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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.29 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe167-il-1000000.txt
Download as CSV file: xf-goe167-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3752   0.09064   0.08907  -0.0172   0.9175   0.0152
  -8.000  -0.3741   0.08814   0.08631  -0.0173   0.8442   0.0155
  -7.750  -0.3703   0.08514   0.08312  -0.0191   0.8008   0.0161
  -7.250  -0.3462   0.07349   0.07123  -0.0364   0.7481   0.0178
  -7.000  -0.3295   0.06790   0.06550  -0.0428   0.7233   0.0178
  -6.750  -0.3176   0.05988   0.05732  -0.0499   0.7023   0.0181
  -6.500  -0.3004   0.05755   0.05485  -0.0514   0.6743   0.0184
  -6.250  -0.2808   0.05524   0.05239  -0.0532   0.6496   0.0187
  -6.000  -0.2593   0.05255   0.04957  -0.0555   0.6291   0.0192
  -5.750  -0.2356   0.04941   0.04627  -0.0583   0.6130   0.0202
  -5.500  -0.1984   0.04306   0.03957  -0.0631   0.6022   0.0223
  -5.250  -0.1764   0.03426   0.03034  -0.0667   0.5939   0.0228
  -5.000  -0.1524   0.03274   0.02871  -0.0676   0.5830   0.0232
  -4.750  -0.1270   0.03140   0.02726  -0.0684   0.5741   0.0236
  -4.000  -0.0394   0.02666   0.02186  -0.0696   0.5534   0.0280
  -3.750  -0.0119   0.02063   0.01523  -0.0711   0.5487   0.0289
  -3.500   0.0159   0.01952   0.01406  -0.0717   0.5442   0.0295
  -3.250   0.0440   0.01890   0.01338  -0.0722   0.5394   0.0303
  -3.000   0.0726   0.01816   0.01250  -0.0726   0.5350   0.0315
  -2.750   0.1019   0.01742   0.01162  -0.0728   0.5313   0.0337
  -2.500   0.1316   0.01818   0.01229  -0.0727   0.5273   0.0355
  -2.250   0.1609   0.01731   0.01123  -0.0730   0.5232   0.0356
  -2.000   0.1901   0.01411   0.00771  -0.0738   0.5186   0.0378
  -1.750   0.2191   0.01351   0.00708  -0.0742   0.5150   0.0388
  -1.500   0.2495   0.01185   0.00520  -0.0741   0.5115   0.0321
  -1.250   0.2786   0.01128   0.00455  -0.0743   0.5082   0.0321
  -1.000   0.3076   0.01089   0.00409  -0.0745   0.5050   0.0322
  -0.750   0.3367   0.01053   0.00370  -0.0747   0.5022   0.0323
  -0.500   0.3658   0.01020   0.00336  -0.0750   0.4992   0.0324
  -0.250   0.3950   0.00994   0.00307  -0.0752   0.4955   0.0326
   0.000   0.4241   0.00977   0.00287  -0.0755   0.4920   0.0334
   0.250   0.4532   0.00963   0.00269  -0.0758   0.4886   0.0339
   0.500   0.4824   0.00948   0.00254  -0.0761   0.4864   0.0346
   0.750   0.5117   0.00937   0.00243  -0.0764   0.4839   0.0352
   1.000   0.5409   0.00926   0.00231  -0.0767   0.4804   0.0361
   1.250   0.5700   0.00917   0.00216  -0.0769   0.4756   0.0376
   1.500   0.5991   0.00912   0.00211  -0.0772   0.4717   0.0396
   1.750   0.6283   0.00907   0.00208  -0.0775   0.4688   0.0426
   2.000   0.6574   0.00902   0.00206  -0.0778   0.4656   0.0550
   2.250   0.6806   0.00690   0.00218  -0.0775   0.4621   1.0000
   2.500   0.7095   0.00699   0.00222  -0.0777   0.4573   1.0000
   2.750   0.7386   0.00702   0.00224  -0.0780   0.4521   1.0000
   3.000   0.7675   0.00711   0.00227  -0.0783   0.4460   1.0000
   3.250   0.7963   0.00719   0.00233  -0.0786   0.4417   1.0000
   3.500   0.8253   0.00724   0.00238  -0.0789   0.4366   1.0000
   3.750   0.8540   0.00734   0.00244  -0.0791   0.4302   1.0000
   4.000   0.8828   0.00741   0.00251  -0.0794   0.4240   1.0000
   4.250   0.9114   0.00752   0.00259  -0.0797   0.4155   1.0000
   4.500   0.9400   0.00761   0.00268  -0.0799   0.4059   1.0000
   4.750   0.9682   0.00779   0.00277  -0.0802   0.3876   1.0000
   5.000   0.9955   0.00811   0.00293  -0.0803   0.3522   1.0000
   5.250   1.0193   0.00915   0.00347  -0.0803   0.2579   1.0000
   5.500   1.0448   0.00980   0.00390  -0.0803   0.2180   1.0000
   5.750   1.0713   0.01023   0.00422  -0.0804   0.1947   1.0000
   6.000   1.0933   0.01139   0.00490  -0.0801   0.1081   1.0000
   6.250   1.1170   0.01221   0.00552  -0.0798   0.0672   1.0000
   6.500   1.1430   0.01258   0.00587  -0.0797   0.0608   1.0000
   6.750   1.1695   0.01286   0.00616  -0.0797   0.0571   1.0000
   7.000   1.1958   0.01314   0.00646  -0.0797   0.0540   1.0000
   7.250   1.2213   0.01353   0.00682  -0.0796   0.0485   1.0000
   7.500   1.2473   0.01381   0.00710  -0.0796   0.0423   1.0000
   7.750   1.2691   0.01462   0.00770  -0.0790   0.0176   1.0000
   8.000   1.2927   0.01517   0.00828  -0.0786   0.0150   1.0000
   8.250   1.3162   0.01570   0.00885  -0.0781   0.0137   1.0000
   8.500   1.3395   0.01619   0.00940  -0.0777   0.0130   1.0000
   8.750   1.3619   0.01675   0.01001  -0.0771   0.0123   1.0000
   9.000   1.3831   0.01741   0.01073  -0.0763   0.0116   1.0000
   9.250   1.4016   0.01826   0.01165  -0.0752   0.0109   1.0000
   9.500   1.4175   0.01928   0.01276  -0.0737   0.0103   1.0000
   9.750   1.4373   0.01988   0.01340  -0.0728   0.0100   1.0000
  10.000   1.4543   0.02063   0.01422  -0.0715   0.0096   1.0000
  10.250   1.4692   0.02146   0.01512  -0.0699   0.0093   1.0000
  10.500   1.4814   0.02237   0.01610  -0.0679   0.0090   1.0000
  10.750   1.4888   0.02337   0.01717  -0.0652   0.0087   1.0000
  11.000   1.4925   0.02459   0.01846  -0.0622   0.0085   1.0000
  11.250   1.4952   0.02612   0.02007  -0.0597   0.0083   1.0000
  11.500   1.4951   0.02813   0.02216  -0.0575   0.0081   1.0000
  11.750   1.4908   0.03085   0.02500  -0.0559   0.0079   1.0000
  12.000   1.4809   0.03452   0.02880  -0.0547   0.0077   1.0000
  12.250   1.4765   0.03781   0.03219  -0.0540   0.0076   1.0000
  12.500   1.4825   0.04008   0.03455  -0.0538   0.0075   1.0000
  12.750   1.4862   0.04264   0.03719  -0.0537   0.0075   1.0000
  13.000   1.4888   0.04532   0.03996  -0.0535   0.0073   1.0000
  13.250   1.4909   0.04809   0.04282  -0.0534   0.0072   1.0000
  13.500   1.4924   0.05094   0.04575  -0.0534   0.0071   1.0000
  13.750   1.4924   0.05393   0.04883  -0.0533   0.0069   1.0000
  14.000   1.4922   0.05698   0.05197  -0.0533   0.0068   1.0000
  14.250   1.4909   0.06014   0.05521  -0.0533   0.0066   1.0000
  14.500   1.4893   0.06337   0.05853  -0.0534   0.0065   1.0000
  14.750   1.4872   0.06672   0.06196  -0.0535   0.0064   1.0000
  15.000   1.4854   0.07012   0.06544  -0.0537   0.0063   1.0000
  15.250   1.4833   0.07361   0.06901  -0.0540   0.0062   1.0000
  15.500   1.4807   0.07720   0.07268  -0.0544   0.0061   1.0000
  15.750   1.4784   0.08082   0.07638  -0.0549   0.0060   1.0000
  16.000   1.4757   0.08453   0.08017  -0.0555   0.0059   1.0000
  16.250   1.4720   0.08840   0.08411  -0.0561   0.0059   1.0000
  16.500   1.4682   0.09228   0.08806  -0.0568   0.0058   1.0000
  16.750   1.4634   0.09629   0.09215  -0.0574   0.0057   1.0000
  17.000   1.4576   0.10038   0.09634  -0.0579   0.0056   1.0000
  17.250   1.4504   0.10460   0.10067  -0.0583   0.0055   1.0000
  17.750   1.4304   0.11434   0.11070  -0.0600   0.0054   1.0000
  18.000   1.4240   0.11939   0.11586  -0.0622   0.0054   1.0000
  18.250   1.4167   0.12460   0.12120  -0.0643   0.0054   1.0000
  18.500   1.4090   0.12994   0.12667  -0.0668   0.0054   1.0000
  18.750   1.4013   0.13550   0.13235  -0.0695   0.0053   1.0000
  19.000   1.3923   0.14133   0.13831  -0.0724   0.0053   1.0000
  19.250   1.3837   0.14735   0.14445  -0.0756   0.0053   1.0000
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