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GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 399 AIRFOIL (goe399-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.09 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe399-il-1000000.txt
Download as CSV file: xf-goe399-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 399 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3656   0.08500   0.08345  -0.0267   1.0000   0.0113
  -7.750  -0.3681   0.08310   0.08158  -0.0257   1.0000   0.0114
  -7.500  -0.3724   0.08213   0.08065  -0.0234   1.0000   0.0120
  -6.750  -0.3325   0.01488   0.01128  -0.0835   0.9764   0.0118
  -6.500  -0.2985   0.01467   0.01105  -0.0849   0.9730   0.0124
  -6.250  -0.2652   0.01373   0.00993  -0.0863   0.9698   0.0132
  -6.000  -0.2391   0.01289   0.00891  -0.0860   0.9616   0.0140
  -5.750  -0.2081   0.01235   0.00823  -0.0867   0.9557   0.0147
  -5.500  -0.1838   0.01121   0.00688  -0.0861   0.9451   0.0161
  -5.250  -0.1557   0.01132   0.00700  -0.0860   0.9348   0.0170
  -5.000  -0.1281   0.01143   0.00708  -0.0857   0.9223   0.0183
  -4.750  -0.1016   0.01130   0.00685  -0.0853   0.9068   0.0194
  -4.500  -0.0774   0.01030   0.00560  -0.0845   0.8881   0.0208
  -4.250  -0.0515   0.01016   0.00537  -0.0840   0.8696   0.0221
  -4.000  -0.0251   0.01019   0.00533  -0.0835   0.8509   0.0234
  -3.750   0.0010   0.01017   0.00521  -0.0830   0.8324   0.0249
  -3.500   0.0273   0.01013   0.00506  -0.0825   0.8154   0.0262
  -3.250   0.0540   0.01019   0.00502  -0.0821   0.8003   0.0268
  -3.000   0.0778   0.00885   0.00345  -0.0814   0.7872   0.0292
  -2.750   0.1043   0.00871   0.00326  -0.0810   0.7749   0.0309
  -2.500   0.1307   0.00851   0.00298  -0.0806   0.7636   0.0322
  -2.250   0.1571   0.00832   0.00271  -0.0802   0.7528   0.0335
  -2.000   0.1835   0.00813   0.00245  -0.0798   0.7427   0.0346
  -1.750   0.2101   0.00791   0.00218  -0.0794   0.7337   0.0352
  -1.500   0.2366   0.00775   0.00195  -0.0790   0.7250   0.0358
  -1.250   0.2632   0.00756   0.00170  -0.0787   0.7160   0.0366
  -1.000   0.2893   0.00726   0.00133  -0.0782   0.7068   0.0401
  -0.750   0.3159   0.00717   0.00120  -0.0778   0.6972   0.0425
  -0.500   0.3428   0.00710   0.00110  -0.0775   0.6863   0.0450
  -0.250   0.3697   0.00706   0.00101  -0.0772   0.6753   0.0474
   0.000   0.3963   0.00697   0.00093  -0.0769   0.6634   0.0600
   0.250   0.4229   0.00693   0.00090  -0.0765   0.6503   0.0790
   0.500   0.4496   0.00691   0.00087  -0.0762   0.6380   0.0925
   0.750   0.4760   0.00685   0.00086  -0.0759   0.6259   0.1217
   1.000   0.5015   0.00660   0.00090  -0.0755   0.6129   0.2509
   1.250   0.5667   0.00498   0.00105  -0.0847   0.5935   1.0000
   1.500   0.5915   0.00513   0.00107  -0.0840   0.5669   1.0000
   1.750   0.6165   0.00529   0.00110  -0.0833   0.5416   1.0000
   2.000   0.6415   0.00545   0.00115  -0.0827   0.5171   1.0000
   2.250   0.6663   0.00564   0.00123  -0.0820   0.4922   1.0000
   2.500   0.6908   0.00585   0.00131  -0.0814   0.4686   1.0000
   2.750   0.7159   0.00602   0.00141  -0.0808   0.4504   1.0000
   3.000   0.7410   0.00619   0.00150  -0.0802   0.4341   1.0000
   3.250   0.7663   0.00636   0.00162  -0.0797   0.4202   1.0000
   3.500   0.7916   0.00651   0.00173  -0.0792   0.4073   1.0000
   3.750   0.8169   0.00667   0.00184  -0.0786   0.3956   1.0000
   4.000   0.8422   0.00683   0.00196  -0.0781   0.3824   1.0000
   4.250   0.8674   0.00700   0.00210  -0.0776   0.3680   1.0000
   4.500   0.8922   0.00719   0.00223  -0.0770   0.3473   1.0000
   4.750   0.9153   0.00755   0.00241  -0.0762   0.3061   1.0000
   5.000   0.9355   0.00818   0.00273  -0.0749   0.2439   1.0000
   5.250   0.9564   0.00877   0.00307  -0.0738   0.1945   1.0000
   5.500   0.9701   0.01009   0.00381  -0.0716   0.0791   1.0000
   5.750   0.9924   0.01055   0.00415  -0.0706   0.0599   1.0000
   6.000   1.0165   0.01082   0.00443  -0.0700   0.0538   1.0000
   6.250   1.0400   0.01114   0.00474  -0.0692   0.0482   1.0000
   6.500   1.0639   0.01142   0.00505  -0.0686   0.0431   1.0000
   6.750   1.0871   0.01175   0.00534  -0.0678   0.0342   1.0000
   7.000   1.1085   0.01227   0.00574  -0.0668   0.0201   1.0000
   7.250   1.1306   0.01273   0.00621  -0.0658   0.0160   1.0000
   7.500   1.1519   0.01324   0.00674  -0.0647   0.0138   1.0000
   7.750   1.1717   0.01390   0.00750  -0.0633   0.0122   1.0000
   8.000   1.1933   0.01435   0.00800  -0.0623   0.0116   1.0000
   8.250   1.2138   0.01488   0.00859  -0.0611   0.0108   1.0000
   8.500   1.2335   0.01545   0.00922  -0.0598   0.0102   1.0000
   8.750   1.2520   0.01611   0.00993  -0.0584   0.0096   1.0000
   9.000   1.2626   0.01741   0.01135  -0.0557   0.0087   1.0000
   9.250   1.2784   0.01821   0.01225  -0.0538   0.0084   1.0000
   9.500   1.2972   0.01872   0.01282  -0.0525   0.0080   1.0000
   9.750   1.3122   0.01950   0.01367  -0.0506   0.0077   1.0000
  10.000   1.3260   0.02033   0.01458  -0.0485   0.0074   1.0000
  10.250   1.3381   0.02114   0.01547  -0.0461   0.0071   1.0000
  10.500   1.3456   0.02208   0.01650  -0.0430   0.0069   1.0000
  10.750   1.3551   0.02292   0.01740  -0.0404   0.0067   1.0000
  11.000   1.3617   0.02401   0.01859  -0.0376   0.0066   1.0000
  11.250   1.3695   0.02505   0.01970  -0.0351   0.0063   1.0000
  11.500   1.3719   0.02660   0.02134  -0.0323   0.0061   1.0000
  11.750   1.3725   0.02846   0.02332  -0.0296   0.0060   1.0000
  12.000   1.3614   0.03192   0.02702  -0.0260   0.0057   1.0000
  12.250   1.3653   0.03369   0.02892  -0.0242   0.0056   1.0000
  12.500   1.3734   0.03489   0.03022  -0.0230   0.0055   1.0000
  12.750   1.3762   0.03687   0.03233  -0.0216   0.0054   1.0000
  13.000   1.3804   0.03870   0.03428  -0.0207   0.0053   1.0000
  13.250   1.3830   0.04081   0.03651  -0.0198   0.0050   1.0000
  13.500   1.3795   0.04378   0.03964  -0.0190   0.0050   1.0000
  13.750   1.3752   0.04694   0.04297  -0.0185   0.0049   1.0000
  14.000   1.3691   0.05047   0.04666  -0.0183   0.0049   1.0000
  14.250   1.3639   0.05397   0.05029  -0.0186   0.0048   1.0000
  14.500   1.3507   0.05877   0.05529  -0.0192   0.0047   1.0000
  14.750   1.3429   0.06298   0.05964  -0.0202   0.0047   1.0000
  15.000   1.3282   0.06852   0.06535  -0.0219   0.0047   1.0000
  15.250   1.3151   0.07412   0.07111  -0.0240   0.0046   1.0000
  15.500   1.3005   0.08027   0.07742  -0.0266   0.0046   1.0000
  15.750   1.2777   0.08836   0.08571  -0.0304   0.0047   1.0000
  16.000   1.2546   0.09691   0.09445  -0.0347   0.0048   1.0000
  16.250   1.2419   0.10378   0.10143  -0.0384   0.0047   1.0000
  16.500   1.2155   0.11399   0.11182  -0.0441   0.0047   1.0000
  16.750   1.2006   0.12201   0.11995  -0.0487   0.0047   1.0000
  17.000   1.1638   0.13617   0.13430  -0.0569   0.0049   1.0000
  17.250   1.1389   0.14824   0.14650  -0.0640   0.0050   1.0000
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