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S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1223 RTL (s1223rtl-il)
Reynolds number: 100,000
Max Cl/Cd: 43.28 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1223rtl-il-100000.txt
Download as CSV file: xf-s1223rtl-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1223 RTL                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.250  -0.0573   0.11230   0.10845  -0.0444   0.9532   0.0711
  -6.000  -0.0453   0.10994   0.10611  -0.0491   0.9428   0.0742
  -5.750  -0.0544   0.11023   0.10645  -0.0537   0.9304   0.0751
  -5.500  -0.0061   0.10209   0.09832  -0.0556   0.9216   0.0774
  -5.250   0.0200   0.09812   0.09437  -0.0586   0.9102   0.0822
  -5.000   0.0214   0.09666   0.09295  -0.0619   0.8955   0.0854
  -4.750   0.0520   0.09111   0.08743  -0.0656   0.8842   0.0888
  -4.500   0.0818   0.08673   0.08307  -0.0682   0.8687   0.0942
  -4.250   0.0942   0.08430   0.08068  -0.0819   0.8432   0.0994
  -4.000   0.1156   0.07879   0.07519  -0.0744   0.8208   0.1019
  -3.750   0.1352   0.07518   0.07155  -0.0736   0.7733   0.1063
  -3.500   0.2180   0.06700   0.06274  -0.0908   0.6658   0.1179
  -3.250   0.2809   0.06232   0.05716  -0.1070   0.5814   0.1309
  -3.000   0.3085   0.06017   0.05462  -0.1068   0.5514   0.1373
  -2.750   0.3501   0.05694   0.05111  -0.1164   0.5332   0.1492
  -2.500   0.3974   0.05410   0.04797  -0.1254   0.5188   0.1658
  -2.250   0.7359   0.02786   0.01884  -0.2219   0.4922   0.0855
  -2.000   0.8060   0.02608   0.01630  -0.2314   0.4820   0.0885
  -1.750   0.8525   0.02527   0.01523  -0.2352   0.4742   0.0928
  -1.500   0.8968   0.02475   0.01446  -0.2385   0.4667   0.1025
  -1.250   0.9428   0.02457   0.01407  -0.2421   0.4601   0.1175
  -1.000   0.9825   0.02427   0.01393  -0.2445   0.4538   0.1507
  -0.750   1.0250   0.02466   0.01478  -0.2472   0.4477   0.3299
  -0.500   1.0531   0.02561   0.01561  -0.2467   0.4432   0.3821
  -0.250   1.0806   0.02656   0.01651  -0.2461   0.4392   0.4206
   0.000   1.1027   0.02711   0.01717  -0.2443   0.4353   0.4501
   0.250   1.1313   0.02756   0.01757  -0.2443   0.4308   0.4753
   0.500   1.1620   0.02797   0.01787  -0.2448   0.4264   0.4940
   0.750   1.1952   0.02849   0.01821  -0.2458   0.4224   0.5124
   1.000   1.2275   0.02914   0.01875  -0.2468   0.4189   0.5300
   1.250   1.2549   0.02953   0.01922  -0.2467   0.4156   0.5473
   1.500   1.2837   0.03001   0.01972  -0.2469   0.4122   0.5654
   1.750   1.3129   0.03053   0.02024  -0.2472   0.4088   0.5857
   2.000   1.3416   0.03106   0.02075  -0.2474   0.4055   0.6060
   2.250   1.3716   0.03169   0.02131  -0.2479   0.4023   0.6279
   2.500   1.4018   0.03263   0.02219  -0.2485   0.3993   0.6528
   2.750   1.4247   0.03317   0.02288  -0.2476   0.3964   0.6772
   3.000   1.4476   0.03380   0.02367  -0.2467   0.3937   0.7034
   3.250   1.4711   0.03448   0.02446  -0.2460   0.3909   0.7345
   3.500   1.4939   0.03511   0.02521  -0.2451   0.3884   0.7726
   4.000   1.5348   0.03618   0.02646  -0.2425   0.3835   1.0000
   4.250   1.5682   0.03748   0.02755  -0.2441   0.3808   1.0000
   4.500   1.5914   0.03884   0.02895  -0.2438   0.3783   1.0000
   4.750   1.6100   0.04007   0.03033  -0.2424   0.3758   1.0000
   5.000   1.6285   0.04143   0.03184  -0.2411   0.3734   1.0000
   5.250   1.6471   0.04283   0.03334  -0.2399   0.3711   1.0000
   5.500   1.6662   0.04421   0.03479  -0.2387   0.3688   1.0000
   5.750   1.6874   0.04545   0.03605  -0.2379   0.3664   1.0000
   6.000   1.7119   0.04657   0.03712  -0.2375   0.3641   1.0000
   6.250   1.7369   0.04786   0.03837  -0.2374   0.3619   1.0000
   6.500   1.7588   0.04992   0.04041  -0.2370   0.3599   1.0000
   6.750   1.7588   0.05212   0.04297  -0.2329   0.3581   1.0000
   7.000   1.7568   0.05475   0.04592  -0.2288   0.3562   1.0000
   7.250   1.7510   0.05776   0.04922  -0.2245   0.3543   1.0000
   7.500   1.7399   0.06107   0.05284  -0.2196   0.3522   1.0000
   7.750   1.7237   0.06464   0.05666  -0.2143   0.3500   1.0000
   8.000   1.6942   0.06885   0.06113  -0.2076   0.3482   1.0000
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