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REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: REPUBLIC S-3 AIRFOIL (s3-il)
Reynolds number: 500,000
Max Cl/Cd: 73.74 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3-il-500000-n5.txt
Download as CSV file: xf-s3-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: REPUBLIC S-3 AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6756   0.05989   0.05765  -0.0298   1.0000   0.0056
 -10.000  -0.6977   0.05519   0.05284  -0.0316   1.0000   0.0055
  -9.750  -0.7910   0.03809   0.03497  -0.0281   1.0000   0.0054
  -9.500  -0.8061   0.03122   0.02743  -0.0253   1.0000   0.0055
  -9.250  -0.7985   0.02802   0.02382  -0.0236   1.0000   0.0056
  -9.000  -0.7892   0.02505   0.02047  -0.0218   1.0000   0.0058
  -8.750  -0.7727   0.02336   0.01858  -0.0206   1.0000   0.0059
  -8.500  -0.7533   0.02220   0.01726  -0.0196   1.0000   0.0061
  -8.250  -0.7334   0.02107   0.01598  -0.0186   1.0000   0.0063
  -8.000  -0.7129   0.02001   0.01478  -0.0176   1.0000   0.0064
  -7.750  -0.6909   0.01933   0.01402  -0.0168   1.0000   0.0068
  -7.500  -0.6695   0.01851   0.01309  -0.0158   1.0000   0.0072
  -7.250  -0.6385   0.01742   0.01184  -0.0168   0.9854   0.0076
  -7.000  -0.6041   0.01639   0.01064  -0.0185   0.9669   0.0080
  -6.500  -0.5410   0.01436   0.00831  -0.0205   0.9210   0.0088
  -6.250  -0.5159   0.01382   0.00767  -0.0199   0.8980   0.0092
  -5.750  -0.4679   0.01298   0.00659  -0.0182   0.8537   0.0105
  -5.500  -0.4438   0.01263   0.00611  -0.0174   0.8305   0.0114
  -5.250  -0.4196   0.01226   0.00560  -0.0166   0.8077   0.0121
  -5.000  -0.3959   0.01179   0.00499  -0.0157   0.7869   0.0136
  -4.500  -0.3448   0.01124   0.00424  -0.0146   0.7575   0.0166
  -4.250  -0.3189   0.01096   0.00389  -0.0141   0.7455   0.0198
  -4.000  -0.2926   0.01074   0.00362  -0.0137   0.7339   0.0241
  -3.750  -0.2662   0.01053   0.00336  -0.0134   0.7228   0.0291
  -3.500  -0.2394   0.01039   0.00316  -0.0131   0.7126   0.0345
  -3.250  -0.2126   0.01018   0.00295  -0.0128   0.7022   0.0417
  -3.000  -0.1857   0.01004   0.00274  -0.0125   0.6905   0.0480
  -2.750  -0.1589   0.00988   0.00256  -0.0122   0.6772   0.0574
  -2.500  -0.1321   0.00970   0.00237  -0.0120   0.6628   0.0727
  -2.250  -0.1057   0.00944   0.00218  -0.0117   0.6489   0.1066
  -2.000  -0.0833   0.00852   0.00186  -0.0111   0.6356   0.2878
  -1.750  -0.0594   0.00795   0.00169  -0.0106   0.6184   0.4150
  -1.500  -0.0340   0.00771   0.00158  -0.0101   0.5941   0.4843
  -1.250  -0.0088   0.00756   0.00151  -0.0095   0.5614   0.5419
  -1.000   0.0163   0.00757   0.00145  -0.0090   0.5135   0.5835
  -0.750   0.0414   0.00765   0.00144  -0.0084   0.4626   0.6216
  -0.500   0.0666   0.00770   0.00147  -0.0078   0.4287   0.6629
  -0.250   0.0921   0.00773   0.00152  -0.0072   0.4089   0.7012
   0.000   0.1190   0.00779   0.00154  -0.0069   0.3938   0.7222
   0.250   0.1458   0.00783   0.00158  -0.0066   0.3795   0.7434
   0.500   0.1725   0.00788   0.00162  -0.0063   0.3646   0.7638
   0.750   0.1995   0.00795   0.00165  -0.0060   0.3481   0.7788
   1.000   0.2267   0.00804   0.00168  -0.0058   0.3300   0.7906
   1.250   0.2537   0.00814   0.00173  -0.0056   0.3114   0.8028
   1.500   0.2805   0.00825   0.00178  -0.0053   0.2950   0.8154
   1.750   0.3073   0.00835   0.00185  -0.0051   0.2821   0.8275
   2.000   0.3340   0.00846   0.00193  -0.0048   0.2713   0.8393
   2.250   0.3608   0.00856   0.00202  -0.0045   0.2616   0.8517
   2.500   0.3876   0.00865   0.00211  -0.0042   0.2533   0.8651
   2.750   0.4141   0.00876   0.00222  -0.0039   0.2446   0.8800
   3.000   0.4411   0.00884   0.00233  -0.0036   0.2358   0.8961
   3.250   0.4686   0.00897   0.00245  -0.0035   0.2243   0.9130
   3.500   0.4980   0.00913   0.00257  -0.0038   0.2117   0.9302
   3.750   0.5303   0.00930   0.00270  -0.0048   0.2006   0.9460
   4.000   0.5653   0.00946   0.00286  -0.0064   0.1936   0.9600
   4.250   0.6005   0.00965   0.00302  -0.0081   0.1869   0.9727
   4.500   0.6351   0.00984   0.00318  -0.0097   0.1812   0.9844
   4.750   0.6698   0.01004   0.00337  -0.0114   0.1745   0.9948
   5.000   0.6999   0.01026   0.00357  -0.0121   0.1694   1.0000
   5.250   0.7246   0.01043   0.00375  -0.0115   0.1668   1.0000
   5.500   0.7493   0.01061   0.00395  -0.0110   0.1630   1.0000
   5.750   0.7736   0.01087   0.00417  -0.0104   0.1562   1.0000
   6.000   0.7988   0.01105   0.00436  -0.0100   0.1499   1.0000
   6.250   0.8235   0.01131   0.00458  -0.0096   0.1417   1.0000
   6.500   0.8487   0.01152   0.00481  -0.0092   0.1333   1.0000
   6.750   0.8731   0.01184   0.00505  -0.0087   0.1164   1.0000
   7.000   0.8925   0.01277   0.00565  -0.0078   0.0688   1.0000
   7.250   0.9149   0.01335   0.00616  -0.0072   0.0545   1.0000
   7.500   0.9374   0.01392   0.00666  -0.0065   0.0407   1.0000
   7.750   0.9575   0.01479   0.00742  -0.0056   0.0146   1.0000
   8.000   0.9802   0.01533   0.00803  -0.0049   0.0122   1.0000
   8.250   1.0027   0.01589   0.00868  -0.0043   0.0104   1.0000
   8.500   1.0257   0.01636   0.00922  -0.0037   0.0096   1.0000
   8.750   1.0478   0.01690   0.00984  -0.0030   0.0086   1.0000
   9.000   1.0690   0.01753   0.01056  -0.0022   0.0080   1.0000
   9.250   1.0885   0.01833   0.01149  -0.0013   0.0073   1.0000
   9.500   1.1092   0.01895   0.01220  -0.0005   0.0070   1.0000
   9.750   1.1286   0.01966   0.01301   0.0004   0.0066   1.0000
  10.000   1.1472   0.02041   0.01386   0.0014   0.0062   1.0000
  10.250   1.1651   0.02115   0.01467   0.0024   0.0058   1.0000
  10.500   1.1807   0.02205   0.01564   0.0037   0.0055   1.0000
  10.750   1.1911   0.02327   0.01697   0.0054   0.0052   1.0000
  11.000   1.2008   0.02438   0.01818   0.0073   0.0050   1.0000
  11.250   1.2071   0.02541   0.01933   0.0098   0.0049   1.0000
  11.500   1.2107   0.02661   0.02065   0.0121   0.0048   1.0000
  11.750   1.2126   0.02808   0.02223   0.0141   0.0046   1.0000
  12.000   1.2106   0.03003   0.02430   0.0157   0.0045   1.0000
  12.250   1.2117   0.03198   0.02637   0.0165   0.0044   1.0000
  12.500   1.2088   0.03458   0.02909   0.0167   0.0043   1.0000
  12.750   1.2019   0.03790   0.03254   0.0163   0.0043   1.0000
  13.000   1.1965   0.04136   0.03613   0.0154   0.0041   1.0000
  13.250   1.1886   0.04548   0.04038   0.0139   0.0041   1.0000
  13.500   1.1821   0.04977   0.04479   0.0119   0.0040   1.0000
  13.750   1.1664   0.05579   0.05097   0.0089   0.0041   1.0000
  14.000   1.1544   0.06154   0.05685   0.0059   0.0040   1.0000
  14.250   1.1405   0.06758   0.06301   0.0029   0.0040   1.0000
  14.500   1.1255   0.07379   0.06933  -0.0002   0.0040   1.0000
  14.750   1.1121   0.07977   0.07542  -0.0031   0.0039   1.0000
  15.000   1.0978   0.08597   0.08172  -0.0061   0.0040   1.0000
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