.9235   0.0768
  -6.250  -0.0427   0.01828   0.01067  -0.0979   0.9134   0.0792
  -6.000  -0.0089   0.01749   0.00976  -0.0985   0.9083   0.0825
  -5.750   0.0169   0.01674   0.00897  -0.0978   0.8984   0.0864
  -5.500   0.0476   0.01611   0.00837  -0.0979   0.8922   0.0917
  -5.250   0.0736   0.01570   0.00786  -0.0970   0.8818   0.0971
  -5.000   0.1021   0.01496   0.00720  -0.0967   0.8746   0.1054
  -4.750   0.1275   0.01449   0.00676  -0.0958   0.8635   0.1166
  -4.500   0.1543   0.01403   0.00634  -0.0952   0.8542   0.1331
  -4.250   0.1816   0.01362   0.00594  -0.0947   0.8450   0.1578
  -4.000   0.2077   0.01322   0.00568  -0.0942   0.8348   0.1870
  -3.750   0.2353   0.01284   0.00537  -0.0938   0.8267   0.2212
  -3.500   0.2611   0.01249   0.00522  -0.0933   0.8156   0.2652
  -3.250   0.2873   0.01203   0.00507  -0.0929   0.8064   0.3461
  -3.000   0.3115   0.01139   0.00498  -0.0921   0.7965   0.4998
  -2.750   0.3311   0.01070   0.00503  -0.0899   0.7862   0.7057
  -2.500   0.3780   0.01015   0.00491  -0.0919   0.7777   0.9742
  -2.250   0.4172   0.01016   0.00479  -0.0942   0.7658   1.0001
  -2.000   0.4428   0.01022   0.00470  -0.0936   0.7549   1.0001
  -1.750   0.4691   0.01027   0.00457  -0.0930   0.7446   1.0001
  -1.500   0.4945   0.01034   0.00454  -0.0924   0.7320   1.0001
  -1.250   0.5204   0.01042   0.00451  -0.0919   0.7200   1.0001
  -1.000   0.5468   0.01051   0.00446  -0.0914   0.7086   1.0001
  -0.750   0.5732   0.01060   0.00443  -0.0909   0.6965   1.0001
  -0.500   0.5992   0.01069   0.00444  -0.0904   0.6829   1.0001
  -0.250   0.6253   0.01080   0.00446  -0.0900   0.6691   1.0001
   0.000   0.6516   0.01091   0.00448  -0.0895   0.6553   1.0001
   0.250   0.6778   0.01104   0.00451  -0.0891   0.6414   1.0001
   0.500   0.7040   0.01118   0.00454  -0.0887   0.6267   1.0001
   0.750   0.7300   0.01132   0.00459  -0.0883   0.6113   1.0001
   1.000   0.7559   0.01149   0.00467  -0.0878   0.5954   1.0001
   1.250   0.7817   0.01168   0.00476  -0.0874   0.5796   1.0001
   1.500   0.8074   0.01189   0.00487  -0.0870   0.5637   1.0001
   1.750   0.8330   0.01213   0.00502  -0.0866   0.5478   1.0001
   2.000   0.8585   0.01238   0.00518  -0.0862   0.5324   1.0001
   2.250   0.8840   0.01266   0.00536  -0.0858   0.5178   1.0001
   2.500   0.9092   0.01293   0.00557  -0.0854   0.5028   1.0001
   2.750   0.9340   0.01321   0.00577  -0.0850   0.4872   1.0001
   3.000   0.9585   0.01350   0.00598  -0.0845   0.4718   1.0001
   3.250   0.9832   0.01379   0.00624  -0.0840   0.4579   1.0001
   3.500   1.0081   0.01411   0.00651  -0.0837   0.4457   1.0001
   3.750   1.0330   0.01446   0.00678  -0.0833   0.4349   1.0001
   4.000   1.0577   0.01477   0.00708  -0.0829   0.4240   1.0001
   4.250   1.0824   0.01510   0.00742  -0.0826   0.4138   1.0001
   4.750   1.1313   0.01578   0.00809  -0.0819   0.3945   1.0001
   5.000   1.1554   0.01616   0.00845  -0.0815   0.3853   1.0001
   5.250   1.1791   0.01650   0.00880  -0.0810   0.3754   1.0001
   5.500   1.2025   0.01686   0.00920  -0.0805   0.3657   1.0001
   5.750   1.2259   0.01729   0.00957  -0.0800   0.3567   1.0001
   6.000   1.2481   0.01760   0.01000  -0.0793   0.3464   1.0001
   6.250   1.2702   0.01801   0.01042  -0.0786   0.3366   1.0001
   6.500   1.2913   0.01842   0.01083  -0.0778   0.3259   1.0001
   6.750   1.3114   0.01879   0.01129  -0.0768   0.3138   1.0001
   7.000   1.3306   0.01922   0.01177  -0.0757   0.3013   1.0001
   7.250   1.3486   0.01970   0.01226  -0.0744   0.2881   1.0001
   7.500   1.3649   0.02021   0.01280  -0.0728   0.2735   1.0001
   7.750   1.3794   0.02077   0.01337  -0.0710   0.2575   1.0001
   8.000   1.3917   0.02139   0.01398  -0.0689   0.2411   1.0001
   8.250   1.4012   0.02210   0.01466  -0.0664   0.2259   1.0001
   8.500   1.4107   0.02293   0.01546  -0.0641   0.2122   1.0001
   8.750   1.4197   0.02386   0.01636  -0.0618   0.2001   1.0001
   9.000   1.4278   0.02491   0.01736  -0.0597   0.1895   1.0001
   9.250   1.4387   0.02588   0.01839  -0.0580   0.1799   1.0001
   9.500   1.4470   0.02705   0.01955  -0.0561   0.1722   1.0001
   9.750   1.4566   0.02818   0.02073  -0.0545   0.1646   1.0001
  10.000   1.4645   0.02946   0.02203  -0.0529   0.1579   1.0001
  10.250   1.4732   0.03070   0.02335  -0.0515   0.1508   1.0001
  10.500   1.4796   0.03218   0.02484  -0.0500   0.1447   1.0001
  10.750   1.4884   0.03351   0.02630  -0.0489   0.1383   1.0001
  11.000   1.4919   0.03530   0.02808  -0.0476   0.1326   1.0001
  11.250   1.5007   0.03673   0.02972  -0.0468   0.1258   1.0001
  11.500   1.5018   0.03887   0.03185  -0.0457   0.1195   1.0001
  11.750   1.5085   0.04065   0.03381  -0.0452   0.1107   1.0001
  12.000   1.5098   0.04301   0.03625  -0.0446   0.1000   1.0001
  12.250   1.5060   0.04604   0.03929  -0.0442   0.0853   1.0001
  12.500   1.4966   0.04978   0.04300  -0.0437   0.0672   1.0001
  12.750   1.4835   0.05411   0.04727  -0.0435   0.0557   1.0001
  13.000   1.4708   0.05859   0.05176  -0.0435   0.0494   1.0001
  13.250   1.4569   0.06342   0.05663  -0.0439   0.0460   1.0001
  13.500   1.4462   0.06804   0.06137  -0.0444   0.0433   1.0001
  13.750   1.4337   0.07303   0.06645  -0.0452   0.0415   1.0001
  14.000   1.4191   0.07848   0.07198  -0.0464   0.0402   1.0001
  14.250   1.4067   0.08372   0.07732  -0.0475   0.0390   1.0001
  14.500   1.3973   0.08860   0.08233  -0.0487   0.0379   1.0001
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