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S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1223 RTL (s1223rtl-il)
Reynolds number: 50,000
Max Cl/Cd: 35.91 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223rtl-il-50000-n5.txt
Download as CSV file: xf-s1223rtl-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -5.750  -0.0207   0.10861   0.10306  -0.0509   0.9100   0.1089
  -5.500  -0.0230   0.10773   0.10226  -0.0525   0.8952   0.1122
  -5.250  -0.0300   0.10744   0.10205  -0.0558   0.8791   0.1134
  -5.000  -0.0007   0.10124   0.09588  -0.0552   0.8688   0.1154
  -4.750   0.0187   0.09739   0.09205  -0.0554   0.8538   0.1186
  -4.500   0.0279   0.09475   0.08946  -0.0557   0.8354   0.1223
  -4.250   0.0246   0.09378   0.08857  -0.0586   0.8103   0.1280
  -4.000   0.0342   0.09060   0.08547  -0.0608   0.7859   0.1298
  -3.500   0.0561   0.08456   0.07949  -0.0560   0.7193   0.1386
  -3.000   0.1330   0.06985   0.06427  -0.0792   0.6468   0.0739
  -2.750   0.2049   0.06123   0.05506  -0.0957   0.6038   0.0646
  -2.500   0.2649   0.05558   0.04880  -0.1076   0.5661   0.0621
  -2.250   0.3721   0.04594   0.03829  -0.1357   0.5363   0.0623
  -2.000   0.5723   0.03436   0.02429  -0.1833   0.5050   0.0657
  -1.750   0.6228   0.03322   0.02273  -0.1888   0.4911   0.0713
  -1.500   0.6830   0.03189   0.02062  -0.1957   0.4794   0.0766
  -1.250   0.7318   0.03125   0.01960  -0.2000   0.4692   0.0858
  -1.000   0.7860   0.03078   0.01875  -0.2053   0.4610   0.0990
  -0.750   0.8387   0.03041   0.01834  -0.2105   0.4527   0.1230
  -0.500   0.8964   0.03019   0.01832  -0.2168   0.4447   0.2107
  -0.250   0.9382   0.03086   0.01901  -0.2191   0.4386   0.3260
   0.000   0.9671   0.03161   0.01984  -0.2187   0.4327   0.3871
   0.250   0.9994   0.03216   0.02028  -0.2190   0.4275   0.4273
   0.500   1.0394   0.03257   0.02035  -0.2213   0.4228   0.4547
   0.750   1.0769   0.03299   0.02051  -0.2230   0.4185   0.4759
   1.000   1.1084   0.03339   0.02083  -0.2237   0.4137   0.4947
   1.250   1.1404   0.03382   0.02115  -0.2246   0.4090   0.5137
   1.500   1.1732   0.03429   0.02146  -0.2255   0.4048   0.5333
   1.750   1.2071   0.03480   0.02178  -0.2266   0.4012   0.5542
   2.000   1.2380   0.03537   0.02227  -0.2273   0.3980   0.5754
   2.250   1.2648   0.03597   0.02292  -0.2272   0.3944   0.5976
   2.500   1.2924   0.03659   0.02356  -0.2273   0.3907   0.6216
   2.750   1.3190   0.03717   0.02416  -0.2272   0.3873   0.6470
   3.000   1.3467   0.03776   0.02472  -0.2272   0.3840   0.6767
   3.250   1.3746   0.03833   0.02525  -0.2273   0.3812   0.7120
   3.500   1.3972   0.03891   0.02594  -0.2263   0.3785   0.7561
   3.750   1.4066   0.03930   0.02666  -0.2228   0.3758   0.8554
   4.250   1.4587   0.04149   0.02881  -0.2233   0.3697   1.0000
   4.500   1.4846   0.04257   0.02985  -0.2234   0.3667   1.0000
   4.750   1.5110   0.04361   0.03078  -0.2235   0.3640   1.0000
   5.000   1.5386   0.04463   0.03166  -0.2237   0.3615   1.0000
   5.250   1.5618   0.04586   0.03285  -0.2233   0.3591   1.0000
   5.500   1.5739   0.04744   0.03467  -0.2212   0.3564   1.0000
   5.750   1.5870   0.04906   0.03645  -0.2193   0.3538   1.0000
   6.000   1.6007   0.05067   0.03819  -0.2175   0.3513   1.0000
   6.250   1.6149   0.05224   0.03985  -0.2158   0.3487   1.0000
   6.500   1.6307   0.05371   0.04138  -0.2144   0.3463   1.0000
   6.750   1.6494   0.05506   0.04278  -0.2133   0.3441   1.0000
   7.000   1.6719   0.05631   0.04399  -0.2128   0.3420   1.0000
   7.250   1.6835   0.05815   0.04592  -0.2109   0.3400   1.0000
   7.500   1.6649   0.06143   0.04960  -0.2052   0.3375   1.0000
   7.750   1.6391   0.06510   0.05363  -0.1989   0.3352   1.0000
   8.000   1.6025   0.06959   0.05846  -0.1920   0.3327   1.0000
   8.250   1.5566   0.07546   0.06468  -0.1857   0.3298   1.0000
   8.500   1.5188   0.08167   0.07114  -0.1817   0.3269   1.0000
   8.750   1.5195   0.08482   0.07434  -0.1803   0.3246   1.0000
   9.000   1.5355   0.08658   0.07610  -0.1796   0.3229   1.0000
   9.500   1.2940   0.13106   0.12153  -0.1899   0.3054   1.0000
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