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FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il)
Reynolds number: 500,000
Max Cl/Cd: 96.86 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxs21158-il-500000.txt
Download as CSV file: xf-fxs21158-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX S 02/1-158 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6796   0.06995   0.06752  -0.0487   1.0000   0.0047
 -13.250  -0.7176   0.05940   0.05674  -0.0560   1.0000   0.0046
 -13.000  -0.7284   0.05437   0.05160  -0.0593   1.0000   0.0046
 -12.750  -0.7438   0.04904   0.04610  -0.0626   1.0000   0.0046
 -12.500  -0.7533   0.04481   0.04173  -0.0651   1.0000   0.0045
 -12.250  -0.7775   0.03896   0.03562  -0.0681   1.0000   0.0046
 -12.000  -0.7800   0.03602   0.03255  -0.0693   1.0000   0.0046
 -11.750  -0.7925   0.03239   0.02872  -0.0702   1.0000   0.0047
 -11.500  -0.8008   0.02965   0.02583  -0.0704   1.0000   0.0047
 -11.250  -0.7975   0.02738   0.02338  -0.0708   1.0000   0.0048
 -11.000  -0.7909   0.02549   0.02133  -0.0701   1.0000   0.0051
 -10.750  -0.7593   0.02361   0.01928  -0.0735   0.9735   0.0055
 -10.500  -0.6931   0.02152   0.01692  -0.0837   0.9357   0.0060
 -10.250  -0.6348   0.01994   0.01495  -0.0917   0.8617   0.0072
 -10.000  -0.6108   0.02008   0.01493  -0.0912   0.7994   0.0085
  -9.750  -0.5901   0.01993   0.01456  -0.0903   0.7582   0.0099
  -9.500  -0.5652   0.02032   0.01484  -0.0899   0.7248   0.0113
  -9.250  -0.5390   0.02084   0.01524  -0.0897   0.6969   0.0133
  -9.000  -0.5131   0.02129   0.01552  -0.0895   0.6741   0.0149
  -8.750  -0.4916   0.02082   0.01488  -0.0892   0.6555   0.0165
  -8.500  -0.4670   0.02108   0.01509  -0.0892   0.6376   0.0178
  -8.250  -0.4417   0.02144   0.01537  -0.0892   0.6220   0.0193
  -8.000  -0.4169   0.02149   0.01530  -0.0891   0.6090   0.0208
  -7.750  -0.3903   0.02203   0.01572  -0.0891   0.5974   0.0222
  -7.500  -0.3683   0.02066   0.01410  -0.0888   0.5880   0.0233
  -7.250  -0.3456   0.01959   0.01295  -0.0887   0.5788   0.0251
  -7.000  -0.3204   0.01909   0.01236  -0.0886   0.5701   0.0261
  -6.750  -0.2954   0.01852   0.01166  -0.0885   0.5629   0.0270
  -6.500  -0.2697   0.01791   0.01095  -0.0883   0.5564   0.0279
  -6.250  -0.2443   0.01730   0.01023  -0.0881   0.5509   0.0288
  -6.000  -0.2182   0.01681   0.00965  -0.0879   0.5460   0.0298
  -5.750  -0.1903   0.01687   0.00960  -0.0880   0.5411   0.0314
  -5.500  -0.1649   0.01616   0.00878  -0.0878   0.5369   0.0323
  -5.250  -0.1403   0.01521   0.00775  -0.0875   0.5331   0.0327
  -5.000  -0.1146   0.01445   0.00695  -0.0873   0.5291   0.0332
  -4.750  -0.0883   0.01387   0.00630  -0.0873   0.5254   0.0338
  -4.500  -0.0616   0.01341   0.00575  -0.0874   0.5221   0.0343
  -4.250  -0.0343   0.01302   0.00527  -0.0875   0.5190   0.0348
  -4.000  -0.0063   0.01265   0.00485  -0.0877   0.5159   0.0357
  -3.750   0.0217   0.01235   0.00450  -0.0879   0.5128   0.0370
  -3.500   0.0498   0.01210   0.00416  -0.0880   0.5094   0.0383
  -3.250   0.0779   0.01193   0.00387  -0.0882   0.5059   0.0399
  -3.000   0.1065   0.01171   0.00360  -0.0883   0.5025   0.0425
  -2.750   0.1348   0.01118   0.00323  -0.0887   0.4992   0.0991
  -2.500   0.1604   0.00968   0.00277  -0.0897   0.4962   0.4127
  -2.250   0.1889   0.00978   0.00282  -0.0897   0.4932   0.4449
  -2.000   0.2176   0.00990   0.00288  -0.0898   0.4906   0.4592
  -1.750   0.2465   0.00998   0.00293  -0.0900   0.4881   0.4706
  -1.500   0.2753   0.01009   0.00300  -0.0901   0.4855   0.4812
  -1.250   0.3038   0.01016   0.00304  -0.0901   0.4828   0.4876
  -1.000   0.3324   0.01025   0.00306  -0.0902   0.4803   0.4925
  -0.750   0.3609   0.01041   0.00312  -0.0904   0.4775   0.4983
  -0.500   0.3893   0.01050   0.00325  -0.0904   0.4753   0.5070
  -0.250   0.4179   0.01056   0.00329  -0.0905   0.4726   0.5132
   0.000   0.4462   0.01057   0.00330  -0.0906   0.4691   0.5166
   0.250   0.4745   0.01062   0.00331  -0.0907   0.4660   0.5197
   0.500   0.5027   0.01075   0.00336  -0.0908   0.4626   0.5226
   0.750   0.5313   0.01074   0.00336  -0.0909   0.4599   0.5253
   1.000   0.5598   0.01073   0.00336  -0.0911   0.4567   0.5278
   1.250   0.5881   0.01074   0.00339  -0.0912   0.4541   0.5304
   1.500   0.6164   0.01078   0.00342  -0.0913   0.4518   0.5328
   1.750   0.6446   0.01086   0.00348  -0.0914   0.4497   0.5354
   2.000   0.6729   0.01095   0.00356  -0.0916   0.4477   0.5382
   2.250   0.7013   0.01098   0.00361  -0.0917   0.4456   0.5407
   2.500   0.7295   0.01095   0.00363  -0.0918   0.4421   0.5433
   2.750   0.7574   0.01093   0.00363  -0.0919   0.4378   0.5466
   3.000   0.7851   0.01099   0.00367  -0.0919   0.4336   0.5503
   3.250   0.8133   0.01101   0.00373  -0.0920   0.4301   0.5539
   3.500   0.8414   0.01105   0.00381  -0.0921   0.4273   0.5569
   3.750   0.8692   0.01107   0.00388  -0.0922   0.4247   0.5597
   4.000   0.8969   0.01114   0.00396  -0.0923   0.4222   0.5629
   4.250   0.9244   0.01124   0.00408  -0.0923   0.4196   0.5664
   4.500   0.9525   0.01130   0.00420  -0.0924   0.4171   0.5702
   4.750   0.9801   0.01133   0.00432  -0.0925   0.4143   0.5739
   5.000   1.0077   0.01139   0.00444  -0.0926   0.4113   0.5776
   5.250   1.0347   0.01147   0.00453  -0.0925   0.4071   0.5817
   5.750   1.0887   0.01150   0.00467  -0.0924   0.3871   0.5893
   6.000   1.1152   0.01156   0.00473  -0.0923   0.3703   0.5934
   6.250   1.1400   0.01177   0.00487  -0.0920   0.3508   0.5980
   6.500   1.1642   0.01205   0.00513  -0.0916   0.3304   0.6026
   6.750   1.1789   0.01313   0.00584  -0.0900   0.2556   0.6075
   7.000   1.1848   0.01495   0.00719  -0.0872   0.1720   0.6128
   7.250   1.1947   0.01626   0.00826  -0.0850   0.1166   0.6184
   7.500   1.2074   0.01724   0.00912  -0.0831   0.0849   0.6255
   7.750   1.2251   0.01780   0.00971  -0.0819   0.0620   0.6337
   8.000   1.2384   0.01858   0.01046  -0.0800   0.0509   0.6440
   8.250   1.2539   0.01914   0.01110  -0.0784   0.0380   0.6573
   8.750   1.2647   0.02072   0.01288  -0.0722   0.0247   0.7028
   9.000   1.2723   0.02113   0.01365  -0.0694   0.0222   0.7948
   9.250   1.2734   0.02230   0.01503  -0.0668   0.0096   1.0000
   9.500   1.2727   0.02389   0.01664  -0.0645   0.0065   1.0000
   9.750   1.2748   0.02560   0.01841  -0.0629   0.0059   1.0000
  10.000   1.2769   0.02757   0.02046  -0.0619   0.0055   1.0000
  10.250   1.2762   0.03005   0.02303  -0.0611   0.0049   1.0000
  10.500   1.2772   0.03255   0.02561  -0.0607   0.0047   1.0000
  10.750   1.2780   0.03514   0.02828  -0.0604   0.0046   1.0000
  11.000   1.2777   0.03789   0.03112  -0.0601   0.0045   1.0000
  11.250   1.2752   0.04091   0.03424  -0.0598   0.0042   1.0000
  11.500   1.2754   0.04366   0.03709  -0.0596   0.0043   1.0000
  11.750   1.2724   0.04679   0.04031  -0.0595   0.0041   1.0000
  12.000   1.2696   0.04991   0.04352  -0.0594   0.0040   1.0000
  12.250   1.2659   0.05318   0.04688  -0.0593   0.0039   1.0000
  12.500   1.2641   0.05627   0.05004  -0.0594   0.0039   1.0000
  12.750   1.2619   0.05955   0.05341  -0.0595   0.0038   1.0000
  13.000   1.2603   0.06284   0.05679  -0.0598   0.0038   1.0000
  13.250   1.2582   0.06628   0.06031  -0.0601   0.0037   1.0000
  13.500   1.2584   0.06950   0.06361  -0.0605   0.0037   1.0000
  13.750   1.2564   0.07307   0.06726  -0.0610   0.0037   1.0000
  14.000   1.2557   0.07652   0.07079  -0.0615   0.0037   1.0000
  14.250   1.2543   0.08014   0.07449  -0.0622   0.0036   1.0000
  14.500   1.2549   0.08353   0.07795  -0.0628   0.0037   1.0000
  14.750   1.2532   0.08728   0.08179  -0.0635   0.0036   1.0000
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