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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 50,000
Max Cl/Cd: 6.67 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63158-il-50000.txt
Download as CSV file: xf-fx63158-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-158 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2828   0.11707   0.11099  -0.0319   1.0000   0.3053
  -9.000  -0.2646   0.11313   0.10710  -0.0303   1.0000   0.3186
  -8.750  -0.2580   0.11041   0.10448  -0.0288   1.0000   0.3312
  -8.500  -0.2581   0.10824   0.10243  -0.0270   1.0000   0.3438
  -8.250  -0.2675   0.10688   0.10124  -0.0246   1.0000   0.3559
  -8.000  -0.2972   0.10802   0.10263  -0.0206   1.0000   0.3690
  -7.750  -0.2766   0.10422   0.09889  -0.0185   1.0000   0.3768
  -7.500  -0.3106   0.10561   0.10052  -0.0129   1.0000   0.3871
  -7.250  -0.3168   0.10502   0.10005  -0.0090   1.0000   0.3950
  -5.500  -0.4554   0.06006   0.05346  -0.0677   0.9519   0.1398
  -5.250  -0.4123   0.05461   0.04709  -0.0730   0.9442   0.1170
  -5.000  -0.3726   0.05125   0.04293  -0.0764   0.9361   0.1056
  -4.750  -0.3357   0.04815   0.03966  -0.0788   0.9282   0.1009
  -4.500  -0.2949   0.04597   0.03666  -0.0812   0.9207   0.0950
  -4.250  -0.2629   0.04432   0.03471  -0.0821   0.9129   0.0934
  -4.000  -0.2224   0.04276   0.03290  -0.0837   0.9069   0.0929
  -3.750  -0.2050   0.04208   0.03206  -0.0819   0.8989   0.0932
  -3.500  -0.1741   0.04125   0.03123  -0.0813   0.8925   0.0968
  -3.250  -0.1588   0.04103   0.03103  -0.0787   0.8856   0.1008
  -3.000  -0.1387   0.04085   0.03076  -0.0769   0.8791   0.1063
  -2.750  -0.1071   0.04029   0.03026  -0.0772   0.8743   0.1163
  -2.500  -0.0958   0.04012   0.03019  -0.0760   0.8686   0.1278
  -2.250  -0.0634   0.03870   0.02937  -0.0793   0.8633   0.1826
  -2.000  -0.0738   0.04044   0.03357  -0.0672   0.8588   0.6906
  -1.750  -0.0934   0.04241   0.03551  -0.0553   0.8540   0.7414
  -1.500  -0.1129   0.04351   0.03661  -0.0447   0.8499   0.7770
  -1.250   0.2403   0.04298   0.03432  -0.0819   0.8409   0.9988
  -1.000   0.2218   0.04406   0.03539  -0.0769   0.8329   1.0000
  -0.750   0.2348   0.04442   0.03561  -0.0764   0.8260   1.0000
  -0.500   0.2362   0.04511   0.03621  -0.0741   0.8197   1.0000
  -0.250   0.2180   0.04613   0.03722  -0.0692   0.8143   1.0000
   0.000   0.2196   0.04684   0.03786  -0.0671   0.8096   1.0000
   0.250   0.2404   0.04738   0.03823  -0.0676   0.8049   1.0000
   0.500   0.2110   0.04848   0.03937  -0.0612   0.8013   1.0000
   0.750   0.1960   0.04939   0.04026  -0.0569   0.7988   1.0000
   1.000   0.1839   0.05028   0.04112  -0.0531   0.7979   1.0000
   1.250   0.1716   0.05117   0.04199  -0.0494   0.7988   1.0000
   1.500   0.1612   0.05202   0.04282  -0.0460   0.8005   1.0000
   1.750   0.1528   0.05280   0.04357  -0.0428   0.8016   1.0000
   2.000   0.1471   0.05358   0.04431  -0.0400   0.8030   1.0000
   2.250   0.1468   0.05449   0.04518  -0.0381   0.8047   1.0000
   2.500  -0.0260   0.05224   0.04346  -0.0153   0.9454   1.0000
   2.750   0.0011   0.05419   0.04527  -0.0181   0.9401   1.0000
   3.000   0.0225   0.05504   0.04601  -0.0198   0.9289   1.0000
   3.250   0.0490   0.05687   0.04774  -0.0225   0.9218   1.0000
   3.500   0.0813   0.05880   0.04956  -0.0261   0.9095   1.0000
   3.750   0.0999   0.05984   0.05053  -0.0274   0.8992   1.0000
   4.000   0.1407   0.06305   0.05364  -0.0325   0.8911   1.0000
   4.250   0.1562   0.06367   0.05424  -0.0332   0.8785   1.0000
   4.500   0.1807   0.06556   0.05608  -0.0356   0.8683   1.0000
   4.750   0.2245   0.06908   0.05953  -0.0409   0.8569   1.0000
   5.000   0.2466   0.07036   0.06080  -0.0426   0.8417   1.0000
   5.250   0.2645   0.07166   0.06210  -0.0438   0.8277   1.0000
   5.500   0.2885   0.07393   0.06436  -0.0461   0.8184   1.0000
   5.750   0.3231   0.07675   0.06718  -0.0499   0.8068   1.0000
   6.000   0.3377   0.07810   0.06856  -0.0507   0.7932   1.0000
   6.250   0.3597   0.08032   0.07080  -0.0526   0.7812   1.0000
   6.500   0.4065   0.08459   0.07509  -0.0579   0.7702   1.0000
   6.750   0.4157   0.08545   0.07600  -0.0580   0.7554   1.0000
   7.000   0.4297   0.08729   0.07789  -0.0590   0.7424   1.0000
   7.250   0.4547   0.09018   0.08083  -0.0615   0.7318   1.0000
   7.500   0.4948   0.09392   0.08466  -0.0654   0.7184   1.0000
   7.750   0.5039   0.09530   0.08609  -0.0658   0.7032   1.0000
   8.000   0.5148   0.09737   0.08824  -0.0666   0.6904   1.0000
   8.250   0.5364   0.10031   0.09125  -0.0686   0.6788   1.0000
   8.500   0.5793   0.10462   0.09564  -0.0726   0.6659   1.0000
   8.750   0.5849   0.10604   0.09715  -0.0728   0.6510   1.0000
   9.000   0.5913   0.10826   0.09948  -0.0735   0.6384   1.0000
   9.250   0.6148   0.11184   0.10316  -0.0758   0.6288   1.0000
   9.500   0.6537   0.11601   0.10745  -0.0790   0.6142   1.0000
   9.750   0.6706   0.11845   0.11003  -0.0802   0.5973   1.0000
  10.250   0.7703   0.11547   0.10729  -0.0780   0.4945   1.0000
  10.500   0.7537   0.11987   0.11178  -0.0794   0.4916   1.0000
  10.750   0.7517   0.12392   0.11594  -0.0812   0.4883   1.0000
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