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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 100,000
Max Cl/Cd: 47.95 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda2-il-100000-n5.txt
Download as CSV file: xf-coanda2-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 2                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4279   0.09123   0.08653  -0.0183   1.0000   0.0211
  -8.250  -0.4330   0.08797   0.08336  -0.0190   1.0000   0.0203
  -8.000  -0.4419   0.08425   0.07974  -0.0195   1.0000   0.0196
  -7.750  -0.4429   0.08019   0.07575  -0.0213   1.0000   0.0188
  -7.250  -0.4386   0.07294   0.06853  -0.0235   1.0000   0.0181
  -7.000  -0.4356   0.06919   0.06480  -0.0246   1.0000   0.0179
  -6.750  -0.4320   0.06494   0.06055  -0.0258   1.0000   0.0178
  -6.500  -0.4267   0.06059   0.05616  -0.0269   1.0000   0.0176
  -6.250  -0.4198   0.05618   0.05168  -0.0277   1.0000   0.0175
  -6.000  -0.4122   0.05118   0.04654  -0.0284   1.0000   0.0173
  -5.750  -0.4040   0.04577   0.04089  -0.0286   1.0000   0.0172
  -5.500  -0.3952   0.04018   0.03497  -0.0280   1.0000   0.0170
  -5.250  -0.3862   0.03434   0.02869  -0.0266   1.0000   0.0169
  -5.000  -0.3750   0.02935   0.02301  -0.0243   1.0000   0.0169
  -4.750  -0.3600   0.02617   0.01923  -0.0221   1.0000   0.0173
  -4.500  -0.3422   0.02410   0.01666  -0.0201   1.0000   0.0182
  -4.250  -0.3237   0.02240   0.01459  -0.0182   1.0000   0.0205
  -4.000  -0.3030   0.02135   0.01324  -0.0165   1.0000   0.0226
  -3.750  -0.2812   0.02054   0.01220  -0.0150   1.0000   0.0253
  -3.500  -0.2616   0.02205   0.01433  -0.0136   1.0000   0.0407
  -3.250  -0.2366   0.02106   0.01243  -0.0120   1.0000   0.0702
  -3.000  -0.2071   0.02255   0.01389  -0.0128   0.9962   0.0866
  -2.750  -0.1639   0.02292   0.01416  -0.0167   0.9872   0.1020
  -2.500  -0.1244   0.02243   0.01331  -0.0191   0.9790   0.1074
  -2.250  -0.0889   0.02179   0.01236  -0.0206   0.9716   0.1088
  -2.000  -0.0521   0.02114   0.01145  -0.0224   0.9653   0.1094
  -1.750  -0.0179   0.02045   0.01055  -0.0236   0.9576   0.1094
  -1.500   0.0173   0.01984   0.00979  -0.0251   0.9499   0.1096
  -1.250   0.0548   0.01927   0.00908  -0.0269   0.9422   0.1103
  -1.000   0.0887   0.01870   0.00843  -0.0280   0.9328   0.1109
  -0.750   0.1272   0.01800   0.00775  -0.0301   0.9247   0.1121
  -0.500   0.1636   0.01743   0.00721  -0.0317   0.9147   0.1134
  -0.250   0.1982   0.01693   0.00675  -0.0329   0.9031   0.1147
   0.000   0.2339   0.01647   0.00637  -0.0343   0.8906   0.1177
   0.250   0.2697   0.01608   0.00603  -0.0357   0.8760   0.1216
   0.500   0.3060   0.01569   0.00568  -0.0371   0.8588   0.1235
   0.750   0.3406   0.01536   0.00538  -0.0381   0.8363   0.1243
   1.000   0.3810   0.01497   0.00506  -0.0404   0.8087   0.1258
   1.250   0.4234   0.01465   0.00473  -0.0430   0.7715   0.1281
   1.500   0.4658   0.01445   0.00442  -0.0455   0.7193   0.1311
   1.750   0.5036   0.01447   0.00424  -0.0470   0.6619   0.1350
   2.000   0.5348   0.01466   0.00424  -0.0474   0.6144   0.1394
   2.250   0.5632   0.01487   0.00438  -0.0475   0.5745   0.1470
   2.500   0.5915   0.01502   0.00462  -0.0475   0.5396   0.1723
   3.000   0.7140   0.01489   0.00535  -0.0635   0.3660   1.0000
   3.250   0.7342   0.01553   0.00561  -0.0621   0.2887   1.0000
   3.500   0.7557   0.01617   0.00596  -0.0609   0.2290   1.0000
   3.750   0.7752   0.01717   0.00649  -0.0596   0.1474   1.0000
   4.250   0.8126   0.01963   0.00827  -0.0565   0.0220   1.0000
   4.500   0.8339   0.02048   0.00936  -0.0551   0.0193   1.0000
   4.750   0.8542   0.02151   0.01063  -0.0535   0.0172   1.0000
   5.000   0.8739   0.02260   0.01199  -0.0518   0.0165   1.0000
   5.250   0.8920   0.02379   0.01343  -0.0500   0.0162   1.0000
   5.500   0.9091   0.02502   0.01484  -0.0480   0.0160   1.0000
   5.750   0.9251   0.02634   0.01633  -0.0459   0.0158   1.0000
   6.000   0.9417   0.02761   0.01775  -0.0439   0.0151   1.0000
   6.250   0.9582   0.02904   0.01938  -0.0420   0.0144   1.0000
   6.500   0.9751   0.03071   0.02117  -0.0400   0.0138   1.0000
   6.750   0.9933   0.03259   0.02318  -0.0383   0.0139   1.0000
   7.000   1.0122   0.03469   0.02546  -0.0367   0.0140   1.0000
   7.250   1.0304   0.03699   0.02800  -0.0350   0.0142   1.0000
   7.500   1.0468   0.03949   0.03078  -0.0332   0.0145   1.0000
   7.750   1.0605   0.04238   0.03400  -0.0311   0.0148   1.0000
   8.000   1.0704   0.04569   0.03766  -0.0288   0.0152   1.0000
   8.250   1.0772   0.04958   0.04184  -0.0265   0.0158   1.0000
   8.500   1.0931   0.05139   0.04387  -0.0247   0.0170   1.0000
   8.750   1.0985   0.05321   0.04617  -0.0216   0.0182   1.0000
   9.000   1.0914   0.05665   0.05019  -0.0176   0.0196   1.0000
   9.250   1.0840   0.06000   0.05387  -0.0146   0.0203   1.0000
   9.500   1.0688   0.06347   0.05760  -0.0109   0.0212   1.0000
   9.750   1.0531   0.06681   0.06115  -0.0084   0.0215   1.0000
  10.000   1.0359   0.07059   0.06512  -0.0073   0.0217   1.0000
  10.250   1.0176   0.07503   0.06975  -0.0078   0.0218   1.0000
  10.500   0.9987   0.08030   0.07520  -0.0103   0.0216   1.0000
  10.750   0.9783   0.08699   0.08205  -0.0148   0.0214   1.0000
  11.000   0.9586   0.09479   0.08998  -0.0207   0.0209   1.0000
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