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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 500,000
Max Cl/Cd: 106.83 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe116-il-500000.txt
Download as CSV file: xf-goe116-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4140   0.11447   0.11229  -0.0220   1.0000   0.0133
 -10.250  -0.4240   0.10736   0.10522  -0.0243   1.0000   0.0139
 -10.000  -0.4221   0.10342   0.10131  -0.0259   1.0000   0.0143
  -9.750  -0.4174   0.10017   0.09807  -0.0273   1.0000   0.0147
  -9.500  -0.4129   0.09685   0.09477  -0.0288   1.0000   0.0150
  -5.750  -0.2355   0.01702   0.01139  -0.0921   0.8009   0.0199
  -5.500  -0.2086   0.01515   0.00924  -0.0918   0.7931   0.0174
  -5.250  -0.1808   0.01406   0.00788  -0.0914   0.7863   0.0155
  -5.000  -0.1530   0.01328   0.00692  -0.0913   0.7790   0.0150
  -4.750  -0.1252   0.01250   0.00598  -0.0913   0.7727   0.0152
  -4.500  -0.0971   0.01177   0.00511  -0.0914   0.7660   0.0161
  -4.250  -0.0690   0.01126   0.00442  -0.0914   0.7604   0.0173
  -4.000  -0.0404   0.01083   0.00384  -0.0916   0.7541   0.0189
  -3.750  -0.0120   0.01054   0.00337  -0.0916   0.7486   0.0208
  -3.500   0.0167   0.01030   0.00301  -0.0917   0.7431   0.0239
  -3.250   0.0444   0.00964   0.00277  -0.0919   0.7376   0.1243
  -3.000   0.0735   0.01007   0.00310  -0.0920   0.7328   0.1425
  -2.750   0.1025   0.01029   0.00332  -0.0923   0.7272   0.1506
  -2.500   0.1313   0.01048   0.00340  -0.0924   0.7222   0.1553
  -2.250   0.1595   0.01042   0.00334  -0.0926   0.7176   0.1607
  -2.000   0.1884   0.01074   0.00360  -0.0928   0.7124   0.1679
  -1.750   0.2164   0.01049   0.00334  -0.0930   0.7078   0.1719
  -1.500   0.2448   0.01036   0.00318  -0.0932   0.7034   0.1729
  -1.250   0.2732   0.01022   0.00304  -0.0934   0.6985   0.1741
  -1.000   0.3016   0.01012   0.00290  -0.0935   0.6942   0.1754
  -0.750   0.3300   0.01005   0.00280  -0.0937   0.6902   0.1767
  -0.500   0.3585   0.00995   0.00272  -0.0939   0.6856   0.1781
  -0.250   0.3869   0.00989   0.00264  -0.0941   0.6814   0.1795
   0.000   0.4153   0.00987   0.00258  -0.0942   0.6776   0.1809
   0.250   0.4439   0.00983   0.00257  -0.0944   0.6732   0.1822
   0.500   0.4722   0.00968   0.00246  -0.0946   0.6691   0.1846
   0.750   0.5005   0.00963   0.00242  -0.0948   0.6653   0.1866
   1.000   0.5290   0.00960   0.00244  -0.0950   0.6611   0.1887
   1.250   0.5574   0.00956   0.00244  -0.0952   0.6561   0.1910
   1.500   0.5857   0.00955   0.00243  -0.0953   0.6512   0.1936
   1.750   0.6140   0.00953   0.00245  -0.0955   0.6455   0.1960
   2.000   0.6423   0.00946   0.00246  -0.0957   0.6400   0.2002
   2.250   0.6705   0.00947   0.00251  -0.0958   0.6353   0.2048
   2.750   0.7266   0.00939   0.00257  -0.0960   0.6202   0.2192
   3.000   0.7539   0.00925   0.00254  -0.0959   0.6025   0.2370
   3.250   0.7765   0.00757   0.00268  -0.0951   0.5912   1.0000
   3.500   0.8040   0.00763   0.00272  -0.0950   0.5754   1.0000
   3.750   0.8301   0.00777   0.00273  -0.0946   0.5382   1.0000
   4.000   0.8507   0.00857   0.00296  -0.0935   0.4199   1.0000
   4.500   0.8739   0.01290   0.00539  -0.0894   0.0223   1.0000
   4.750   0.8985   0.01334   0.00591  -0.0888   0.0197   1.0000
   5.000   0.9220   0.01392   0.00657  -0.0881   0.0179   1.0000
   5.250   0.9438   0.01466   0.00738  -0.0871   0.0165   1.0000
   5.500   0.9628   0.01566   0.00847  -0.0857   0.0154   1.0000
   5.750   0.9788   0.01691   0.00982  -0.0837   0.0148   1.0000
   6.000   0.9900   0.01863   0.01163  -0.0811   0.0138   1.0000
   6.250   1.0112   0.01928   0.01234  -0.0800   0.0133   1.0000
   6.500   1.0290   0.02040   0.01351  -0.0784   0.0129   1.0000
   6.750   1.0474   0.02172   0.01489  -0.0768   0.0126   1.0000
   7.000   1.0683   0.02343   0.01665  -0.0754   0.0125   1.0000
   9.250   1.2311   0.05242   0.04751  -0.0632   0.0138   1.0000
   9.500   1.2342   0.05365   0.04902  -0.0600   0.0136   1.0000
   9.750   1.2500   0.05208   0.04764  -0.0575   0.0121   1.0000
  10.000   1.2517   0.05452   0.05031  -0.0546   0.0113   1.0000
  10.250   1.2475   0.05724   0.05324  -0.0514   0.0109   1.0000
  10.500   1.2367   0.05979   0.05596  -0.0475   0.0106   1.0000
  10.750   1.2235   0.06258   0.05892  -0.0443   0.0104   1.0000
  11.000   1.2087   0.06571   0.06222  -0.0417   0.0102   1.0000
  11.250   1.1929   0.06923   0.06594  -0.0400   0.0101   1.0000
  11.500   1.1760   0.07316   0.07003  -0.0390   0.0101   1.0000
  11.750   1.1580   0.07753   0.07455  -0.0386   0.0100   1.0000
  12.000   1.1388   0.08244   0.07962  -0.0390   0.0100   1.0000
  12.250   1.1186   0.08787   0.08517  -0.0402   0.0100   1.0000
  12.500   1.0973   0.09394   0.09139  -0.0422   0.0100   1.0000
  12.750   1.0747   0.10081   0.09840  -0.0451   0.0101   1.0000
  13.000   1.0510   0.10873   0.10646  -0.0493   0.0102   1.0000
  13.250   1.0265   0.11815   0.11601  -0.0550   0.0105   1.0000
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