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S2048 (s2048-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 50,000
Max Cl/Cd: 37.24 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2048-il-50000.txt
Download as CSV file: xf-s2048-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2048                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4320   0.09582   0.08903  -0.0135   1.0000   0.2998
  -7.750  -0.4322   0.09323   0.08648  -0.0124   1.0000   0.3163
  -7.500  -0.4402   0.09133   0.08471  -0.0110   1.0000   0.3330
  -7.250  -0.4348   0.08813   0.08156  -0.0092   1.0000   0.3502
  -7.000  -0.4320   0.08577   0.07927  -0.0066   1.0000   0.3751
  -6.750  -0.4238   0.08297   0.07651  -0.0039   1.0000   0.4030
  -6.500  -0.4176   0.08034   0.07394  -0.0010   1.0000   0.4314
  -6.250  -0.4026   0.07681   0.07043   0.0010   1.0000   0.4557
  -5.250  -0.4562   0.04630   0.03847  -0.0417   1.0000   0.1352
  -5.000  -0.4384   0.04251   0.03441  -0.0414   1.0000   0.1322
  -4.750  -0.4178   0.03888   0.03024  -0.0414   1.0000   0.1287
  -4.500  -0.3923   0.03570   0.02603  -0.0413   1.0000   0.1225
  -4.250  -0.3687   0.03284   0.02281  -0.0407   1.0000   0.1215
  -4.000  -0.3437   0.03044   0.01995  -0.0399   1.0000   0.1220
  -3.750  -0.3195   0.02819   0.01751  -0.0391   1.0000   0.1261
  -3.500  -0.2950   0.02668   0.01568  -0.0381   1.0000   0.1370
  -3.250  -0.2710   0.02498   0.01397  -0.0369   1.0000   0.1488
  -3.000  -0.2470   0.02335   0.01235  -0.0353   1.0000   0.1672
  -2.750  -0.2232   0.02154   0.01089  -0.0344   1.0000   0.2252
  -2.250  -0.1441   0.01829   0.01040  -0.0275   1.0000   1.0000
  -2.000  -0.1485   0.01784   0.00976  -0.0239   1.0000   1.0000
  -1.750  -0.1388   0.01761   0.00919  -0.0224   1.0000   1.0000
  -1.500  -0.1209   0.01755   0.00879  -0.0220   1.0000   1.0000
  -1.250  -0.1000   0.01759   0.00850  -0.0220   1.0000   1.0000
  -1.000  -0.0781   0.01770   0.00832  -0.0219   1.0000   1.0000
  -0.750  -0.0559   0.01786   0.00822  -0.0219   1.0000   1.0000
  -0.500  -0.0337   0.01806   0.00815  -0.0218   1.0000   1.0000
  -0.250  -0.0115   0.01830   0.00819  -0.0217   1.0000   1.0000
   0.000   0.0105   0.01858   0.00829  -0.0216   1.0000   1.0000
   0.250   0.0323   0.01889   0.00845  -0.0214   1.0000   1.0000
   0.500   0.0538   0.01923   0.00865  -0.0213   1.0000   1.0000
   0.750   0.0751   0.01961   0.00892  -0.0211   1.0000   1.0000
   1.000   0.0961   0.02003   0.00925  -0.0210   1.0000   1.0000
   1.250   0.1168   0.02049   0.00964  -0.0208   1.0000   1.0000
   1.500   0.1372   0.02100   0.01010  -0.0207   1.0000   1.0000
   1.750   0.1572   0.02155   0.01061  -0.0206   1.0000   1.0000
   2.000   0.1767   0.02215   0.01120  -0.0205   1.0000   1.0000
   2.250   0.1958   0.02282   0.01187  -0.0204   1.0000   1.0000
   2.500   0.2142   0.02355   0.01262  -0.0204   1.0000   1.0000
   2.750   0.2321   0.02437   0.01348  -0.0205   1.0000   1.0000
   3.000   0.2769   0.02581   0.01503  -0.0258   0.9859   1.0000
   3.250   0.3477   0.02744   0.01684  -0.0352   0.9569   1.0000
   3.500   0.4097   0.02840   0.01805  -0.0422   0.9266   1.0000
   3.750   0.4672   0.02889   0.01881  -0.0476   0.8948   1.0000
   4.000   0.5310   0.02890   0.01919  -0.0531   0.8623   1.0000
   4.250   0.5933   0.02831   0.01900  -0.0573   0.8276   1.0000
   4.500   0.6654   0.02674   0.01790  -0.0613   0.7914   1.0000
   4.750   0.7259   0.02484   0.01646  -0.0622   0.7485   1.0000
   5.000   0.7716   0.02325   0.01511  -0.0607   0.6935   1.0000
   5.250   0.8050   0.02237   0.01420  -0.0578   0.6268   1.0000
   5.500   0.8308   0.02231   0.01393  -0.0546   0.5561   1.0000
   5.750   0.8517   0.02297   0.01423  -0.0517   0.4885   1.0000
   6.000   0.8708   0.02407   0.01492  -0.0491   0.4239   1.0000
   6.250   0.8870   0.02549   0.01604  -0.0465   0.3585   1.0000
   6.500   0.9024   0.02730   0.01745  -0.0439   0.2915   1.0000
   6.750   0.9204   0.02943   0.01925  -0.0418   0.2353   1.0000
   7.000   0.9419   0.03170   0.02141  -0.0403   0.1966   1.0000
   7.250   0.9627   0.03388   0.02359  -0.0389   0.1685   1.0000
   7.500   0.9857   0.03652   0.02637  -0.0377   0.1492   1.0000
   7.750   1.0075   0.03918   0.02893  -0.0367   0.1320   1.0000
   8.000   1.0246   0.04239   0.03275  -0.0347   0.1221   1.0000
   8.250   1.0378   0.04607   0.03691  -0.0328   0.1141   1.0000
   8.500   1.0551   0.04949   0.04032  -0.0317   0.1051   1.0000
   8.750   1.0588   0.05400   0.04555  -0.0290   0.1037   1.0000
   9.000   1.0577   0.05862   0.05076  -0.0265   0.1025   1.0000
   9.250   1.0515   0.06334   0.05596  -0.0242   0.1018   1.0000
   9.500   1.0406   0.06813   0.06113  -0.0221   0.1016   1.0000
   9.750   1.0264   0.07302   0.06631  -0.0205   0.1022   1.0000
  10.000   1.0098   0.07783   0.07131  -0.0192   0.1031   1.0000
  10.250   0.9933   0.08260   0.07618  -0.0183   0.1041   1.0000
  10.500   0.9799   0.08777   0.08142  -0.0183   0.1049   1.0000
  10.750   0.9701   0.09341   0.08713  -0.0190   0.1056   1.0000
  11.000   0.9249   0.10409   0.09786  -0.0258   0.1187   1.0000
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