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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 100,000
Max Cl/Cd: 54.84 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe529-il-100000.txt
Download as CSV file: xf-goe529-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2677   0.10175   0.09749  -0.0316   1.0000   0.0760
  -7.750  -0.2907   0.10216   0.09805  -0.0274   1.0000   0.0764
  -7.500  -0.3160   0.10276   0.09880  -0.0225   1.0000   0.0764
  -7.250  -0.2991   0.10166   0.09770  -0.0423   0.9842   0.0781
  -7.000  -0.2799   0.09469   0.09075  -0.0414   0.9794   0.0794
  -6.750  -0.2541   0.08980   0.08584  -0.0407   0.9746   0.0824
  -6.500  -0.2249   0.08553   0.08152  -0.0475   0.9646   0.0875
  -6.250  -0.1865   0.08155   0.07738  -0.0698   0.9473   0.0933
  -6.000  -0.1663   0.07630   0.07219  -0.0653   0.9441   0.0962
  -5.750  -0.1394   0.07262   0.06846  -0.0694   0.9349   0.1011
  -5.500  -0.0930   0.06751   0.06312  -0.0857   0.9267   0.1090
  -5.250  -0.0754   0.06411   0.05977  -0.0841   0.9171   0.1124
  -5.000  -0.0284   0.05960   0.05500  -0.0957   0.9113   0.1246
  -4.750  -0.0109   0.05673   0.05216  -0.0947   0.9006   0.1289
  -4.500   0.0243   0.05329   0.04846  -0.1017   0.8911   0.1401
  -4.250   0.0519   0.05024   0.04538  -0.1028   0.8839   0.1475
  -4.000   0.0767   0.04759   0.04258  -0.1050   0.8741   0.1590
  -3.750   0.1091   0.04476   0.03959  -0.1081   0.8676   0.1739
  -3.500   0.1313   0.04271   0.03739  -0.1090   0.8573   0.1876
  -3.250   0.1627   0.04021   0.03475  -0.1109   0.8515   0.2042
  -3.000   0.1818   0.03859   0.03303  -0.1105   0.8412   0.2204
  -2.750   0.2110   0.03651   0.03084  -0.1113   0.8357   0.2508
  -2.500   0.2633   0.03074   0.02345  -0.1162   0.8262   0.1242
  -2.250   0.2968   0.02809   0.02048  -0.1169   0.8209   0.1139
  -2.000   0.3223   0.02675   0.01843  -0.1157   0.8112   0.1076
  -1.750   0.3537   0.02506   0.01663  -0.1162   0.8057   0.1117
  -1.500   0.3763   0.02434   0.01572  -0.1152   0.7958   0.1140
  -1.250   0.4094   0.02315   0.01422  -0.1153   0.7902   0.1167
  -1.000   0.4324   0.02263   0.01351  -0.1141   0.7803   0.1208
  -0.750   0.4637   0.02175   0.01255  -0.1141   0.7744   0.1309
  -0.500   0.4863   0.02139   0.01220  -0.1131   0.7644   0.1449
  -0.250   0.5147   0.02070   0.01149  -0.1125   0.7575   0.1699
   0.000   0.5390   0.02022   0.01118  -0.1117   0.7485   0.2125
   0.250   0.5648   0.01967   0.01090  -0.1111   0.7405   0.2802
   0.500   0.6126   0.01761   0.01034  -0.1143   0.7327   1.0000
   0.750   0.6369   0.01788   0.01037  -0.1133   0.7236   1.0000
   1.000   0.6651   0.01795   0.01021  -0.1129   0.7160   1.0000
   1.250   0.6876   0.01830   0.01044  -0.1118   0.7058   1.0000
   1.500   0.7166   0.01836   0.01030  -0.1115   0.6988   1.0000
   1.750   0.7392   0.01870   0.01056  -0.1105   0.6884   1.0000
   2.000   0.7639   0.01898   0.01074  -0.1097   0.6793   1.0000
   2.250   0.7915   0.01911   0.01073  -0.1092   0.6711   1.0000
   2.500   0.8139   0.01951   0.01109  -0.1082   0.6608   1.0000
   2.750   0.8425   0.01963   0.01108  -0.1079   0.6532   1.0000
   3.000   0.8651   0.01999   0.01142  -0.1069   0.6427   1.0000
   3.250   0.8890   0.02036   0.01175  -0.1061   0.6333   1.0000
   3.500   0.9170   0.02050   0.01181  -0.1057   0.6252   1.0000
   3.750   0.9381   0.02100   0.01234  -0.1046   0.6149   1.0000
   4.000   0.9672   0.02115   0.01238  -0.1044   0.6079   1.0000
   4.250   0.9875   0.02168   0.01297  -0.1032   0.5975   1.0000
   4.500   1.0122   0.02204   0.01335  -0.1026   0.5893   1.0000
   4.750   1.0369   0.02236   0.01367  -0.1019   0.5806   1.0000
   5.000   1.0588   0.02284   0.01420  -0.1010   0.5714   1.0000
   5.250   1.0871   0.02293   0.01426  -0.1007   0.5638   1.0000
   5.500   1.1064   0.02348   0.01493  -0.0994   0.5537   1.0000
   5.750   1.1351   0.02354   0.01494  -0.0991   0.5464   1.0000
   6.000   1.1556   0.02394   0.01545  -0.0979   0.5363   1.0000
   6.250   1.1781   0.02428   0.01588  -0.0970   0.5271   1.0000
   6.500   1.2061   0.02430   0.01589  -0.0967   0.5192   1.0000
   6.750   1.2251   0.02481   0.01655  -0.0953   0.5092   1.0000
   7.000   1.2523   0.02487   0.01661  -0.0949   0.5011   1.0000
   7.250   1.2746   0.02516   0.01702  -0.0939   0.4916   1.0000
   7.500   1.2956   0.02559   0.01757  -0.0928   0.4822   1.0000
   7.750   1.3254   0.02559   0.01755  -0.0927   0.4745   1.0000
   8.000   1.3423   0.02626   0.01842  -0.0911   0.4643   1.0000
   8.250   1.3658   0.02657   0.01883  -0.0903   0.4551   1.0000
   8.500   1.3938   0.02642   0.01864  -0.0899   0.4440   1.0000
   8.750   1.4140   0.02632   0.01857  -0.0882   0.4287   1.0000
   9.000   1.4318   0.02635   0.01867  -0.0863   0.4132   1.0000
   9.250   1.4498   0.02650   0.01888  -0.0845   0.3987   1.0000
   9.500   1.4652   0.02672   0.01919  -0.0824   0.3840   1.0000
   9.750   1.4750   0.02698   0.01958  -0.0795   0.3676   1.0000
  10.000   1.4827   0.02732   0.02005  -0.0763   0.3511   1.0000
  10.250   1.4856   0.02771   0.02056  -0.0725   0.3326   1.0000
  10.500   1.4846   0.02824   0.02117  -0.0682   0.3141   1.0000
  10.750   1.4812   0.02905   0.02204  -0.0638   0.2958   1.0000
  11.000   1.4735   0.03027   0.02333  -0.0595   0.2733   1.0000
  11.250   1.4610   0.03210   0.02510  -0.0555   0.2449   1.0000
  11.500   1.4434   0.03477   0.02764  -0.0519   0.2092   1.0000
  11.750   1.4218   0.03839   0.03102  -0.0492   0.1618   1.0000
  12.000   1.3977   0.04280   0.03513  -0.0473   0.1321   1.0000
  12.250   1.3737   0.04775   0.03990  -0.0462   0.1105   1.0000
  12.500   1.3533   0.05273   0.04480  -0.0456   0.0926   1.0000
  12.750   1.3357   0.05769   0.04971  -0.0454   0.0760   1.0000
  13.000   1.3211   0.06247   0.05446  -0.0455   0.0698   1.0000
  13.250   1.3081   0.06724   0.05927  -0.0458   0.0649   1.0000
  13.500   1.2963   0.07199   0.06406  -0.0462   0.0614   1.0000
  13.750   1.2852   0.07662   0.06867  -0.0466   0.0586   1.0000
  14.000   1.2841   0.07992   0.07208  -0.0464   0.0555   1.0000
  14.250   1.2854   0.08281   0.07502  -0.0460   0.0524   1.0000
  14.500   1.2949   0.08389   0.07591  -0.0440   0.0484   1.0000
  14.750   1.3059   0.08554   0.07771  -0.0429   0.0461   1.0000
  15.000   1.3223   0.08651   0.07879  -0.0412   0.0441   1.0000
  15.250   1.3395   0.08762   0.07999  -0.0395   0.0426   1.0000
  15.500   1.3571   0.08902   0.08148  -0.0380   0.0412   1.0000
  15.750   1.3824   0.09011   0.08256  -0.0359   0.0394   1.0000
  16.000   1.3918   0.09362   0.08627  -0.0353   0.0384   1.0000
  16.250   1.3853   0.09805   0.09100  -0.0363   0.0381   1.0000
  16.500   1.3757   0.10297   0.09620  -0.0377   0.0379   1.0000
  16.750   1.3656   0.10819   0.10169  -0.0394   0.0378   1.0000
  17.000   1.3536   0.11386   0.10761  -0.0416   0.0377   1.0000
  17.250   1.3409   0.11984   0.11384  -0.0442   0.0379   1.0000
  17.500   1.3262   0.12633   0.12056  -0.0474   0.0380   1.0000
  17.750   1.3109   0.13320   0.12764  -0.0510   0.0382   1.0000
  18.000   1.2947   0.14050   0.13513  -0.0551   0.0384   1.0000
  18.250   1.2794   0.14796   0.14279  -0.0595   0.0387   1.0000
  18.500   1.2536   0.15759   0.15267  -0.0668   0.0392   1.0000
  19.000   1.1139   0.21908   0.21425  -0.1053   0.0573   1.0000
  19.250   1.1260   0.22177   0.21701  -0.1053   0.0588   1.0000
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