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S1223 (s1223-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 100,000
Max Cl/Cd: 54.48 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1223-il-100000.txt
Download as CSV file: xf-s1223-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1223                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -5.500  -0.0105   0.10503   0.10101  -0.0547   0.9320   0.0686
  -5.250   0.0047   0.10263   0.09863  -0.0592   0.9191   0.0714
  -5.000   0.0103   0.10225   0.09828  -0.0688   0.9014   0.0727
  -4.750   0.0386   0.09558   0.09163  -0.0648   0.8932   0.0746
  -4.500   0.0702   0.09134   0.08739  -0.0687   0.8858   0.0781
  -4.250   0.0884   0.08839   0.08445  -0.0731   0.8701   0.0821
  -4.000   0.1103   0.08464   0.08072  -0.0818   0.8534   0.0847
  -3.750   0.1289   0.08072   0.07681  -0.0783   0.8397   0.0874
  -3.500   0.1542   0.07715   0.07323  -0.0813   0.8248   0.0922
  -3.250   0.1897   0.07260   0.06865  -0.0923   0.8082   0.0983
  -3.000   0.2240   0.06862   0.06461  -0.0931   0.7962   0.1062
  -2.750   0.2714   0.06377   0.05965  -0.1031   0.7789   0.1151
  -2.500   0.3355   0.05889   0.05459  -0.1188   0.7554   0.1284
  -2.250   0.4065   0.05411   0.04954  -0.1332   0.7308   0.1442
  -2.000   0.4772   0.04983   0.04493  -0.1458   0.7064   0.1612
  -1.750   0.8569   0.02451   0.01681  -0.2451   0.6665   0.0825
  -1.500   0.9316   0.02289   0.01425  -0.2551   0.6427   0.0838
  -1.250   0.9834   0.02207   0.01313  -0.2602   0.6248   0.0909
  -1.000   1.0275   0.02169   0.01241  -0.2632   0.6098   0.0976
  -0.750   1.0711   0.02145   0.01216  -0.2664   0.5966   0.1168
  -0.500   1.1236   0.02167   0.01264  -0.2712   0.5853   0.2859
  -0.250   1.1483   0.02246   0.01342  -0.2701   0.5751   0.3449
   0.000   1.1729   0.02337   0.01430  -0.2688   0.5671   0.4004
   0.250   1.1995   0.02372   0.01464  -0.2684   0.5583   0.4252
   0.500   1.2338   0.02405   0.01477  -0.2696   0.5509   0.4444
   0.750   1.2672   0.02443   0.01503  -0.2707   0.5445   0.4607
   1.000   1.2977   0.02476   0.01533  -0.2713   0.5378   0.4771
   1.250   1.3313   0.02513   0.01556  -0.2724   0.5317   0.4949
   1.500   1.3650   0.02561   0.01592  -0.2736   0.5263   0.5155
   1.750   1.3918   0.02601   0.01641  -0.2734   0.5204   0.5383
   2.000   1.4219   0.02644   0.01685  -0.2739   0.5153   0.5662
   2.250   1.4531   0.02690   0.01726  -0.2745   0.5109   0.6019
   2.500   1.4823   0.02744   0.01782  -0.2746   0.5068   0.6465
   2.750   1.5037   0.02784   0.01847  -0.2732   0.5020   0.7026
   3.000   1.5223   0.02811   0.01899  -0.2711   0.4976   0.7898
   3.250   1.5379   0.02823   0.01917  -0.2686   0.4939   1.0000
   3.500   1.5728   0.02903   0.01973  -0.2703   0.4902   1.0000
   3.750   1.6028   0.02996   0.02055  -0.2709   0.4867   1.0000
   4.000   1.6248   0.03079   0.02150  -0.2700   0.4825   1.0000
   4.250   1.6490   0.03161   0.02235  -0.2694   0.4781   1.0000
   4.500   1.6752   0.03240   0.02311  -0.2692   0.4743   1.0000
   4.750   1.7032   0.03323   0.02387  -0.2693   0.4711   1.0000
   5.000   1.7335   0.03427   0.02481  -0.2700   0.4681   1.0000
   5.250   1.7484   0.03535   0.02614  -0.2678   0.4642   1.0000
   5.500   1.7673   0.03642   0.02733  -0.2663   0.4601   1.0000
   5.750   1.7899   0.03739   0.02836  -0.2655   0.4564   1.0000
   6.000   1.8152   0.03826   0.02925  -0.2652   0.4529   1.0000
   6.250   1.8443   0.03914   0.03005  -0.2655   0.4496   1.0000
   6.500   1.8582   0.04061   0.03172  -0.2633   0.4459   1.0000
   6.750   1.8685   0.04213   0.03348  -0.2605   0.4416   1.0000
   7.000   1.8860   0.04332   0.03480  -0.2589   0.4375   1.0000
   7.250   1.9110   0.04411   0.03559  -0.2585   0.4337   1.0000
   7.500   1.9414   0.04485   0.03626  -0.2590   0.4304   1.0000
   7.750   1.9463   0.04684   0.03852  -0.2555   0.4263   1.0000
   8.000   1.9457   0.04896   0.04095  -0.2511   0.4215   1.0000
   8.250   1.9623   0.05011   0.04219  -0.2494   0.4171   1.0000
   8.500   1.9937   0.05041   0.04244  -0.2499   0.4132   1.0000
   8.750   2.0220   0.05130   0.04331  -0.2501   0.4095   1.0000
   9.000   1.9896   0.05513   0.04764  -0.2412   0.4042   1.0000
   9.250   1.9883   0.05721   0.04993  -0.2370   0.3993   1.0000
   9.500   2.0272   0.05688   0.04954  -0.2384   0.3952   1.0000
   9.750   2.0814   0.05612   0.04859  -0.2422   0.3914   1.0000
  10.000   1.9821   0.06371   0.05687  -0.2247   0.3865   1.0000
  10.500   1.9679   0.06835   0.06181  -0.2157   0.3771   1.0000
  10.750   2.0778   0.06333   0.05652  -0.2255   0.3721   1.0000
  11.500   1.8149   0.09405   0.08820  -0.1970   0.3552   1.0000
  11.750   1.4189   0.16839   0.16288  -0.2248   0.3114   1.0000
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