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FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il)
Reynolds number: 500,000
Max Cl/Cd: 87.22 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxs21158-il-500000-n5.txt
Download as CSV file: xf-fxs21158-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7333   0.05711   0.05431  -0.0588   1.0000   0.0024
 -13.000  -0.7567   0.05056   0.04757  -0.0630   1.0000   0.0023
 -12.750  -0.7744   0.04520   0.04202  -0.0661   1.0000   0.0023
 -12.500  -0.7815   0.04146   0.03814  -0.0681   1.0000   0.0023
 -12.250  -0.7323   0.03383   0.02994  -0.0871   0.9083   0.0025
 -12.000  -0.7056   0.03104   0.02651  -0.0935   0.7963   0.0025
 -11.750  -0.7072   0.02912   0.02428  -0.0928   0.7530   0.0026
 -11.500  -0.7095   0.02753   0.02243  -0.0916   0.7220   0.0026
 -11.250  -0.7025   0.02619   0.02086  -0.0908   0.6974   0.0026
 -11.000  -0.6917   0.02496   0.01937  -0.0900   0.6770   0.0027
 -10.750  -0.6776   0.02386   0.01808  -0.0893   0.6610   0.0028
 -10.500  -0.6611   0.02289   0.01694  -0.0887   0.6452   0.0028
 -10.250  -0.6440   0.02186   0.01573  -0.0881   0.6298   0.0031
 -10.000  -0.6259   0.02087   0.01456  -0.0876   0.6163   0.0034
  -9.750  -0.6062   0.02003   0.01356  -0.0871   0.6049   0.0036
  -9.500  -0.5856   0.01920   0.01260  -0.0867   0.5941   0.0040
  -9.250  -0.5638   0.01847   0.01178  -0.0864   0.5837   0.0046
  -9.000  -0.5389   0.01821   0.01155  -0.0864   0.5732   0.0066
  -8.750  -0.5126   0.01817   0.01148  -0.0864   0.5632   0.0103
  -8.500  -0.4869   0.01796   0.01118  -0.0863   0.5549   0.0122
  -8.250  -0.4612   0.01775   0.01086  -0.0862   0.5479   0.0137
  -8.000  -0.4349   0.01757   0.01060  -0.0862   0.5415   0.0146
  -7.750  -0.4070   0.01773   0.01067  -0.0863   0.5355   0.0153
  -7.500  -0.3836   0.01695   0.00981  -0.0862   0.5305   0.0165
  -7.250  -0.3580   0.01659   0.00938  -0.0862   0.5247   0.0173
  -7.000  -0.3324   0.01621   0.00892  -0.0861   0.5190   0.0179
  -6.750  -0.3063   0.01582   0.00846  -0.0861   0.5132   0.0184
  -6.500  -0.2803   0.01542   0.00798  -0.0861   0.5079   0.0189
  -6.250  -0.2539   0.01506   0.00754  -0.0861   0.5036   0.0195
  -6.000  -0.2271   0.01475   0.00717  -0.0862   0.4998   0.0204
  -5.750  -0.1997   0.01460   0.00695  -0.0863   0.4962   0.0216
  -5.500  -0.1725   0.01439   0.00667  -0.0863   0.4931   0.0223
  -5.250  -0.1456   0.01403   0.00623  -0.0864   0.4903   0.0224
  -5.000  -0.1184   0.01366   0.00580  -0.0865   0.4876   0.0226
  -4.750  -0.0913   0.01322   0.00528  -0.0866   0.4848   0.0229
  -4.500  -0.0639   0.01283   0.00480  -0.0868   0.4821   0.0234
  -4.250  -0.0362   0.01252   0.00439  -0.0870   0.4796   0.0242
  -4.000  -0.0084   0.01228   0.00408  -0.0871   0.4774   0.0250
  -3.750   0.0199   0.01206   0.00381  -0.0873   0.4753   0.0257
  -3.500   0.0482   0.01187   0.00358  -0.0875   0.4724   0.0265
  -3.250   0.0765   0.01172   0.00336  -0.0876   0.4692   0.0277
  -3.000   0.1048   0.01160   0.00318  -0.0877   0.4658   0.0296
  -2.750   0.1329   0.01148   0.00301  -0.0879   0.4630   0.0353
  -2.500   0.1614   0.01125   0.00285  -0.0881   0.4603   0.0608
  -2.250   0.1900   0.01112   0.00271  -0.0883   0.4575   0.0743
  -2.000   0.2184   0.01093   0.00258  -0.0886   0.4551   0.1091
  -1.750   0.2465   0.01052   0.00238  -0.0890   0.4526   0.1946
  -1.500   0.2733   0.00966   0.00220  -0.0897   0.4504   0.4068
  -1.250   0.3017   0.00969   0.00222  -0.0898   0.4481   0.4288
  -1.000   0.3306   0.00971   0.00222  -0.0900   0.4459   0.4383
  -0.750   0.3593   0.00973   0.00224  -0.0901   0.4433   0.4486
  -0.500   0.3879   0.00979   0.00230  -0.0902   0.4406   0.4626
  -0.250   0.4165   0.00984   0.00232  -0.0904   0.4375   0.4707
   0.000   0.4448   0.00990   0.00233  -0.0904   0.4337   0.4748
   0.250   0.4734   0.00992   0.00234  -0.0906   0.4300   0.4780
   0.500   0.5019   0.00996   0.00235  -0.0907   0.4258   0.4809
   0.750   0.5302   0.01002   0.00236  -0.0908   0.4224   0.4834
   1.000   0.5584   0.01007   0.00240  -0.0909   0.4191   0.4861
   1.250   0.5869   0.01011   0.00245  -0.0910   0.4165   0.4890
   1.500   0.6152   0.01016   0.00249  -0.0912   0.4135   0.4917
   1.750   0.6435   0.01022   0.00255  -0.0913   0.4107   0.4943
   2.000   0.6716   0.01029   0.00260  -0.0914   0.4083   0.4965
   2.250   0.6995   0.01037   0.00266  -0.0915   0.4058   0.4984
   2.500   0.7278   0.01041   0.00274  -0.0916   0.4018   0.5007
   2.750   0.7557   0.01047   0.00281  -0.0917   0.3948   0.5044
   3.000   0.7835   0.01055   0.00288  -0.0917   0.3874   0.5084
   3.250   0.8113   0.01063   0.00296  -0.0918   0.3793   0.5119
   3.500   0.8390   0.01071   0.00306  -0.0919   0.3739   0.5146
   3.750   0.8665   0.01080   0.00316  -0.0919   0.3665   0.5168
   4.000   0.8938   0.01091   0.00327  -0.0919   0.3602   0.5195
   4.250   0.9209   0.01103   0.00341  -0.0919   0.3534   0.5224
   4.500   0.9478   0.01118   0.00355  -0.0918   0.3474   0.5262
   4.750   0.9749   0.01130   0.00371  -0.0918   0.3410   0.5296
   5.000   1.0013   0.01148   0.00389  -0.0917   0.3332   0.5330
   5.250   1.0263   0.01177   0.00413  -0.0914   0.3065   0.5362
   5.500   1.0341   0.01367   0.00539  -0.0890   0.1874   0.5386
   5.750   1.0483   0.01489   0.00630  -0.0873   0.1261   0.5410
   6.000   1.0667   0.01566   0.00695  -0.0862   0.0902   0.5435
   6.250   1.0886   0.01610   0.00738  -0.0855   0.0788   0.5465
   6.500   1.1078   0.01673   0.00795  -0.0844   0.0556   0.5498
   6.750   1.1296   0.01713   0.00837  -0.0837   0.0485   0.5534
   7.000   1.1473   0.01778   0.00901  -0.0825   0.0304   0.5567
   7.250   1.1670   0.01823   0.00951  -0.0815   0.0274   0.5606
   7.500   1.1856   0.01873   0.01005  -0.0803   0.0232   0.5649
   7.750   1.2048   0.01915   0.01053  -0.0792   0.0211   0.5698
   8.000   1.2130   0.02007   0.01142  -0.0767   0.0047   0.5744
   8.250   1.2221   0.02070   0.01212  -0.0740   0.0040   0.5800
   8.750   1.2373   0.02225   0.01385  -0.0689   0.0030   0.5924
   9.000   1.2424   0.02327   0.01496  -0.0665   0.0027   0.5996
   9.250   1.2462   0.02450   0.01631  -0.0644   0.0026   0.6077
   9.500   1.2486   0.02603   0.01795  -0.0627   0.0024   0.6171
   9.750   1.2508   0.02781   0.01986  -0.0614   0.0024   0.6280
  10.000   1.2532   0.02979   0.02197  -0.0605   0.0023   0.6414
  10.250   1.2533   0.03215   0.02448  -0.0597   0.0022   0.6584
  10.500   1.2543   0.03452   0.02701  -0.0592   0.0022   0.6833
  10.750   1.2541   0.03696   0.02967  -0.0586   0.0021   0.7282
  11.250   1.2585   0.04260   0.03592  -0.0599   0.0019   1.0000
  11.500   1.2601   0.04522   0.03863  -0.0597   0.0020   1.0000
  11.750   1.2563   0.04843   0.04193  -0.0596   0.0019   1.0000
  12.000   1.2521   0.05171   0.04531  -0.0595   0.0018   1.0000
  12.250   1.2485   0.05498   0.04865  -0.0595   0.0018   1.0000
  12.500   1.2489   0.05789   0.05164  -0.0596   0.0018   1.0000
  12.750   1.2492   0.06092   0.05474  -0.0598   0.0017   1.0000
  13.000   1.2505   0.06388   0.05777  -0.0601   0.0017   1.0000
  13.250   1.2506   0.06706   0.06102  -0.0605   0.0017   1.0000
  13.500   1.2523   0.07008   0.06411  -0.0608   0.0017   1.0000
  13.750   1.2524   0.07340   0.06751  -0.0613   0.0016   1.0000
  14.000   1.2536   0.07659   0.07077  -0.0618   0.0016   1.0000
  14.250   1.2541   0.07996   0.07422  -0.0625   0.0016   1.0000
  14.500   1.2556   0.08323   0.07756  -0.0631   0.0016   1.0000
  14.750   1.2554   0.08680   0.08121  -0.0639   0.0015   1.0000
  15.000   1.2572   0.09011   0.08459  -0.0646   0.0015   1.0000
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