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S8038 (13%) (s8038-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8038 (13%) (s8038-il)
Reynolds number: 50,000
Max Cl/Cd: 29.24 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8038-il-50000.txt
Download as CSV file: xf-s8038-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8038 (13%)                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5624   0.09218   0.08497  -0.0334   1.0000   0.1337
 -10.000  -0.5875   0.08311   0.07596  -0.0391   1.0000   0.1250
  -9.750  -0.7009   0.07410   0.06679  -0.0430   1.0000   0.1163
  -9.500  -0.6972   0.06961   0.06231  -0.0422   1.0000   0.1147
  -9.250  -0.7087   0.06549   0.05810  -0.0406   1.0000   0.1132
  -9.000  -0.7221   0.06146   0.05391  -0.0384   1.0000   0.1116
  -8.750  -0.7344   0.05747   0.04966  -0.0358   1.0000   0.1101
  -8.500  -0.7418   0.05365   0.04552  -0.0331   1.0000   0.1091
  -8.250  -0.7435   0.05022   0.04176  -0.0303   1.0000   0.1092
  -8.000  -0.7410   0.04712   0.03829  -0.0276   1.0000   0.1107
  -7.750  -0.7360   0.04421   0.03497  -0.0249   1.0000   0.1129
  -7.500  -0.7284   0.04147   0.03173  -0.0221   1.0000   0.1152
  -7.250  -0.7140   0.03861   0.02865  -0.0202   1.0000   0.1187
  -7.000  -0.6955   0.03627   0.02623  -0.0185   1.0000   0.1242
  -6.750  -0.6789   0.03409   0.02374  -0.0164   1.0000   0.1323
  -6.500  -0.6607   0.03221   0.02172  -0.0145   1.0000   0.1453
  -6.250  -0.6413   0.03024   0.02004  -0.0129   1.0000   0.1653
  -6.000  -0.6257   0.02847   0.01849  -0.0106   1.0000   0.1959
  -5.750  -0.6142   0.02670   0.01711  -0.0077   1.0000   0.2422
  -5.500  -0.6074   0.02495   0.01589  -0.0039   1.0000   0.3110
  -5.250  -0.6028   0.02359   0.01528   0.0006   1.0000   0.3949
  -5.000  -0.5974   0.02312   0.01541   0.0057   1.0000   0.4796
  -4.750  -0.5891   0.02346   0.01607   0.0112   1.0000   0.5497
  -4.500  -0.5793   0.02403   0.01676   0.0166   1.0000   0.6061
  -4.250  -0.5675   0.02469   0.01747   0.0219   1.0000   0.6524
  -4.000  -0.5543   0.02534   0.01812   0.0271   1.0000   0.6931
  -3.750  -0.5412   0.02583   0.01855   0.0320   1.0000   0.7310
  -3.500  -0.5287   0.02611   0.01872   0.0365   1.0000   0.7672
  -3.250  -0.5051   0.02665   0.01914   0.0397   1.0000   0.8011
  -3.000  -0.4670   0.02732   0.01960   0.0402   1.0000   0.8353
  -2.750  -0.4007   0.02817   0.02012   0.0355   1.0000   0.8688
  -2.500  -0.3044   0.02883   0.02035   0.0245   1.0000   0.8991
  -2.250  -0.2300   0.02886   0.02009   0.0158   1.0000   0.9262
  -2.000  -0.1505   0.02858   0.01955   0.0054   1.0000   0.9502
  -1.750  -0.0861   0.02816   0.01894  -0.0032   1.0000   0.9724
  -1.500  -0.0160   0.02759   0.01821  -0.0134   1.0000   0.9938
  -1.250  -0.0018   0.02742   0.01799  -0.0144   1.0000   1.0000
  -1.000  -0.0154   0.02751   0.01810  -0.0106   1.0000   1.0000
  -0.750  -0.0285   0.02754   0.01812  -0.0070   1.0000   1.0000
  -0.500  -0.0415   0.02751   0.01807  -0.0035   1.0000   1.0000
  -0.250  -0.0548   0.02741   0.01795   0.0002   1.0000   1.0000
   0.000  -0.0686   0.02722   0.01774   0.0040   1.0000   1.0000
   0.250  -0.0382   0.02757   0.01805   0.0003   0.9896   1.0000
   0.500   0.0108   0.02817   0.01858  -0.0062   0.9733   1.0000
   0.750   0.0562   0.02868   0.01905  -0.0117   0.9569   1.0000
   1.000   0.0921   0.02907   0.01941  -0.0153   0.9398   1.0000
   1.250   0.1274   0.02948   0.01979  -0.0184   0.9227   1.0000
   1.500   0.1629   0.02991   0.02020  -0.0213   0.9055   1.0000
   1.750   0.1996   0.03033   0.02063  -0.0241   0.8880   1.0000
   2.000   0.2396   0.03074   0.02104  -0.0271   0.8703   1.0000
   2.250   0.2845   0.03107   0.02142  -0.0305   0.8526   1.0000
   2.500   0.3404   0.03121   0.02165  -0.0353   0.8349   1.0000
   2.750   0.3683   0.03152   0.02199  -0.0355   0.8149   1.0000
   3.000   0.4128   0.03153   0.02210  -0.0379   0.7943   1.0000
   3.250   0.4781   0.03081   0.02154  -0.0423   0.7734   1.0000
   3.500   0.5148   0.03052   0.02134  -0.0423   0.7510   1.0000
   3.750   0.5536   0.02998   0.02089  -0.0422   0.7277   1.0000
   4.000   0.5891   0.02941   0.02040  -0.0414   0.7038   1.0000
   4.250   0.6230   0.02874   0.01979  -0.0400   0.6787   1.0000
   4.500   0.6452   0.02849   0.01957  -0.0374   0.6520   1.0000
   4.750   0.6734   0.02792   0.01899  -0.0351   0.6239   1.0000
   5.000   0.6991   0.02742   0.01847  -0.0326   0.5933   1.0000
   5.250   0.7212   0.02707   0.01806  -0.0297   0.5600   1.0000
   5.500   0.7430   0.02680   0.01767  -0.0268   0.5244   1.0000
   5.750   0.7649   0.02661   0.01728  -0.0240   0.4870   1.0000
   6.000   0.7803   0.02694   0.01745  -0.0208   0.4489   1.0000
   6.250   0.7990   0.02733   0.01757  -0.0182   0.4130   1.0000
   6.500   0.8173   0.02804   0.01804  -0.0159   0.3806   1.0000
   6.750   0.8332   0.02901   0.01889  -0.0135   0.3519   1.0000
   7.000   0.8502   0.03022   0.02004  -0.0115   0.3279   1.0000
   7.250   0.8696   0.03141   0.02111  -0.0099   0.3066   1.0000
   7.500   0.8917   0.03272   0.02225  -0.0088   0.2882   1.0000
   7.750   0.9102   0.03432   0.02391  -0.0074   0.2736   1.0000
   8.000   0.9251   0.03603   0.02578  -0.0055   0.2605   1.0000
   8.250   0.9391   0.03785   0.02777  -0.0036   0.2485   1.0000
   8.500   0.9560   0.03987   0.02988  -0.0022   0.2391   1.0000
   8.750   0.9701   0.04196   0.03218  -0.0005   0.2306   1.0000
   9.000   0.9783   0.04441   0.03487   0.0016   0.2233   1.0000
   9.250   0.9908   0.04652   0.03712   0.0033   0.2153   1.0000
   9.500   0.9975   0.04943   0.04023   0.0053   0.2103   1.0000
   9.750   0.9856   0.05301   0.04425   0.0087   0.2075   1.0000
  10.000   0.9713   0.05676   0.04830   0.0118   0.2049   1.0000
  10.250   0.9538   0.06069   0.05246   0.0146   0.2028   1.0000
  10.500   0.9343   0.06467   0.05659   0.0171   0.2009   1.0000
  10.750   0.9142   0.06876   0.06076   0.0193   0.1993   1.0000
  11.000   0.8983   0.07339   0.06545   0.0202   0.1979   1.0000
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