Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 645 AIRFOIL (goe645-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.46 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe645-il-1000000.txt
Download as CSV file: xf-goe645-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 645 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
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -0.6784   0.14191   0.13974  -0.0292   1.0000   0.0190
 -18.750  -0.7092   0.13169   0.12941  -0.0349   1.0000   0.0193
 -18.500  -0.7246   0.12472   0.12238  -0.0387   1.0000   0.0196
 -18.250  -0.7491   0.11632   0.11387  -0.0435   1.0000   0.0199
 -18.000  -0.7633   0.10993   0.10741  -0.0471   1.0000   0.0201
 -17.750  -0.7788   0.10350   0.10089  -0.0507   1.0000   0.0204
 -17.500  -0.7915   0.09771   0.09503  -0.0539   1.0000   0.0205
 -17.250  -0.8046   0.09198   0.08922  -0.0571   1.0000   0.0207
 -17.000  -0.8177   0.08632   0.08347  -0.0604   1.0000   0.0209
 -16.750  -0.8296   0.08096   0.07803  -0.0635   1.0000   0.0212
 -16.500  -0.8395   0.07612   0.07312  -0.0662   1.0000   0.0213
 -16.250  -0.8516   0.07102   0.06794  -0.0692   1.0000   0.0215
 -16.000  -0.8638   0.06631   0.06315  -0.0718   1.0000   0.0215
 -15.750  -0.8782   0.06154   0.05831  -0.0745   1.0000   0.0216
 -15.500  -0.8953   0.05669   0.05339  -0.0771   1.0000   0.0217
 -15.250  -0.9183   0.05142   0.04806  -0.0799   1.0000   0.0219
 -15.000  -0.9439   0.04591   0.04246  -0.0827   1.0000   0.0220
 -14.750  -0.9722   0.04006   0.03653  -0.0857   1.0000   0.0220
 -14.500  -1.0086   0.03105   0.02732  -0.0942   1.0000   0.0219
 -14.250  -1.0349   0.02848   0.02462  -0.0910   1.0000   0.0219
 -14.000  -1.0441   0.02663   0.02270  -0.0880   1.0000   0.0222
 -13.750  -1.0449   0.02535   0.02137  -0.0851   1.0000   0.0224
 -13.500  -1.0185   0.02428   0.02025  -0.0865   0.9986   0.0229
 -13.250  -0.9865   0.02330   0.01921  -0.0887   0.9965   0.0233
 -13.000  -0.9524   0.02247   0.01833  -0.0910   0.9943   0.0239
 -12.750  -0.9195   0.02163   0.01741  -0.0929   0.9916   0.0244
 -12.500  -0.8864   0.02095   0.01667  -0.0945   0.9879   0.0250
 -12.250  -0.8519   0.02030   0.01593  -0.0964   0.9848   0.0253
 -12.000  -0.8216   0.01881   0.01438  -0.0985   0.9818   0.0261
 -11.750  -0.7953   0.01810   0.01365  -0.0988   0.9748   0.0266
 -11.500  -0.7622   0.01748   0.01299  -0.1002   0.9704   0.0272
 -11.250  -0.7322   0.01695   0.01242  -0.1009   0.9622   0.0279
 -10.750  -0.6554   0.01591   0.01125  -0.1055   0.9460   0.0291
 -10.500  -0.6174   0.01498   0.01023  -0.1082   0.9311   0.0299
 -10.250  -0.5834   0.01433   0.00948  -0.1098   0.9086   0.0307
 -10.000  -0.5561   0.01399   0.00902  -0.1097   0.8828   0.0314
  -9.750  -0.5320   0.01372   0.00863  -0.1089   0.8590   0.0321
  -9.500  -0.5085   0.01347   0.00827  -0.1080   0.8383   0.0328
  -9.250  -0.4849   0.01325   0.00792  -0.1070   0.8200   0.0334
  -9.000  -0.4606   0.01303   0.00760  -0.1062   0.8043   0.0338
  -8.750  -0.4393   0.01247   0.00694  -0.1050   0.7909   0.0348
  -8.500  -0.4155   0.01215   0.00655  -0.1042   0.7786   0.0358
  -8.250  -0.3905   0.01191   0.00625  -0.1035   0.7669   0.0367
  -8.000  -0.3653   0.01167   0.00594  -0.1028   0.7562   0.0375
  -7.750  -0.3399   0.01147   0.00565  -0.1021   0.7461   0.0383
  -7.500  -0.3137   0.01127   0.00539  -0.1016   0.7373   0.0389
  -7.250  -0.2895   0.01088   0.00494  -0.1008   0.7279   0.0406
  -7.000  -0.2634   0.01064   0.00466  -0.1002   0.7191   0.0419
  -6.750  -0.2374   0.01046   0.00441  -0.0997   0.7097   0.0432
  -6.500  -0.2105   0.01029   0.00419  -0.0992   0.7012   0.0444
  -6.250  -0.1851   0.01001   0.00386  -0.0986   0.6923   0.0469
  -6.000  -0.1584   0.00979   0.00362  -0.0981   0.6838   0.0495
  -5.750  -0.1324   0.00958   0.00336  -0.0975   0.6742   0.0534
  -5.500  -0.1063   0.00929   0.00308  -0.0970   0.6645   0.0618
  -5.250  -0.0812   0.00898   0.00289  -0.0964   0.6540   0.0950
  -5.000  -0.0539   0.00887   0.00279  -0.0960   0.6436   0.1053
  -4.750  -0.0271   0.00877   0.00267  -0.0956   0.6330   0.1121
  -4.500  -0.0001   0.00872   0.00257  -0.0951   0.6209   0.1174
  -4.250   0.0271   0.00866   0.00246  -0.0947   0.6081   0.1217
  -4.000   0.0537   0.00859   0.00236  -0.0943   0.5944   0.1268
  -3.750   0.0803   0.00857   0.00226  -0.0938   0.5790   0.1309
  -3.500   0.1069   0.00855   0.00218  -0.0933   0.5644   0.1358
  -3.000   0.1599   0.00842   0.00203  -0.0923   0.5374   0.1572
  -2.750   0.1860   0.00836   0.00198  -0.0918   0.5231   0.1782
  -2.500   0.2124   0.00832   0.00196  -0.0913   0.5108   0.1994
  -2.250   0.2391   0.00832   0.00195  -0.0909   0.4992   0.2153
  -2.000   0.2665   0.00833   0.00195  -0.0905   0.4904   0.2271
  -1.750   0.2935   0.00835   0.00196  -0.0901   0.4817   0.2398
  -1.500   0.3210   0.00836   0.00197  -0.0899   0.4744   0.2484
  -1.250   0.3481   0.00840   0.00198  -0.0895   0.4657   0.2553
  -1.000   0.3756   0.00845   0.00198  -0.0892   0.4575   0.2604
  -0.750   0.4027   0.00847   0.00199  -0.0888   0.4498   0.2671
  -0.500   0.4299   0.00851   0.00201  -0.0885   0.4432   0.2728
  -0.250   0.4576   0.00855   0.00203  -0.0882   0.4370   0.2771
   0.000   0.4844   0.00859   0.00205  -0.0878   0.4303   0.2838
   0.250   0.5117   0.00862   0.00208  -0.0875   0.4245   0.2898
   0.500   0.5391   0.00867   0.00211  -0.0872   0.4184   0.2948
   0.750   0.5656   0.00872   0.00215  -0.0868   0.4119   0.3026
   1.000   0.5929   0.00875   0.00219  -0.0865   0.4068   0.3090
   1.250   0.6200   0.00881   0.00222  -0.0862   0.4004   0.3142
   1.500   0.6462   0.00888   0.00228  -0.0857   0.3938   0.3220
   1.750   0.6735   0.00890   0.00233  -0.0854   0.3886   0.3293
   2.000   0.7000   0.00896   0.00238  -0.0850   0.3820   0.3378
   2.250   0.7262   0.00903   0.00245  -0.0846   0.3755   0.3479
   2.500   0.7528   0.00907   0.00251  -0.0842   0.3686   0.3599
   3.000   0.8045   0.00919   0.00267  -0.0832   0.3535   0.3930
   3.250   0.8294   0.00927   0.00277  -0.0826   0.3448   0.4190
   3.500   0.8544   0.00925   0.00288  -0.0819   0.3374   0.4681
   3.750   0.8766   0.00919   0.00304  -0.0809   0.3273   0.5725
   4.000   0.9532   0.00867   0.00340  -0.0916   0.3110   1.0000
   4.250   0.9765   0.00884   0.00352  -0.0906   0.3011   1.0000
   4.500   0.9992   0.00905   0.00366  -0.0895   0.2915   1.0000
   4.750   1.0214   0.00927   0.00381  -0.0883   0.2811   1.0000
   5.000   1.0441   0.00947   0.00396  -0.0873   0.2721   1.0000
   5.250   1.0659   0.00972   0.00414  -0.0861   0.2629   1.0000
   5.500   1.0885   0.00992   0.00431  -0.0850   0.2557   1.0000
   5.750   1.1101   0.01017   0.00450  -0.0838   0.2480   1.0000
   6.000   1.1328   0.01036   0.00467  -0.0828   0.2423   1.0000
   6.250   1.1543   0.01061   0.00487  -0.0816   0.2360   1.0000
   6.500   1.1766   0.01081   0.00506  -0.0805   0.2314   1.0000
   6.750   1.1989   0.01101   0.00525  -0.0794   0.2268   1.0000
   7.000   1.2199   0.01126   0.00547  -0.0782   0.2217   1.0000
   7.250   1.2411   0.01150   0.00569  -0.0770   0.2168   1.0000
   7.500   1.2626   0.01171   0.00589  -0.0758   0.2121   1.0000
   7.750   1.2821   0.01200   0.00615  -0.0743   0.2062   1.0000
   8.000   1.3015   0.01224   0.00638  -0.0728   0.2015   1.0000
   8.250   1.3198   0.01248   0.00661  -0.0710   0.1963   1.0000
   8.500   1.3353   0.01282   0.00692  -0.0688   0.1891   1.0000
   8.750   1.3523   0.01312   0.00720  -0.0670   0.1802   1.0000
   9.000   1.3650   0.01363   0.00761  -0.0645   0.1641   1.0000
   9.250   1.3667   0.01461   0.00838  -0.0604   0.1343   1.0000
   9.500   1.3797   0.01516   0.00890  -0.0582   0.1285   1.0000
   9.750   1.3928   0.01573   0.00946  -0.0561   0.1232   1.0000
  10.000   1.4080   0.01623   0.00997  -0.0544   0.1213   1.0000
  10.250   1.4230   0.01676   0.01051  -0.0527   0.1199   1.0000
  10.500   1.4371   0.01735   0.01112  -0.0511   0.1182   1.0000
  10.750   1.4504   0.01803   0.01182  -0.0494   0.1162   1.0000
  11.000   1.4646   0.01870   0.01252  -0.0480   0.1150   1.0000
  11.250   1.4784   0.01942   0.01327  -0.0466   0.1139   1.0000
  11.500   1.4910   0.02026   0.01415  -0.0452   0.1124   1.0000
  11.750   1.5052   0.02104   0.01498  -0.0441   0.1119   1.0000
  12.000   1.5201   0.02181   0.01580  -0.0432   0.1114   1.0000
  12.250   1.5340   0.02269   0.01673  -0.0422   0.1108   1.0000
  12.500   1.5472   0.02364   0.01774  -0.0413   0.1105   1.0000
  12.750   1.5599   0.02466   0.01882  -0.0405   0.1093   1.0000
  13.000   1.5714   0.02581   0.02002  -0.0397   0.1084   1.0000
  13.250   1.5813   0.02712   0.02138  -0.0388   0.1072   1.0000
  13.500   1.5905   0.02852   0.02283  -0.0380   0.1063   1.0000
  13.750   1.5978   0.03013   0.02448  -0.0373   0.1051   1.0000
  14.000   1.6029   0.03196   0.02637  -0.0365   0.1038   1.0000
  14.250   1.6064   0.03396   0.02843  -0.0358   0.1024   1.0000
  14.500   1.6063   0.03637   0.03091  -0.0351   0.1007   1.0000
  14.750   1.6129   0.03819   0.03279  -0.0347   0.1000   1.0000
  15.000   1.6240   0.03958   0.03424  -0.0344   0.0994   1.0000
  15.250   1.6336   0.04115   0.03588  -0.0341   0.0984   1.0000
  15.500   1.6407   0.04299   0.03778  -0.0338   0.0972   1.0000
  15.750   1.6477   0.04488   0.03972  -0.0336   0.0949   1.0000
  16.000   1.6494   0.04734   0.04223  -0.0334   0.0932   1.0000
  16.250   1.6455   0.05047   0.04541  -0.0333   0.0907   1.0000
  16.500   1.6466   0.05311   0.04810  -0.0333   0.0886   1.0000
  16.750   1.6566   0.05476   0.04982  -0.0333   0.0858   1.0000
  17.000   1.6535   0.05793   0.05297  -0.0334   0.0786   1.0000
  17.250   1.6341   0.06303   0.05799  -0.0338   0.0621   1.0000
  17.500   1.5993   0.07017   0.06512  -0.0347   0.0513   1.0000
  17.750   1.5716   0.07662   0.07162  -0.0357   0.0453   1.0000
  18.000   1.5487   0.08260   0.07767  -0.0367   0.0410   1.0000
<< Back to GOE 645 AIRFOIL (goe645-il)

Polar data table (+)

Polar graphs


<< Back to GOE 645 AIRFOIL (goe645-il)