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S8036 (16%) (s8036-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S8036 (16%) (s8036-il)
Reynolds number: 100,000
Max Cl/Cd: 48.25 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8036-il-100000.txt
Download as CSV file: xf-s8036-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8036 (16%)                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4006   0.11883   0.11361  -0.0394   1.0000   0.1349
 -11.500  -0.3906   0.09127   0.08653  -0.0574   1.0000   0.0902
 -11.250  -0.5034   0.08591   0.08083  -0.0607   1.0000   0.0798
 -11.000  -0.4598   0.09273   0.08770  -0.0529   1.0000   0.0936
 -10.750  -0.6642   0.06884   0.06326  -0.0642   1.0000   0.0677
 -10.500  -0.6467   0.06479   0.05926  -0.0640   1.0000   0.0653
 -10.250  -0.6677   0.06215   0.05657  -0.0602   1.0000   0.0644
 -10.000  -0.6952   0.05989   0.05425  -0.0545   1.0000   0.0636
  -9.750  -0.7216   0.05732   0.05156  -0.0489   1.0000   0.0622
  -9.500  -0.7545   0.05487   0.04890  -0.0419   1.0000   0.0607
  -9.250  -0.8164   0.05352   0.04686  -0.0298   1.0000   0.0581
  -9.000  -0.8253   0.05167   0.04488  -0.0254   1.0000   0.0577
  -8.750  -0.8332   0.04945   0.04251  -0.0211   1.0000   0.0574
  -8.500  -0.8391   0.04734   0.04021  -0.0170   1.0000   0.0572
  -8.250  -0.8337   0.04479   0.03734  -0.0148   0.9980   0.0570
  -8.000  -0.8093   0.04170   0.03360  -0.0157   0.9903   0.0577
  -7.750  -0.7772   0.03879   0.03061  -0.0180   0.9846   0.0600
  -7.500  -0.7467   0.03694   0.02860  -0.0194   0.9775   0.0630
  -7.250  -0.7111   0.03467   0.02590  -0.0212   0.9721   0.0654
  -7.000  -0.6807   0.03257   0.02360  -0.0220   0.9649   0.0690
  -6.750  -0.6406   0.03120   0.02212  -0.0248   0.9599   0.0763
  -6.500  -0.6123   0.02967   0.02065  -0.0253   0.9522   0.0829
  -6.250  -0.5737   0.02822   0.01923  -0.0277   0.9473   0.0946
  -6.000  -0.5487   0.02709   0.01818  -0.0276   0.9391   0.1081
  -5.750  -0.5151   0.02588   0.01701  -0.0290   0.9332   0.1309
  -5.500  -0.4975   0.02475   0.01617  -0.0278   0.9249   0.1583
  -5.250  -0.4759   0.02332   0.01518  -0.0272   0.9180   0.2115
  -5.000  -0.4715   0.02192   0.01454  -0.0237   0.9089   0.3070
  -4.750  -0.4631   0.02079   0.01449  -0.0200   0.9014   0.4854
  -4.500  -0.4492   0.02097   0.01490  -0.0166   0.8932   0.5750
  -4.250  -0.4268   0.02130   0.01522  -0.0148   0.8858   0.6291
  -4.000  -0.3861   0.02171   0.01559  -0.0157   0.8821   0.6711
  -3.750  -0.3783   0.02218   0.01603  -0.0115   0.8720   0.6945
  -3.500  -0.3407   0.02254   0.01631  -0.0121   0.8673   0.7224
  -3.250  -0.2917   0.02291   0.01659  -0.0144   0.8647   0.7488
  -3.000  -0.2891   0.02340   0.01706  -0.0095   0.8541   0.7653
  -2.750  -0.2473   0.02366   0.01722  -0.0108   0.8501   0.7871
  -2.500  -0.1913   0.02400   0.01744  -0.0145   0.8478   0.8073
  -2.250  -0.1858   0.02453   0.01795  -0.0101   0.8380   0.8231
  -2.000  -0.1161   0.02503   0.01832  -0.0165   0.8353   0.8357
  -1.750  -0.0543   0.02511   0.01826  -0.0221   0.8325   0.8460
  -1.500   0.0179   0.02514   0.01813  -0.0297   0.8303   0.8531
  -1.250   0.0288   0.02550   0.01847  -0.0271   0.8205   0.8641
  -1.000   0.0937   0.02548   0.01833  -0.0337   0.8167   0.8700
  -0.750   0.1414   0.02521   0.01795  -0.0373   0.8128   0.8784
  -0.500   0.1895   0.02555   0.01825  -0.0415   0.8053   0.8836
  -0.250   0.2126   0.02548   0.01812  -0.0409   0.7983   0.8945
   0.000   0.2844   0.02519   0.01774  -0.0488   0.7949   0.8974
   0.250   0.3097   0.02560   0.01816  -0.0491   0.7853   0.9059
   0.500   0.3483   0.02539   0.01789  -0.0512   0.7795   0.9133
   0.750   0.3921   0.02547   0.01796  -0.0546   0.7725   0.9193
   1.000   0.4137   0.02556   0.01804  -0.0540   0.7642   0.9288
   1.250   0.4721   0.02514   0.01757  -0.0595   0.7595   0.9327
   1.500   0.4860   0.02562   0.01809  -0.0580   0.7486   0.9431
   1.750   0.5403   0.02516   0.01759  -0.0627   0.7429   0.9476
   2.000   0.5639   0.02548   0.01797  -0.0629   0.7323   0.9569
   2.250   0.6135   0.02499   0.01745  -0.0668   0.7258   0.9620
   2.500   0.6397   0.02523   0.01775  -0.0673   0.7150   0.9712
   2.750   0.6915   0.02458   0.01706  -0.0716   0.7078   0.9761
   3.000   0.7230   0.02462   0.01718  -0.0730   0.6960   0.9845
   3.250   0.7679   0.02409   0.01663  -0.0762   0.6866   0.9910
   3.500   0.8106   0.02354   0.01610  -0.0792   0.6751   0.9978
   3.750   0.8293   0.02346   0.01607  -0.0781   0.6632   1.0000
   4.000   0.8531   0.02295   0.01550  -0.0770   0.6544   1.0000
   4.250   0.8596   0.02302   0.01563  -0.0737   0.6423   1.0000
   4.500   0.8703   0.02294   0.01558  -0.0708   0.6313   1.0000
   4.750   0.8940   0.02239   0.01497  -0.0697   0.6219   1.0000
   5.000   0.8975   0.02247   0.01511  -0.0657   0.6093   1.0000
   5.250   0.9082   0.02232   0.01499  -0.0626   0.5977   1.0000
   5.500   0.9300   0.02184   0.01445  -0.0611   0.5868   1.0000
   5.750   0.9388   0.02172   0.01434  -0.0575   0.5736   1.0000
   6.000   0.9473   0.02164   0.01429  -0.0539   0.5597   1.0000
   6.250   0.9593   0.02149   0.01413  -0.0508   0.5454   1.0000
   6.500   0.9724   0.02131   0.01394  -0.0477   0.5299   1.0000
   6.750   0.9850   0.02118   0.01378  -0.0446   0.5130   1.0000
   7.000   0.9974   0.02108   0.01365  -0.0414   0.4947   1.0000
   7.250   1.0101   0.02103   0.01353  -0.0383   0.4751   1.0000
   7.500   1.0190   0.02112   0.01355  -0.0345   0.4534   1.0000
   7.750   1.0248   0.02136   0.01371  -0.0304   0.4297   1.0000
   8.000   1.0316   0.02166   0.01387  -0.0264   0.4053   1.0000
   8.250   1.0346   0.02213   0.01422  -0.0219   0.3802   1.0000
   8.500   1.0379   0.02272   0.01462  -0.0176   0.3559   1.0000
   8.750   1.0391   0.02344   0.01519  -0.0131   0.3328   1.0000
   9.000   1.0412   0.02419   0.01573  -0.0089   0.3125   1.0000
   9.250   1.0440   0.02502   0.01640  -0.0049   0.2936   1.0000
   9.500   1.0481   0.02591   0.01717  -0.0012   0.2762   1.0000
   9.750   1.0549   0.02685   0.01799   0.0018   0.2604   1.0000
  10.000   1.0658   0.02785   0.01884   0.0041   0.2460   1.0000
  10.250   1.0751   0.02883   0.01978   0.0065   0.2331   1.0000
  10.500   1.0844   0.02988   0.02085   0.0089   0.2213   1.0000
  10.750   1.0984   0.03099   0.02190   0.0104   0.2108   1.0000
  11.000   1.1227   0.03212   0.02283   0.0105   0.2003   1.0000
  11.250   1.1262   0.03324   0.02415   0.0135   0.1927   1.0000
  11.500   1.1507   0.03445   0.02522   0.0135   0.1839   1.0000
  11.750   1.1554   0.03566   0.02662   0.0161   0.1775   1.0000
  12.000   1.1869   0.03697   0.02774   0.0152   0.1695   1.0000
  12.250   1.1850   0.03829   0.02934   0.0185   0.1647   1.0000
  12.500   1.1990   0.03952   0.03061   0.0197   0.1590   1.0000
  12.750   1.2199   0.04111   0.03220   0.0200   0.1532   1.0000
  13.000   1.2179   0.04267   0.03400   0.0228   0.1492   1.0000
  13.250   1.2285   0.04404   0.03542   0.0242   0.1444   1.0000
  13.500   1.2507   0.04584   0.03721   0.0242   0.1396   1.0000
  13.750   1.2410   0.04781   0.03947   0.0273   0.1368   1.0000
  14.000   1.2379   0.04980   0.04167   0.0294   0.1336   1.0000
  14.250   1.2454   0.05152   0.04346   0.0307   0.1301   1.0000
  14.500   1.2647   0.05366   0.04557   0.0308   0.1260   1.0000
  14.750   1.2444   0.05646   0.04869   0.0335   0.1247   1.0000
  15.000   1.2234   0.05972   0.05224   0.0356   0.1231   1.0000
  15.250   1.2029   0.06331   0.05609   0.0370   0.1215   1.0000
  15.500   1.1815   0.06736   0.06038   0.0379   0.1202   1.0000
  15.750   1.1577   0.07193   0.06516   0.0382   0.1190   1.0000
  16.000   1.1097   0.07922   0.07275   0.0373   0.1193   1.0000
  16.250   0.9777   0.09941   0.09335   0.0292   0.1239   1.0000
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