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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 200,000
Max Cl/Cd: 76.21 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe116-il-200000-n5.txt
Download as CSV file: xf-goe116-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2793   0.09889   0.09579  -0.0380   1.0000   0.0132
 -10.000  -0.2799   0.09473   0.09165  -0.0389   1.0000   0.0126
  -9.500  -0.3835   0.10164   0.09834  -0.0307   1.0000   0.0133
  -9.250  -0.3826   0.09747   0.09422  -0.0324   1.0000   0.0124
  -9.000  -0.3812   0.09326   0.09005  -0.0343   1.0000   0.0118
  -8.750  -0.3805   0.08892   0.08577  -0.0363   1.0000   0.0113
  -8.500  -0.3813   0.08441   0.08133  -0.0386   1.0000   0.0108
  -8.250  -0.3835   0.07955   0.07654  -0.0413   0.9937   0.0104
  -8.000  -0.3804   0.07194   0.06895  -0.0487   0.9541   0.0097
  -7.750  -0.3849   0.05449   0.05131  -0.0700   0.9164   0.0086
  -7.500  -0.3645   0.04241   0.03858  -0.0863   0.8923   0.0083
  -7.250  -0.3468   0.03759   0.03321  -0.0907   0.8742   0.0082
  -7.000  -0.3283   0.03366   0.02874  -0.0929   0.8596   0.0082
  -6.750  -0.3110   0.02930   0.02393  -0.0944   0.8474   0.0087
  -6.500  -0.2895   0.02685   0.02119  -0.0951   0.8367   0.0096
  -6.250  -0.2658   0.02480   0.01876  -0.0954   0.8269   0.0103
  -6.000  -0.2408   0.02276   0.01630  -0.0955   0.8177   0.0104
  -5.750  -0.2151   0.02104   0.01424  -0.0954   0.8093   0.0104
  -5.500  -0.1890   0.01961   0.01248  -0.0953   0.8018   0.0105
  -5.250  -0.1624   0.01838   0.01105  -0.0952   0.7944   0.0108
  -5.000  -0.1357   0.01739   0.00987  -0.0951   0.7876   0.0112
  -4.750  -0.1083   0.01659   0.00892  -0.0951   0.7806   0.0118
  -4.500  -0.0807   0.01604   0.00816  -0.0952   0.7742   0.0135
  -4.250  -0.0525   0.01550   0.00741  -0.0953   0.7681   0.0143
  -4.000  -0.0241   0.01476   0.00628  -0.0953   0.7622   0.0156
  -3.750   0.0041   0.01418   0.00541  -0.0953   0.7569   0.0184
  -3.500   0.0324   0.01364   0.00473  -0.0954   0.7508   0.0242
  -3.250   0.0599   0.01308   0.00452  -0.0956   0.7457   0.1284
  -3.000   0.0886   0.01337   0.00462  -0.0957   0.7404   0.1447
  -2.750   0.1171   0.01366   0.00483  -0.0958   0.7349   0.1566
  -2.500   0.1450   0.01390   0.00499  -0.0959   0.7303   0.1682
  -2.250   0.1733   0.01385   0.00481  -0.0961   0.7250   0.1722
  -2.000   0.2013   0.01369   0.00455  -0.0962   0.7200   0.1733
  -1.750   0.2293   0.01356   0.00431  -0.0963   0.7157   0.1744
  -1.500   0.2574   0.01340   0.00410  -0.0964   0.7106   0.1755
  -1.250   0.2852   0.01322   0.00391  -0.0965   0.7057   0.1769
  -1.000   0.3130   0.01310   0.00376  -0.0966   0.7016   0.1783
  -0.750   0.3411   0.01300   0.00367  -0.0968   0.6966   0.1803
  -0.500   0.3690   0.01291   0.00359  -0.0969   0.6918   0.1825
  -0.250   0.3969   0.01286   0.00350  -0.0970   0.6877   0.1846
   0.000   0.4250   0.01279   0.00345  -0.0972   0.6830   0.1864
   0.250   0.4530   0.01275   0.00342  -0.0973   0.6783   0.1883
   0.500   0.4809   0.01270   0.00338  -0.0974   0.6743   0.1901
   0.750   0.5088   0.01264   0.00340  -0.0976   0.6701   0.1925
   1.000   0.5368   0.01261   0.00344  -0.0977   0.6653   0.1952
   1.250   0.5647   0.01260   0.00347  -0.0978   0.6612   0.1984
   1.500   0.5927   0.01262   0.00353  -0.0980   0.6575   0.2021
   1.750   0.6206   0.01261   0.00364  -0.0981   0.6526   0.2062
   2.000   0.6485   0.01262   0.00374  -0.0983   0.6483   0.2118
   2.250   0.6765   0.01265   0.00385  -0.0984   0.6447   0.2193
   2.500   0.7042   0.01265   0.00402  -0.0985   0.6394   0.2321
   2.750   0.7318   0.01259   0.00416  -0.0986   0.6333   0.2632
   3.250   0.7827   0.01115   0.00451  -0.0976   0.6201   1.0000
   3.500   0.8098   0.01124   0.00465  -0.0974   0.6109   1.0000
   3.750   0.8346   0.01118   0.00453  -0.0965   0.5785   1.0000
   4.000   0.8589   0.01127   0.00454  -0.0957   0.5347   1.0000
   4.250   0.8745   0.01216   0.00470  -0.0935   0.3956   1.0000
   4.750   0.8865   0.01698   0.00755  -0.0879   0.0200   1.0000
   5.000   0.9068   0.01783   0.00856  -0.0866   0.0166   1.0000
   5.250   0.9283   0.01848   0.00935  -0.0857   0.0145   1.0000
   5.500   0.9476   0.01934   0.01039  -0.0843   0.0130   1.0000
   5.750   0.9643   0.02039   0.01157  -0.0826   0.0121   1.0000
   6.000   0.9785   0.02159   0.01287  -0.0806   0.0115   1.0000
   6.250   0.9911   0.02289   0.01423  -0.0784   0.0108   1.0000
   6.500   1.0009   0.02448   0.01585  -0.0759   0.0096   1.0000
   6.750   1.0106   0.02670   0.01808  -0.0733   0.0087   1.0000
   7.000   1.0298   0.02808   0.01953  -0.0719   0.0085   1.0000
   7.250   1.0519   0.02968   0.02123  -0.0708   0.0083   1.0000
   7.500   1.0766   0.03154   0.02322  -0.0701   0.0081   1.0000
   7.750   1.1023   0.03371   0.02556  -0.0695   0.0080   1.0000
   8.000   1.1267   0.03618   0.02832  -0.0687   0.0080   1.0000
   8.250   1.1483   0.03897   0.03139  -0.0676   0.0080   1.0000
   8.500   1.1656   0.04135   0.03406  -0.0660   0.0078   1.0000
   8.750   1.1802   0.04343   0.03643  -0.0642   0.0073   1.0000
   9.000   1.1918   0.04550   0.03875  -0.0622   0.0066   1.0000
   9.250   1.2001   0.04810   0.04163  -0.0599   0.0064   1.0000
   9.500   1.2042   0.05140   0.04527  -0.0572   0.0065   1.0000
   9.750   1.2024   0.05470   0.04888  -0.0539   0.0066   1.0000
  10.000   1.1954   0.05791   0.05237  -0.0503   0.0067   1.0000
  10.250   1.1855   0.06126   0.05598  -0.0471   0.0069   1.0000
  10.500   1.1731   0.06480   0.05976  -0.0445   0.0070   1.0000
  10.750   1.1590   0.06856   0.06375  -0.0425   0.0072   1.0000
  11.000   1.1435   0.07264   0.06804  -0.0412   0.0073   1.0000
  11.250   1.1269   0.07703   0.07263  -0.0406   0.0074   1.0000
  11.500   1.1092   0.08181   0.07760  -0.0406   0.0075   1.0000
  11.750   1.0913   0.08694   0.08290  -0.0414   0.0076   1.0000
  12.000   1.0727   0.09249   0.08861  -0.0428   0.0076   1.0000
  12.250   1.0541   0.09847   0.09475  -0.0450   0.0077   1.0000
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