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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.26 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe116-il-1000000.txt
Download as CSV file: xf-goe116-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 116 (MVA MK.3) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4160   0.08252   0.08107  -0.0335   1.0000   0.0080
  -8.750  -0.4168   0.07537   0.07386  -0.0395   0.9450   0.0080
  -8.500  -0.4268   0.06977   0.06803  -0.0424   0.8797   0.0080
  -8.250  -0.4322   0.06258   0.06067  -0.0502   0.8460   0.0080
  -8.000  -0.4240   0.05032   0.04817  -0.0683   0.8268   0.0080
  -7.750  -0.4078   0.04037   0.03776  -0.0811   0.8133   0.0080
  -7.500  -0.3931   0.03560   0.03258  -0.0849   0.8022   0.0080
  -7.250  -0.3757   0.03169   0.02829  -0.0870   0.7923   0.0080
  -7.000  -0.3560   0.02828   0.02450  -0.0882   0.7837   0.0080
  -6.750  -0.3415   0.02099   0.01669  -0.0891   0.7761   0.0076
  -6.250  -0.2931   0.01651   0.01157  -0.0896   0.7616   0.0091
  -6.000  -0.2661   0.01523   0.01008  -0.0896   0.7548   0.0088
  -5.750  -0.2390   0.01424   0.00891  -0.0895   0.7481   0.0087
  -5.500  -0.2122   0.01310   0.00767  -0.0897   0.7417   0.0090
  -5.250  -0.1849   0.01233   0.00679  -0.0898   0.7355   0.0097
  -5.000  -0.1570   0.01149   0.00581  -0.0899   0.7298   0.0094
  -4.750  -0.1288   0.01078   0.00497  -0.0899   0.7239   0.0095
  -4.500  -0.1006   0.01022   0.00428  -0.0901   0.7186   0.0100
  -4.250  -0.0720   0.00975   0.00372  -0.0903   0.7131   0.0110
  -4.000  -0.0435   0.00940   0.00325  -0.0904   0.7078   0.0120
  -3.750  -0.0148   0.00911   0.00287  -0.0906   0.7029   0.0127
  -3.500   0.0139   0.00888   0.00257  -0.0907   0.6978   0.0132
  -3.250   0.0425   0.00860   0.00213  -0.0908   0.6929   0.0158
  -3.000   0.0714   0.00840   0.00186  -0.0910   0.6882   0.0198
  -2.750   0.0993   0.00774   0.00159  -0.0914   0.6834   0.1228
  -2.500   0.1280   0.00787   0.00174  -0.0915   0.6788   0.1363
  -2.250   0.1570   0.00804   0.00188  -0.0917   0.6743   0.1407
  -2.000   0.1857   0.00795   0.00178  -0.0920   0.6698   0.1451
  -1.750   0.2143   0.00798   0.00179  -0.0922   0.6655   0.1481
  -1.500   0.2433   0.00814   0.00194  -0.0924   0.6616   0.1531
  -1.250   0.2721   0.00813   0.00192  -0.0926   0.6575   0.1542
  -1.000   0.3007   0.00810   0.00185  -0.0928   0.6535   0.1546
  -0.750   0.3292   0.00798   0.00170  -0.0930   0.6497   0.1561
  -0.500   0.3579   0.00785   0.00159  -0.0933   0.6460   0.1577
  -0.250   0.3866   0.00779   0.00154  -0.0936   0.6421   0.1591
   0.000   0.4152   0.00776   0.00150  -0.0938   0.6383   0.1603
   0.250   0.4439   0.00774   0.00149  -0.0940   0.6344   0.1617
   0.500   0.4726   0.00770   0.00147  -0.0942   0.6296   0.1633
   0.750   0.5011   0.00770   0.00146  -0.0944   0.6245   0.1647
   1.000   0.5297   0.00768   0.00146  -0.0946   0.6198   0.1659
   1.250   0.5584   0.00766   0.00146  -0.0949   0.6152   0.1671
   1.500   0.5868   0.00768   0.00147  -0.0950   0.6100   0.1681
   1.750   0.6155   0.00764   0.00147  -0.0953   0.6041   0.1703
   2.000   0.6440   0.00762   0.00149  -0.0955   0.5983   0.1732
   2.250   0.6724   0.00761   0.00151  -0.0957   0.5900   0.1761
   2.500   0.7006   0.00763   0.00153  -0.0958   0.5773   0.1789
   2.750   0.7287   0.00767   0.00157  -0.0959   0.5649   0.1816
   3.000   0.7567   0.00770   0.00162  -0.0960   0.5485   0.1866
   3.250   0.7840   0.00782   0.00169  -0.0961   0.5183   0.1929
   3.500   0.8093   0.00823   0.00187  -0.0958   0.4539   0.2033
   3.750   0.8192   0.01078   0.00304  -0.0938   0.1567   0.2217
   4.000   0.8334   0.01045   0.00393  -0.0921   0.0203   1.0000
   4.250   0.8591   0.01084   0.00437  -0.0917   0.0147   1.0000
   4.500   0.8848   0.01120   0.00477  -0.0914   0.0135   1.0000
   4.750   0.9103   0.01157   0.00517  -0.0910   0.0125   1.0000
   5.000   0.9351   0.01202   0.00565  -0.0906   0.0113   1.0000
   5.250   0.9592   0.01252   0.00620  -0.0900   0.0102   1.0000
   5.500   0.9806   0.01330   0.00705  -0.0890   0.0090   1.0000
   5.750   0.9946   0.01485   0.00874  -0.0867   0.0084   1.0000
   6.000   1.0168   0.01545   0.00937  -0.0859   0.0082   1.0000
   6.250   1.0391   0.01601   0.00997  -0.0850   0.0079   1.0000
   6.500   1.0598   0.01673   0.01073  -0.0839   0.0074   1.0000
   6.750   1.0786   0.01764   0.01169  -0.0825   0.0069   1.0000
   7.000   1.0961   0.01877   0.01288  -0.0808   0.0066   1.0000
   7.250   1.1131   0.02028   0.01448  -0.0789   0.0065   1.0000
   7.500   1.1337   0.02271   0.01702  -0.0774   0.0070   1.0000
   7.750   1.1578   0.02480   0.01922  -0.0765   0.0071   1.0000
   8.000   1.1821   0.02753   0.02210  -0.0757   0.0074   1.0000
   8.750   1.2308   0.04025   0.03558  -0.0708   0.0083   1.0000
   9.000   1.2524   0.03793   0.03336  -0.0693   0.0074   1.0000
   9.250   1.2688   0.03908   0.03465  -0.0677   0.0064   1.0000
   9.500   1.2795   0.04084   0.03655  -0.0658   0.0060   1.0000
   9.750   1.2877   0.04263   0.03850  -0.0638   0.0057   1.0000
  10.000   1.2937   0.04453   0.04052  -0.0617   0.0055   1.0000
  10.250   1.2977   0.04668   0.04276  -0.0594   0.0054   1.0000
  10.500   1.2933   0.04949   0.04574  -0.0562   0.0052   1.0000
  10.750   1.2781   0.05289   0.04933  -0.0518   0.0051   1.0000
  11.000   1.2476   0.05839   0.05510  -0.0472   0.0050   1.0000
  11.250   1.2031   0.06586   0.06289  -0.0432   0.0049   1.0000
  11.500   1.1852   0.06969   0.06688  -0.0418   0.0049   1.0000
  11.750   1.1664   0.07395   0.07129  -0.0411   0.0049   1.0000
  12.000   1.1479   0.07855   0.07604  -0.0411   0.0049   1.0000
  12.250   1.1289   0.08356   0.08118  -0.0417   0.0049   1.0000
  12.500   1.1095   0.08901   0.08677  -0.0431   0.0049   1.0000
  12.750   1.0899   0.09493   0.09281  -0.0451   0.0049   1.0000
  13.000   1.0712   0.10120   0.09920  -0.0478   0.0049   1.0000
  13.250   1.0528   0.10795   0.10606  -0.0512   0.0049   1.0000
  13.500   1.0359   0.11529   0.11351  -0.0554   0.0049   1.0000
  13.750   0.8713   0.10744   0.10585  -0.0356   0.0057   1.0000
  14.000   0.8285   0.11805   0.11662  -0.0416   0.0061   1.0000
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