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DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DSMA-523A AIRFOIL (dsma523a-il)
Reynolds number: 50,000
Max Cl/Cd: 18.65 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dsma523a-il-50000-n5.txt
Download as CSV file: xf-dsma523a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DSMA-523A 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  -0.7266   0.08055   0.07168  -0.0475   1.0000   0.0718
 -10.250  -0.7524   0.07558   0.06663  -0.0480   1.0000   0.0715
 -10.000  -0.7788   0.07150   0.06246  -0.0472   1.0000   0.0713
  -9.750  -0.8004   0.06727   0.05808  -0.0469   1.0000   0.0712
  -9.500  -0.8152   0.06299   0.05356  -0.0470   1.0000   0.0712
  -9.250  -0.8238   0.05891   0.04914  -0.0469   1.0000   0.0713
  -9.000  -0.8266   0.05495   0.04476  -0.0468   1.0000   0.0718
  -8.750  -0.8142   0.05275   0.04255  -0.0461   1.0000   0.0730
  -8.500  -0.8021   0.05055   0.04024  -0.0455   1.0000   0.0745
  -8.250  -0.7902   0.04798   0.03741  -0.0452   1.0000   0.0762
  -8.000  -0.7765   0.04520   0.03426  -0.0450   1.0000   0.0779
  -7.750  -0.7600   0.04251   0.03113  -0.0447   1.0000   0.0793
  -7.500  -0.7409   0.04061   0.02914  -0.0440   1.0000   0.0806
  -7.250  -0.7212   0.03910   0.02757  -0.0433   1.0000   0.0829
  -7.000  -0.7007   0.03754   0.02582  -0.0426   1.0000   0.0860
  -6.750  -0.6796   0.03601   0.02409  -0.0417   1.0000   0.0889
  -6.500  -0.6588   0.03485   0.02295  -0.0406   1.0000   0.0915
  -6.250  -0.6375   0.03374   0.02176  -0.0392   1.0000   0.0949
  -6.000  -0.6161   0.03275   0.02062  -0.0377   1.0000   0.0993
  -5.750  -0.5958   0.03193   0.01989  -0.0361   1.0000   0.1037
  -5.500  -0.5751   0.03120   0.01907  -0.0341   1.0000   0.1087
  -5.250  -0.5550   0.03047   0.01838  -0.0323   1.0000   0.1143
  -5.000  -0.5347   0.02977   0.01769  -0.0308   1.0000   0.1213
  -4.750  -0.5144   0.02904   0.01702  -0.0294   1.0000   0.1292
  -4.500  -0.4934   0.02833   0.01635  -0.0283   1.0000   0.1398
  -4.250  -0.4720   0.02748   0.01568  -0.0276   1.0000   0.1540
  -4.000  -0.4493   0.02655   0.01493  -0.0274   1.0000   0.1756
  -3.750  -0.4242   0.02535   0.01415  -0.0281   1.0000   0.2181
  -3.500  -0.3966   0.02379   0.01342  -0.0300   1.0000   0.3176
  -3.250  -0.3886   0.02389   0.01454  -0.0242   1.0000   0.4383
  -3.000  -0.3919   0.02573   0.01683  -0.0129   1.0000   0.5135
  -2.500  -0.3320   0.02686   0.01761  -0.0144   1.0000   0.6513
  -2.000  -0.2890   0.02795   0.01848  -0.0108   1.0000   0.7012
  -1.750  -0.2720   0.02828   0.01876  -0.0078   1.0000   0.7193
  -1.500  -0.2568   0.02854   0.01899  -0.0043   1.0000   0.7375
  -1.250  -0.2441   0.02871   0.01915  -0.0002   1.0000   0.7563
  -1.000  -0.2328   0.02876   0.01920   0.0043   1.0000   0.7756
  -0.750  -0.2211   0.02868   0.01912   0.0084   1.0000   0.7941
  -0.500  -0.2057   0.02851   0.01895   0.0112   1.0000   0.8103
  -0.250  -0.1896   0.02823   0.01866   0.0137   1.0000   0.8223
   0.000  -0.1705   0.02794   0.01837   0.0152   1.0000   0.8315
   0.250  -0.1489   0.02772   0.01815   0.0159   1.0000   0.8394
   0.500  -0.1256   0.02754   0.01798   0.0161   1.0000   0.8452
   0.750  -0.1032   0.02733   0.01778   0.0165   1.0000   0.8493
   1.000  -0.0781   0.02722   0.01772   0.0161   1.0000   0.8527
   1.250  -0.0514   0.02720   0.01774   0.0153   1.0000   0.8556
   1.500  -0.0235   0.02726   0.01787   0.0142   1.0000   0.8579
   1.750   0.0035   0.02732   0.01802   0.0132   1.0000   0.8600
   2.000   0.0448   0.02760   0.01842   0.0098   0.9909   0.8616
   2.250   0.1040   0.02796   0.01894   0.0033   0.9705   0.8625
   2.500   0.1739   0.02731   0.01849  -0.0036   0.9263   0.8629
   2.750   0.2208   0.02589   0.01724  -0.0048   0.8543   0.8638
   3.000   0.2493   0.02505   0.01656  -0.0036   0.7807   0.8652
   3.250   0.3455   0.02523   0.01464  -0.0109   0.3528   0.8644
   3.500   0.3658   0.02651   0.01513  -0.0103   0.2337   0.8653
   3.750   0.3921   0.02748   0.01570  -0.0107   0.1837   0.8661
   4.000   0.4209   0.02830   0.01632  -0.0114   0.1599   0.8670
   4.250   0.4514   0.02905   0.01700  -0.0122   0.1439   0.8683
   4.500   0.4845   0.02988   0.01781  -0.0134   0.1328   0.8696
   4.750   0.5195   0.03074   0.01866  -0.0149   0.1235   0.8708
   5.000   0.5552   0.03174   0.01968  -0.0165   0.1157   0.8717
   5.250   0.5904   0.03283   0.02087  -0.0180   0.1099   0.8723
   5.500   0.6237   0.03408   0.02203  -0.0194   0.1049   0.8729
   5.750   0.6560   0.03541   0.02356  -0.0205   0.1000   0.8736
   6.000   0.6869   0.03685   0.02523  -0.0213   0.0960   0.8743
   6.250   0.7148   0.03833   0.02687  -0.0216   0.0932   0.8753
   6.500   0.7409   0.03984   0.02843  -0.0219   0.0902   0.8766
   6.750   0.7645   0.04168   0.03057  -0.0216   0.0874   0.8779
   7.000   0.7862   0.04369   0.03305  -0.0210   0.0847   0.8792
   7.250   0.8066   0.04603   0.03579  -0.0205   0.0832   0.8803
   7.500   0.8251   0.04847   0.03860  -0.0199   0.0816   0.8812
   7.750   0.8430   0.05077   0.04117  -0.0195   0.0797   0.8820
   8.000   0.8626   0.05283   0.04336  -0.0194   0.0777   0.8828
   8.250   0.8792   0.05549   0.04612  -0.0192   0.0761   0.8836
   8.500   0.8833   0.05903   0.05025  -0.0176   0.0752   0.8844
   8.750   0.8856   0.06287   0.05455  -0.0164   0.0748   0.8854
   9.000   0.8842   0.06694   0.05902  -0.0153   0.0746   0.8865
   9.250   0.8775   0.07133   0.06378  -0.0144   0.0745   0.8876
   9.500   0.8654   0.07584   0.06860  -0.0136   0.0746   0.8887
   9.750   0.8482   0.08043   0.07343  -0.0130   0.0748   0.8898
  10.000   0.8294   0.08588   0.07909  -0.0141   0.0750   0.8908
  10.250   0.8112   0.09204   0.08540  -0.0170   0.0753   0.8915
  10.500   0.7952   0.09904   0.09252  -0.0216   0.0756   0.8922
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