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FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il)
Reynolds number: 100,000
Max Cl/Cd: 47.35 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxs21158-il-100000-n5.txt
Download as CSV file: xf-fxs21158-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3717   0.09215   0.08777  -0.0472   1.0000   0.0314
 -10.500  -0.3840   0.08436   0.08003  -0.0518   1.0000   0.0314
 -10.250  -0.4001   0.07729   0.07299  -0.0564   1.0000   0.0313
 -10.000  -0.4192   0.07100   0.06670  -0.0607   1.0000   0.0312
  -9.750  -0.4380   0.06582   0.06151  -0.0640   1.0000   0.0310
  -9.250  -0.4498   0.05204   0.04677  -0.0845   0.8336   0.0323
  -8.750  -0.4312   0.04680   0.04101  -0.0867   0.7666   0.0351
  -8.500  -0.4256   0.04370   0.03748  -0.0872   0.7437   0.0357
  -8.250  -0.4153   0.04092   0.03424  -0.0873   0.7250   0.0365
  -8.000  -0.4009   0.03877   0.03166  -0.0874   0.7085   0.0385
  -7.750  -0.3843   0.03649   0.02885  -0.0874   0.6938   0.0398
  -7.500  -0.3650   0.03421   0.02612  -0.0873   0.6812   0.0402
  -7.250  -0.3433   0.03226   0.02375  -0.0871   0.6699   0.0407
  -7.000  -0.3197   0.03054   0.02166  -0.0869   0.6597   0.0412
  -6.750  -0.2952   0.02908   0.01989  -0.0867   0.6505   0.0417
  -6.500  -0.2701   0.02780   0.01835  -0.0864   0.6412   0.0423
  -6.250  -0.2452   0.02662   0.01697  -0.0861   0.6335   0.0436
  -6.000  -0.2210   0.02549   0.01581  -0.0859   0.6258   0.0455
  -5.750  -0.1962   0.02463   0.01482  -0.0855   0.6193   0.0470
  -5.500  -0.1716   0.02382   0.01393  -0.0849   0.6123   0.0478
  -5.250  -0.1473   0.02312   0.01313  -0.0843   0.6067   0.0489
  -5.000  -0.1230   0.02250   0.01246  -0.0838   0.6003   0.0502
  -4.750  -0.0984   0.02196   0.01180  -0.0835   0.5950   0.0518
  -4.500  -0.0730   0.02147   0.01115  -0.0833   0.5904   0.0539
  -4.250  -0.0474   0.02089   0.01046  -0.0834   0.5853   0.0569
  -4.000  -0.0209   0.02039   0.00979  -0.0837   0.5807   0.0627
  -3.750   0.0060   0.01977   0.00907  -0.0840   0.5764   0.0736
  -3.500   0.0323   0.01865   0.00828  -0.0850   0.5712   0.1508
  -3.250   0.0562   0.01796   0.00874  -0.0853   0.5668   0.4545
  -3.000   0.0828   0.01876   0.00941  -0.0844   0.5631   0.5018
  -2.750   0.1078   0.01949   0.01017  -0.0830   0.5587   0.5317
  -2.500   0.1350   0.01969   0.01022  -0.0826   0.5550   0.5438
  -2.250   0.1626   0.01973   0.01010  -0.0825   0.5517   0.5489
  -2.000   0.1913   0.01977   0.00987  -0.0829   0.5489   0.5564
  -1.750   0.2178   0.01988   0.00998  -0.0825   0.5451   0.5625
  -1.500   0.2460   0.01994   0.00989  -0.0827   0.5415   0.5702
  -1.250   0.2734   0.01998   0.00983  -0.0826   0.5384   0.5742
  -1.000   0.3015   0.02000   0.00972  -0.0828   0.5358   0.5773
  -0.750   0.3299   0.02003   0.00964  -0.0831   0.5332   0.5802
  -0.500   0.3581   0.02008   0.00962  -0.0835   0.5301   0.5835
  -0.250   0.3864   0.02014   0.00960  -0.0839   0.5272   0.5861
   0.000   0.4141   0.02021   0.00962  -0.0841   0.5247   0.5881
   0.250   0.4422   0.02028   0.00962  -0.0843   0.5224   0.5903
   0.500   0.4705   0.02038   0.00963  -0.0845   0.5205   0.5931
   0.750   0.4980   0.02053   0.00979  -0.0848   0.5178   0.5963
   1.000   0.5257   0.02070   0.00995  -0.0851   0.5151   0.5996
   1.250   0.5530   0.02086   0.01012  -0.0853   0.5126   0.6020
   1.500   0.5804   0.02101   0.01027  -0.0854   0.5102   0.6045
   1.750   0.6081   0.02115   0.01039  -0.0856   0.5080   0.6075
   2.000   0.6363   0.02131   0.01050  -0.0858   0.5061   0.6111
   2.250   0.6630   0.02158   0.01082  -0.0860   0.5034   0.6149
   2.500   0.6889   0.02185   0.01119  -0.0860   0.5008   0.6177
   2.750   0.7153   0.02211   0.01154  -0.0861   0.4985   0.6209
   3.000   0.7423   0.02238   0.01184  -0.0862   0.4964   0.6245
   3.250   0.7696   0.02264   0.01212  -0.0864   0.4945   0.6289
   3.500   0.7968   0.02288   0.01240  -0.0865   0.4929   0.6326
   3.750   0.8237   0.02315   0.01274  -0.0865   0.4910   0.6369
   4.000   0.8476   0.02361   0.01336  -0.0864   0.4873   0.6416
   4.250   0.8730   0.02393   0.01379  -0.0863   0.4839   0.6460
   4.500   0.8995   0.02419   0.01412  -0.0863   0.4813   0.6506
   4.750   0.9270   0.02443   0.01443  -0.0865   0.4791   0.6562
   5.000   0.9548   0.02467   0.01472  -0.0866   0.4774   0.6621
   5.250   0.9763   0.02530   0.01559  -0.0862   0.4740   0.6687
   5.500   0.9990   0.02587   0.01635  -0.0859   0.4709   0.6761
   5.750   1.0234   0.02629   0.01695  -0.0857   0.4681   0.6844
   6.000   1.0493   0.02657   0.01737  -0.0856   0.4657   0.6936
   6.250   1.0765   0.02680   0.01770  -0.0856   0.4637   0.7046
   6.500   1.0969   0.02739   0.01854  -0.0850   0.4600   0.7174
   6.750   1.1164   0.02778   0.01920  -0.0841   0.4544   0.7343
   7.000   1.1454   0.02724   0.01880  -0.0837   0.4496   0.7602
   7.250   1.1596   0.02746   0.01942  -0.0817   0.4426   0.8123
   7.500   1.1871   0.02680   0.01890  -0.0812   0.4360   1.0000
   7.750   1.2072   0.02719   0.01944  -0.0805   0.4295   1.0000
   8.000   1.2301   0.02742   0.01978  -0.0800   0.4241   1.0000
   8.250   1.2601   0.02715   0.01953  -0.0800   0.4200   1.0000
   8.500   1.2716   0.02807   0.02076  -0.0785   0.4128   1.0000
   8.750   1.3006   0.02747   0.02017  -0.0781   0.4054   1.0000
   9.000   1.3097   0.02804   0.02097  -0.0760   0.3935   1.0000
   9.250   1.3185   0.02859   0.02171  -0.0739   0.3804   1.0000
   9.500   1.3255   0.02926   0.02254  -0.0716   0.3668   1.0000
   9.750   1.3300   0.02984   0.02320  -0.0688   0.3520   1.0000
  10.000   1.3270   0.03115   0.02461  -0.0659   0.3388   1.0000
  10.250   1.3089   0.03399   0.02759  -0.0631   0.3250   1.0000
  10.500   1.2772   0.03916   0.03291  -0.0619   0.3178   1.0000
  10.750   1.2365   0.04662   0.04055  -0.0623   0.3171   1.0000
  11.000   1.2134   0.05218   0.04619  -0.0627   0.3040   1.0000
  11.250   1.2536   0.04800   0.04108  -0.0598   0.2215   1.0000
  11.500   1.2328   0.05298   0.04594  -0.0598   0.1903   1.0000
  11.750   1.2138   0.05789   0.05074  -0.0599   0.1756   1.0000
  12.000   1.1957   0.06283   0.05558  -0.0602   0.1450   1.0000
  12.250   1.1750   0.06822   0.06077  -0.0608   0.1297   1.0000
  12.500   1.1674   0.07230   0.06483  -0.0613   0.1033   1.0000
  12.750   1.1527   0.07739   0.06974  -0.0621   0.0886   1.0000
  13.000   1.1495   0.08115   0.07356  -0.0627   0.0677   1.0000
  13.250   1.1405   0.08576   0.07801  -0.0636   0.0559   1.0000
  13.500   1.1381   0.08955   0.08180  -0.0644   0.0460   1.0000
  13.750   1.1336   0.09369   0.08584  -0.0653   0.0348   1.0000
  14.000   1.1320   0.09751   0.08966  -0.0661   0.0289   1.0000
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