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S8055 (12%) (s8055-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8055 (12%) (s8055-il)
Reynolds number: 50,000
Max Cl/Cd: 32.17 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8055-il-50000.txt
Download as CSV file: xf-s8055-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8055 (12%)                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3892   0.11034   0.10355  -0.0241   1.0000   0.2758
  -9.250  -0.3703   0.10558   0.09879  -0.0234   1.0000   0.2833
  -9.000  -0.3837   0.10369   0.09703  -0.0239   1.0000   0.2939
  -8.750  -0.3833   0.10115   0.09456  -0.0232   1.0000   0.3074
  -8.500  -0.3644   0.09688   0.09030  -0.0220   1.0000   0.3190
  -8.250  -0.3630   0.09394   0.08745  -0.0211   1.0000   0.3303
  -7.000  -0.5571   0.07160   0.06564  -0.0292   1.0000   0.1632
  -6.750  -0.5933   0.06475   0.05825  -0.0296   1.0000   0.1365
  -6.500  -0.6021   0.05931   0.05244  -0.0282   1.0000   0.1243
  -6.250  -0.5953   0.05572   0.04868  -0.0265   1.0000   0.1189
  -6.000  -0.5935   0.05138   0.04392  -0.0248   1.0000   0.1129
  -5.750  -0.5884   0.04739   0.03909  -0.0228   1.0000   0.1073
  -5.500  -0.5761   0.04416   0.03553  -0.0212   1.0000   0.1061
  -5.250  -0.5620   0.04133   0.03223  -0.0195   1.0000   0.1065
  -5.000  -0.5455   0.03887   0.02918  -0.0179   1.0000   0.1081
  -4.750  -0.5270   0.03630   0.02655  -0.0168   1.0000   0.1122
  -4.500  -0.5061   0.03425   0.02421  -0.0155   1.0000   0.1162
  -4.250  -0.4843   0.03242   0.02189  -0.0141   1.0000   0.1239
  -4.000  -0.4624   0.03076   0.02018  -0.0129   1.0000   0.1354
  -3.750  -0.4400   0.02910   0.01852  -0.0116   1.0000   0.1547
  -3.500  -0.4183   0.02756   0.01719  -0.0102   1.0000   0.1872
  -3.250  -0.3966   0.02575   0.01584  -0.0088   1.0000   0.2575
  -3.000  -0.3871   0.02266   0.01479  -0.0050   1.0000   0.4978
  -2.750  -0.3920   0.02243   0.01590   0.0063   1.0000   0.7827
  -2.500  -0.1363   0.02610   0.01796  -0.0260   1.0000   1.0000
  -2.250  -0.1434   0.02561   0.01734  -0.0226   1.0000   1.0000
  -2.000  -0.1487   0.02521   0.01679  -0.0191   1.0000   1.0000
  -1.750  -0.1525   0.02487   0.01632  -0.0157   1.0000   1.0000
  -1.500  -0.1549   0.02459   0.01589  -0.0124   1.0000   1.0000
  -1.250  -0.1551   0.02438   0.01554  -0.0093   1.0000   1.0000
  -1.000  -0.1521   0.02427   0.01526  -0.0066   1.0000   1.0000
  -0.750  -0.1462   0.02427   0.01508  -0.0043   1.0000   1.0000
  -0.500  -0.1372   0.02438   0.01500  -0.0025   1.0000   1.0000
  -0.250  -0.1258   0.02460   0.01504  -0.0011   1.0000   1.0000
   0.000  -0.1126   0.02491   0.01518   0.0001   1.0000   1.0000
   0.250  -0.0984   0.02529   0.01540   0.0010   1.0000   1.0000
   0.500  -0.0835   0.02573   0.01570   0.0017   1.0000   1.0000
   0.750  -0.0681   0.02624   0.01608   0.0023   1.0000   1.0000
   1.000  -0.0524   0.02681   0.01654   0.0029   1.0000   1.0000
   1.250  -0.0151   0.02807   0.01767  -0.0008   0.9908   1.0000
   1.500   0.0350   0.02972   0.01921  -0.0068   0.9743   1.0000
   1.750   0.0833   0.03127   0.02067  -0.0121   0.9571   1.0000
   2.000   0.1221   0.03243   0.02179  -0.0156   0.9389   1.0000
   2.250   0.1622   0.03362   0.02294  -0.0190   0.9201   1.0000
   2.500   0.2058   0.03482   0.02412  -0.0228   0.9006   1.0000
   2.750   0.2488   0.03593   0.02523  -0.0262   0.8810   1.0000
   3.000   0.2800   0.03673   0.02605  -0.0275   0.8598   1.0000
   3.250   0.3217   0.03755   0.02692  -0.0302   0.8388   1.0000
   3.500   0.3655   0.03823   0.02766  -0.0328   0.8181   1.0000
   3.750   0.3943   0.03876   0.02825  -0.0331   0.7952   1.0000
   4.000   0.4436   0.03892   0.02853  -0.0357   0.7740   1.0000
   4.250   0.4734   0.03917   0.02887  -0.0356   0.7508   1.0000
   4.500   0.5206   0.03878   0.02862  -0.0371   0.7289   1.0000
   4.750   0.5585   0.03836   0.02833  -0.0372   0.7056   1.0000
   5.000   0.6141   0.03688   0.02706  -0.0385   0.6837   1.0000
   5.250   0.6602   0.03536   0.02572  -0.0382   0.6611   1.0000
   5.500   0.7151   0.03301   0.02358  -0.0382   0.6385   1.0000
   5.750   0.7611   0.03110   0.02181  -0.0374   0.6116   1.0000
   6.000   0.8096   0.02915   0.01994  -0.0368   0.5803   1.0000
   6.250   0.8533   0.02782   0.01852  -0.0360   0.5442   1.0000
   6.500   0.8800   0.02784   0.01842  -0.0342   0.5070   1.0000
   6.750   0.9049   0.02820   0.01863  -0.0325   0.4713   1.0000
   7.000   0.9284   0.02886   0.01912  -0.0309   0.4388   1.0000
   7.250   0.9495   0.02975   0.01990  -0.0293   0.4092   1.0000
   7.500   0.9706   0.03080   0.02086  -0.0279   0.3826   1.0000
   7.750   0.9948   0.03187   0.02176  -0.0268   0.3578   1.0000
   8.000   1.0107   0.03329   0.02326  -0.0251   0.3358   1.0000
   8.250   1.0308   0.03468   0.02462  -0.0238   0.3150   1.0000
   8.500   1.0542   0.03612   0.02593  -0.0229   0.2952   1.0000
   8.750   1.0690   0.03787   0.02783  -0.0212   0.2779   1.0000
   9.000   1.0844   0.03968   0.02974  -0.0196   0.2618   1.0000
   9.250   1.1009   0.04162   0.03176  -0.0182   0.2473   1.0000
   9.500   1.1184   0.04357   0.03377  -0.0169   0.2335   1.0000
   9.750   1.1263   0.04583   0.03632  -0.0147   0.2225   1.0000
  10.000   1.1298   0.04869   0.03949  -0.0123   0.2143   1.0000
  10.250   1.1499   0.05086   0.04162  -0.0115   0.2036   1.0000
  10.500   1.1352   0.05429   0.04557  -0.0078   0.1990   1.0000
  10.750   1.1418   0.05710   0.04855  -0.0061   0.1926   1.0000
  11.000   1.1419   0.06062   0.05224  -0.0041   0.1882   1.0000
  11.250   1.1142   0.06487   0.05683  -0.0006   0.1871   1.0000
  11.500   1.0799   0.06936   0.06152   0.0028   0.1871   1.0000
  11.750   1.0429   0.07491   0.06722   0.0045   0.1880   1.0000
  12.000   1.0051   0.08175   0.07415   0.0042   0.1892   1.0000
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