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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.72 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe275-il-1000000-n5.txt
Download as CSV file: xf-goe275-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 275 (DAIMLER VI) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2897   0.08792   0.08629  -0.0370   0.9929   0.0072
  -8.250  -0.2795   0.08334   0.08171  -0.0413   0.9886   0.0074
  -8.000  -0.2780   0.07728   0.07566  -0.0466   0.9792   0.0079
  -7.750  -0.2640   0.07454   0.07293  -0.0497   0.9689   0.0081
  -7.500  -0.2440   0.07090   0.06928  -0.0551   0.9585   0.0082
  -7.250  -0.2125   0.06684   0.06519  -0.0632   0.9485   0.0085
  -7.000  -0.1674   0.06102   0.05929  -0.0763   0.9389   0.0090
  -6.750  -0.1163   0.05202   0.05012  -0.0942   0.9207   0.0103
  -6.500  -0.0863   0.04867   0.04664  -0.0999   0.9034   0.0105
  -6.250  -0.0640   0.04601   0.04385  -0.1027   0.8879   0.0108
  -5.750  -0.0254   0.03619   0.03364  -0.1089   0.8606   0.0128
  -5.500  -0.0038   0.03459   0.03194  -0.1093   0.8469   0.0130
  -5.250   0.0179   0.03290   0.03011  -0.1096   0.8312   0.0133
  -5.000   0.0398   0.03092   0.02798  -0.1098   0.8149   0.0137
  -4.750   0.0612   0.02455   0.02114  -0.1102   0.8008   0.0156
  -4.500   0.0837   0.02349   0.01992  -0.1097   0.7809   0.0158
  -4.250   0.1059   0.02267   0.01892  -0.1090   0.7537   0.0160
  -4.000   0.1270   0.02170   0.01770  -0.1080   0.7129   0.0163
  -3.750   0.1466   0.02066   0.01628  -0.1066   0.6542   0.0167
  -3.500   0.1686   0.01919   0.01446  -0.1055   0.6135   0.0176
  -3.250   0.1914   0.01604   0.01072  -0.1041   0.5854   0.0189
  -3.000   0.2153   0.01547   0.00993  -0.1034   0.5571   0.0191
  -2.750   0.2399   0.01509   0.00940  -0.1029   0.5327   0.0193
  -2.500   0.2649   0.01471   0.00887  -0.1024   0.5094   0.0196
  -2.250   0.2897   0.01429   0.00826  -0.1018   0.4837   0.0201
  -2.000   0.3147   0.01365   0.00739  -0.1011   0.4567   0.0206
  -1.750   0.3397   0.01306   0.00656  -0.1004   0.4292   0.0209
  -1.500   0.3648   0.01254   0.00581  -0.0997   0.4031   0.0213
  -1.250   0.3902   0.01207   0.00515  -0.0990   0.3819   0.0215
  -1.000   0.4160   0.01170   0.00462  -0.0985   0.3661   0.0220
  -0.750   0.4421   0.01144   0.00423  -0.0980   0.3540   0.0222
  -0.250   0.4938   0.01069   0.00333  -0.0970   0.3353   0.0228
   0.000   0.5197   0.01052   0.00311  -0.0965   0.3263   0.0231
   0.250   0.5460   0.01037   0.00294  -0.0961   0.3202   0.0234
   0.750   0.5982   0.01017   0.00268  -0.0953   0.3055   0.0241
   1.000   0.6243   0.01009   0.00256  -0.0948   0.2986   0.0244
   1.250   0.6505   0.01000   0.00245  -0.0944   0.2935   0.0246
   1.500   0.6770   0.00994   0.00239  -0.0941   0.2891   0.0251
   1.750   0.7033   0.00991   0.00234  -0.0937   0.2846   0.0256
   2.000   0.7295   0.00988   0.00228  -0.0933   0.2798   0.0258
   2.250   0.7560   0.00984   0.00224  -0.0929   0.2758   0.0261
   2.500   0.7822   0.00985   0.00224  -0.0925   0.2689   0.0265
   2.750   0.8084   0.00990   0.00226  -0.0921   0.2624   0.0269
   3.000   0.8344   0.00991   0.00225  -0.0917   0.2539   0.0275
   3.250   0.8603   0.00997   0.00227  -0.0913   0.2441   0.0283
   3.500   0.8854   0.01013   0.00235  -0.0908   0.2249   0.0291
   3.750   0.9079   0.01054   0.00255  -0.0898   0.1837   0.0299
   4.000   0.9327   0.01075   0.00270  -0.0892   0.1721   0.0312
   4.250   0.9580   0.01091   0.00284  -0.0887   0.1649   0.0322
   4.500   0.9836   0.01104   0.00296  -0.0883   0.1607   0.0331
   4.750   1.0089   0.01119   0.00311  -0.0878   0.1567   0.0371
   5.000   1.0381   0.00986   0.00356  -0.0888   0.1519   1.0000
   5.250   1.0635   0.01002   0.00371  -0.0883   0.1485   1.0000
   5.500   1.0884   0.01022   0.00389  -0.0877   0.1427   1.0000
   5.750   1.1127   0.01047   0.00409  -0.0871   0.1356   1.0000
   6.000   1.1376   0.01066   0.00427  -0.0866   0.1291   1.0000
   6.250   1.1588   0.01121   0.00461  -0.0855   0.0966   1.0000
   6.500   1.1816   0.01159   0.00492  -0.0846   0.0854   1.0000
   6.750   1.2054   0.01187   0.00519  -0.0839   0.0819   1.0000
   7.000   1.2289   0.01217   0.00548  -0.0832   0.0785   1.0000
   7.250   1.2524   0.01246   0.00578  -0.0825   0.0750   1.0000
   7.500   1.2765   0.01269   0.00603  -0.0819   0.0734   1.0000
   7.750   1.3000   0.01295   0.00631  -0.0812   0.0710   1.0000
   8.000   1.3231   0.01324   0.00662  -0.0804   0.0687   1.0000
   8.250   1.3455   0.01358   0.00696  -0.0795   0.0657   1.0000
   8.500   1.3677   0.01393   0.00732  -0.0786   0.0621   1.0000
   8.750   1.3908   0.01418   0.00761  -0.0779   0.0612   1.0000
   9.000   1.4134   0.01446   0.00792  -0.0771   0.0594   1.0000
   9.250   1.4352   0.01479   0.00826  -0.0762   0.0560   1.0000
   9.500   1.4557   0.01522   0.00865  -0.0751   0.0514   1.0000
   9.750   1.4767   0.01557   0.00902  -0.0741   0.0476   1.0000
  10.000   1.4953   0.01609   0.00950  -0.0727   0.0402   1.0000
  10.250   1.5038   0.01734   0.01055  -0.0698   0.0168   1.0000
  10.500   1.5191   0.01798   0.01122  -0.0679   0.0131   1.0000
  10.750   1.5334   0.01855   0.01182  -0.0657   0.0115   1.0000
  11.000   1.5465   0.01914   0.01246  -0.0634   0.0101   1.0000
  11.250   1.5604   0.01968   0.01306  -0.0613   0.0094   1.0000
  11.500   1.5730   0.02029   0.01372  -0.0590   0.0086   1.0000
  11.750   1.5841   0.02100   0.01447  -0.0566   0.0079   1.0000
  12.000   1.5948   0.02174   0.01527  -0.0542   0.0074   1.0000
  12.250   1.6066   0.02242   0.01602  -0.0521   0.0070   1.0000
  12.500   1.6168   0.02321   0.01688  -0.0499   0.0066   1.0000
  12.750   1.6259   0.02408   0.01781  -0.0476   0.0062   1.0000
  13.000   1.6334   0.02509   0.01888  -0.0454   0.0059   1.0000
  13.250   1.6396   0.02623   0.02009  -0.0431   0.0056   1.0000
  13.500   1.6442   0.02753   0.02148  -0.0409   0.0053   1.0000
  13.750   1.6507   0.02875   0.02278  -0.0390   0.0052   1.0000
  14.000   1.6552   0.03019   0.02431  -0.0371   0.0050   1.0000
  14.250   1.6589   0.03177   0.02598  -0.0355   0.0049   1.0000
  14.500   1.6620   0.03349   0.02779  -0.0340   0.0047   1.0000
  14.750   1.6637   0.03542   0.02981  -0.0327   0.0046   1.0000
  15.000   1.6632   0.03771   0.03221  -0.0315   0.0044   1.0000
  15.250   1.6622   0.04019   0.03477  -0.0308   0.0043   1.0000
  15.500   1.6588   0.04310   0.03780  -0.0303   0.0042   1.0000
  15.750   1.6541   0.04639   0.04120  -0.0303   0.0041   1.0000
  16.000   1.6478   0.05010   0.04501  -0.0307   0.0040   1.0000
  16.250   1.6399   0.05426   0.04929  -0.0315   0.0039   1.0000
  16.500   1.6272   0.05934   0.05451  -0.0329   0.0038   1.0000
  16.750   1.6140   0.06473   0.06004  -0.0347   0.0038   1.0000
  17.000   1.6008   0.07034   0.06578  -0.0368   0.0037   1.0000
  17.250   1.5831   0.07689   0.07247  -0.0394   0.0037   1.0000
  17.500   1.5643   0.08381   0.07953  -0.0423   0.0036   1.0000
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