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S1223 (s1223-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 50,000
Max Cl/Cd: 42.3 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223-il-50000-n5.txt
Download as CSV file: xf-s1223-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.250  -0.0584   0.11731   0.11139  -0.0461   0.9503   0.0921
  -6.000  -0.0522   0.11606   0.11019  -0.0494   0.9358   0.0956
  -5.750  -0.0572   0.11654   0.11075  -0.0527   0.9183   0.0967
  -5.500  -0.0189   0.10881   0.10303  -0.0535   0.9117   0.0999
  -5.250  -0.0009   0.10560   0.09984  -0.0553   0.8989   0.1035
  -5.000   0.0071   0.10344   0.09772  -0.0564   0.8826   0.1071
  -4.750   0.0032   0.10309   0.09744  -0.0585   0.8612   0.1103
  -4.500   0.0129   0.10092   0.09534  -0.0629   0.8427   0.1115
  -4.250   0.0402   0.09527   0.08967  -0.0613   0.8344   0.1143
  -4.000   0.0561   0.09212   0.08653  -0.0619   0.8183   0.1180
  -3.750   0.0695   0.08961   0.08404  -0.0644   0.8007   0.1234
  -3.250   0.1040   0.08331   0.07774  -0.0709   0.7666   0.1289
  -3.000   0.1248   0.07994   0.07434  -0.0717   0.7512   0.1320
  -2.500   0.2103   0.06721   0.06122  -0.0959   0.7248   0.0719
  -2.000   0.3303   0.05482   0.04838  -0.1236   0.6949   0.0628
  -1.750   0.3927   0.04998   0.04329  -0.1346   0.6803   0.0612
  -1.500   0.6753   0.03305   0.02413  -0.2027   0.6594   0.0628
  -1.250   0.7522   0.03077   0.02118  -0.2134   0.6409   0.0663
  -1.000   0.8185   0.02945   0.01914  -0.2213   0.6240   0.0739
  -0.750   0.8728   0.02878   0.01803  -0.2265   0.6087   0.0824
  -0.500   0.9240   0.02838   0.01736  -0.2312   0.5946   0.0976
  -0.250   0.9815   0.02802   0.01703  -0.2374   0.5825   0.1449
   0.000   1.0242   0.02857   0.01774  -0.2402   0.5714   0.2877
   0.250   1.0544   0.02934   0.01854  -0.2402   0.5620   0.3631
   0.500   1.0896   0.02968   0.01865  -0.2414   0.5527   0.3969
   0.750   1.1271   0.02994   0.01863  -0.2431   0.5448   0.4189
   1.000   1.1608   0.03026   0.01879  -0.2443   0.5366   0.4373
   1.250   1.1982   0.03056   0.01886  -0.2460   0.5300   0.4579
   1.500   1.2315   0.03095   0.01913  -0.2471   0.5236   0.4781
   1.750   1.2623   0.03138   0.01951  -0.2477   0.5168   0.5010
   2.000   1.2961   0.03177   0.01980  -0.2488   0.5110   0.5292
   2.250   1.3280   0.03221   0.02019  -0.2496   0.5056   0.5608
   2.500   1.3538   0.03274   0.02084  -0.2492   0.4997   0.5980
   2.750   1.3811   0.03320   0.02139  -0.2491   0.4947   0.6465
   3.000   1.4073   0.03352   0.02178  -0.2485   0.4905   0.7171
   3.250   1.4206   0.03358   0.02198  -0.2453   0.4868   0.8638
   3.500   1.4447   0.03441   0.02281  -0.2450   0.4814   1.0000
   3.750   1.4729   0.03530   0.02358  -0.2454   0.4764   1.0000
   4.000   1.5029   0.03611   0.02425  -0.2460   0.4722   1.0000
   4.250   1.5355   0.03687   0.02482  -0.2470   0.4687   1.0000
   4.500   1.5556   0.03799   0.02604  -0.2460   0.4643   1.0000
   4.750   1.5758   0.03910   0.02721  -0.2449   0.4597   1.0000
   5.000   1.5992   0.04009   0.02820  -0.2444   0.4555   1.0000
   5.250   1.6259   0.04099   0.02903  -0.2443   0.4519   1.0000
   5.500   1.6559   0.04182   0.02979  -0.2448   0.4489   1.0000
   5.750   1.6669   0.04335   0.03153  -0.2423   0.4447   1.0000
   6.000   1.6794   0.04484   0.03318  -0.2402   0.4403   1.0000
   6.250   1.6972   0.04610   0.03451  -0.2388   0.4363   1.0000
   6.500   1.7201   0.04716   0.03558  -0.2382   0.4330   1.0000
   6.750   1.7486   0.04801   0.03643  -0.2384   0.4301   1.0000
   7.000   1.7518   0.05004   0.03870  -0.2350   0.4261   1.0000
   7.250   1.7487   0.05239   0.04131  -0.2307   0.4216   1.0000
   7.500   1.7554   0.05422   0.04330  -0.2279   0.4175   1.0000
   7.750   1.7735   0.05548   0.04462  -0.2267   0.4140   1.0000
   8.000   1.8040   0.05615   0.04530  -0.2271   0.4110   1.0000
   8.250   1.7699   0.06015   0.04966  -0.2191   0.4064   1.0000
   8.500   1.7174   0.06578   0.05567  -0.2101   0.4009   1.0000
   8.750   1.7083   0.06905   0.05909  -0.2065   0.3965   1.0000
   9.000   1.7381   0.06940   0.05945  -0.2065   0.3935   1.0000
   9.500   1.5208   0.10105   0.09186  -0.1979   0.3713   1.0000
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