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FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il)
Reynolds number: 50,000
Max Cl/Cd: 18.36 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxs21158-il-50000-n5.txt
Download as CSV file: xf-fxs21158-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3434   0.10352   0.09730  -0.0432   1.0000   0.0630
 -10.250  -0.3475   0.09848   0.09237  -0.0459   1.0000   0.0634
 -10.000  -0.3525   0.09319   0.08717  -0.0487   1.0000   0.0633
  -9.750  -0.3591   0.08759   0.08167  -0.0518   1.0000   0.0627
  -9.500  -0.3700   0.08187   0.07606  -0.0552   1.0000   0.0618
  -9.250  -0.3881   0.07612   0.07043  -0.0588   1.0000   0.0609
  -9.000  -0.4124   0.07126   0.06569  -0.0615   1.0000   0.0599
  -8.750  -0.4328   0.06571   0.06021  -0.0675   0.9652   0.0590
  -8.500  -0.4275   0.05890   0.05294  -0.0771   0.9145   0.0586
  -8.250  -0.4131   0.05343   0.04686  -0.0833   0.8799   0.0584
  -8.000  -0.3955   0.04917   0.04201  -0.0870   0.8508   0.0587
  -7.750  -0.3767   0.04577   0.03805  -0.0888   0.8259   0.0591
  -7.500  -0.3573   0.04299   0.03474  -0.0895   0.8042   0.0599
  -7.250  -0.3368   0.04080   0.03204  -0.0898   0.7857   0.0622
  -7.000  -0.3154   0.03887   0.02951  -0.0898   0.7695   0.0648
  -6.750  -0.2919   0.03716   0.02728  -0.0894   0.7548   0.0660
  -6.500  -0.2668   0.03545   0.02532  -0.0887   0.7416   0.0669
  -6.250  -0.2414   0.03406   0.02380  -0.0878   0.7296   0.0681
  -6.000  -0.2162   0.03300   0.02254  -0.0866   0.7188   0.0697
  -5.750  -0.1918   0.03214   0.02152  -0.0853   0.7089   0.0716
  -5.500  -0.1688   0.03140   0.02065  -0.0840   0.6993   0.0738
  -5.250  -0.1464   0.03072   0.01978  -0.0828   0.6916   0.0766
  -5.000  -0.1254   0.02998   0.01897  -0.0820   0.6836   0.0798
  -4.750  -0.1037   0.02921   0.01811  -0.0818   0.6769   0.0861
  -4.500  -0.0818   0.02839   0.01725  -0.0818   0.6695   0.0971
  -4.250  -0.0586   0.02732   0.01609  -0.0823   0.6637   0.1134
  -4.000  -0.0363   0.02542   0.01472  -0.0841   0.6567   0.1730
  -3.750  -0.0178   0.02617   0.01661  -0.0816   0.6511   0.4846
  -3.500   0.0014   0.02788   0.01828  -0.0777   0.6451   0.5427
  -3.250   0.0184   0.02920   0.01960  -0.0729   0.6397   0.5825
  -3.000   0.0414   0.02953   0.01968  -0.0709   0.6355   0.6024
  -2.750   0.0649   0.02964   0.01962  -0.0703   0.6296   0.6156
  -2.500   0.0890   0.02964   0.01943  -0.0694   0.6247   0.6240
  -2.250   0.1176   0.02943   0.01890  -0.0703   0.6205   0.6304
  -2.000   0.1422   0.02942   0.01875  -0.0702   0.6148   0.6344
  -1.750   0.1693   0.02934   0.01847  -0.0707   0.6104   0.6395
  -1.500   0.1986   0.02922   0.01808  -0.0717   0.6069   0.6448
  -1.250   0.2228   0.02933   0.01812  -0.0717   0.6019   0.6483
  -1.000   0.2492   0.02939   0.01804  -0.0722   0.5976   0.6520
  -0.750   0.2776   0.02941   0.01788  -0.0730   0.5942   0.6562
  -0.500   0.3054   0.02951   0.01782  -0.0737   0.5908   0.6602
  -0.250   0.3292   0.02980   0.01808  -0.0739   0.5862   0.6633
   0.000   0.3555   0.02999   0.01818  -0.0743   0.5824   0.6669
   0.250   0.3840   0.03013   0.01818  -0.0750   0.5793   0.6711
   0.500   0.4105   0.03043   0.01840  -0.0756   0.5761   0.6752
   0.750   0.4331   0.03096   0.01896  -0.0757   0.5722   0.6787
   1.000   0.4582   0.03139   0.01936  -0.0761   0.5689   0.6828
   1.250   0.4855   0.03176   0.01965  -0.0768   0.5662   0.6874
   1.500   0.5126   0.03203   0.01987  -0.0771   0.5639   0.6916
   1.750   0.5325   0.03286   0.02077  -0.0771   0.5598   0.6960
   2.000   0.5547   0.03360   0.02153  -0.0775   0.5559   0.7008
   2.250   0.5795   0.03410   0.02203  -0.0777   0.5528   0.7055
   2.500   0.6054   0.03452   0.02246  -0.0779   0.5505   0.7107
   2.750   0.6282   0.03532   0.02328  -0.0782   0.5478   0.7166
   3.000   0.6400   0.03686   0.02498  -0.0778   0.5434   0.7218
   3.250   0.6594   0.03784   0.02603  -0.0777   0.5398   0.7280
   3.500   0.6839   0.03844   0.02668  -0.0779   0.5371   0.7345
   3.750   0.7115   0.03875   0.02703  -0.0780   0.5349   0.7419
   4.000   0.7095   0.04133   0.02980  -0.0770   0.5282   0.7493
   4.250   0.7266   0.04238   0.03096  -0.0766   0.5243   0.7584
   4.500   0.7507   0.04291   0.03161  -0.0765   0.5217   0.7689
   4.750   0.7489   0.04546   0.03433  -0.0754   0.5160   0.7801
   5.000   0.7514   0.04765   0.03670  -0.0746   0.5110   0.7941
   5.250   0.7684   0.04869   0.03790  -0.0740   0.5083   0.8144
   5.500   0.7898   0.04933   0.03876  -0.0735   0.5063   0.8525
   5.750   0.7466   0.05509   0.04466  -0.0720   0.4967   1.0000
   6.000   0.7706   0.05631   0.04588  -0.0728   0.4937   1.0000
   6.250   0.8008   0.05702   0.04664  -0.0736   0.4918   1.0000
   6.500   0.7652   0.06292   0.05254  -0.0734   0.4830   1.0000
   6.750   0.7850   0.06441   0.05405  -0.0738   0.4798   1.0000
   7.000   0.8159   0.06493   0.05461  -0.0741   0.4774   1.0000
   7.250   0.7980   0.06897   0.05866  -0.0737   0.4675   1.0000
   7.500   0.8239   0.06983   0.05957  -0.0738   0.4642   1.0000
   7.750   0.8150   0.07348   0.06327  -0.0738   0.4573   1.0000
   8.000   0.8242   0.07579   0.06564  -0.0740   0.4527   1.0000
   8.250   0.8460   0.07710   0.06708  -0.0740   0.4497   1.0000
   8.500   0.8378   0.08072   0.07075  -0.0741   0.4424   1.0000
   8.750   0.8539   0.08231   0.07244  -0.0740   0.4373   1.0000
   9.000   0.8815   0.08295   0.07319  -0.0738   0.4338   1.0000
   9.250   0.8709   0.08660   0.07691  -0.0739   0.4241   1.0000
   9.500   0.9007   0.08691   0.07736  -0.0735   0.4204   1.0000
   9.750   0.8904   0.09062   0.08114  -0.0737   0.4104   1.0000
  10.000   0.9141   0.09157   0.08229  -0.0735   0.4065   1.0000
  10.500   0.9289   0.09617   0.08715  -0.0735   0.3924   1.0000
  10.750   0.9266   0.09921   0.09030  -0.0738   0.3825   1.0000
  11.000   0.9573   0.09883   0.09011  -0.0729   0.3772   1.0000
  11.250   0.9540   0.10186   0.09326  -0.0732   0.3661   1.0000
  11.750   0.9866   0.10359   0.09534  -0.0722   0.3497   1.0000
  12.000   0.9864   0.10623   0.09818  -0.0724   0.3379   1.0000
  12.250   0.9949   0.10747   0.09958  -0.0720   0.3259   1.0000
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