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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 500,000
Max Cl/Cd: 100.68 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe140-il-500000.txt
Download as CSV file: xf-goe140-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2998   0.09797   0.09588  -0.0219   1.0000   0.0206
  -8.000  -0.2996   0.09532   0.09326  -0.0243   1.0000   0.0207
  -7.750  -0.2987   0.09248   0.09047  -0.0267   1.0000   0.0207
  -7.500  -0.2950   0.08938   0.08740  -0.0290   1.0000   0.0207
  -7.250  -0.2926   0.08498   0.08305  -0.0300   0.9992   0.0209
  -7.000  -0.2741   0.08108   0.07914  -0.0303   0.9958   0.0213
  -6.750  -0.2494   0.07729   0.07533  -0.0351   0.9896   0.0217
  -6.500  -0.2221   0.07337   0.07139  -0.0413   0.9803   0.0224
  -6.250  -0.1932   0.06932   0.06731  -0.0481   0.9671   0.0239
  -6.000  -0.1436   0.06378   0.06161  -0.0640   0.9462   0.0260
  -5.750  -0.1139   0.05950   0.05719  -0.0698   0.9251   0.0261
  -5.500  -0.0960   0.05360   0.05116  -0.0735   0.9021   0.0265
  -5.250  -0.0814   0.05112   0.04859  -0.0732   0.8793   0.0270
  -5.000  -0.0624   0.04895   0.04631  -0.0738   0.8573   0.0276
  -4.750  -0.0389   0.04649   0.04371  -0.0756   0.8372   0.0285
  -4.500  -0.0117   0.04370   0.04073  -0.0782   0.8187   0.0299
  -4.250   0.0326   0.04105   0.03770  -0.0826   0.8012   0.0330
  -4.000   0.0631   0.03846   0.03486  -0.0844   0.7836   0.0331
  -3.750   0.0849   0.03339   0.02962  -0.0868   0.7668   0.0343
  -3.500   0.1096   0.03169   0.02779  -0.0875   0.7477   0.0350
  -3.250   0.1364   0.03003   0.02596  -0.0884   0.7285   0.0362
  -3.000   0.1653   0.02831   0.02402  -0.0893   0.7080   0.0381
  -2.750   0.2014   0.02794   0.02322  -0.0892   0.6872   0.0418
  -2.500   0.2300   0.02396   0.01890  -0.0910   0.6686   0.0431
  -2.250   0.2565   0.02272   0.01754  -0.0916   0.6473   0.0442
  -2.000   0.2842   0.02168   0.01633  -0.0920   0.6271   0.0456
  -1.750   0.3133   0.02070   0.01513  -0.0924   0.6079   0.0484
  -1.500   0.3463   0.01961   0.01352  -0.0924   0.5899   0.0533
  -1.250   0.3739   0.01824   0.01206  -0.0930   0.5711   0.0547
  -1.000   0.4020   0.01749   0.01117  -0.0934   0.5520   0.0564
  -0.750   0.4307   0.01688   0.01037  -0.0936   0.5339   0.0593
  -0.500   0.4605   0.01796   0.01115  -0.0929   0.5160   0.0640
   0.000   0.5193   0.01531   0.00802  -0.0935   0.4857   0.0647
   0.250   0.5505   0.01220   0.00452  -0.0934   0.4737   0.0422
   0.500   0.5788   0.01158   0.00379  -0.0934   0.4607   0.0428
   0.750   0.6072   0.01124   0.00338  -0.0936   0.4488   0.0437
   1.000   0.6354   0.01115   0.00325  -0.0937   0.4377   0.0457
   1.250   0.6636   0.01111   0.00315  -0.0937   0.4272   0.0476
   1.500   0.6920   0.01104   0.00303  -0.0938   0.4171   0.0497
   1.750   0.7203   0.01101   0.00296  -0.0939   0.4079   0.0527
   2.000   0.7484   0.01104   0.00296  -0.0940   0.3988   0.0609
   2.250   0.7768   0.01101   0.00295  -0.0941   0.3898   0.0815
   2.500   0.8048   0.01107   0.00299  -0.0942   0.3814   0.0988
   2.750   0.8328   0.01113   0.00306  -0.0943   0.3734   0.1152
   3.000   0.8585   0.00985   0.00336  -0.0946   0.3669   0.8137
   3.250   0.8822   0.00965   0.00336  -0.0934   0.3603   1.0000
   3.500   0.9097   0.00987   0.00348  -0.0933   0.3540   1.0000
   3.750   0.9376   0.01001   0.00359  -0.0934   0.3478   1.0000
   4.000   0.9650   0.01022   0.00373  -0.0934   0.3415   1.0000
   4.250   0.9926   0.01039   0.00389  -0.0934   0.3352   1.0000
   4.500   1.0198   0.01059   0.00402  -0.0933   0.3267   1.0000
   4.750   1.0473   0.01074   0.00416  -0.0934   0.3182   1.0000
   5.000   1.0741   0.01098   0.00434  -0.0933   0.3106   1.0000
   5.250   1.1016   0.01112   0.00450  -0.0933   0.3037   1.0000
   5.500   1.1283   0.01134   0.00466  -0.0933   0.2933   1.0000
   5.750   1.1551   0.01155   0.00483  -0.0932   0.2831   1.0000
   6.000   1.1819   0.01175   0.00503  -0.0932   0.2727   1.0000
   6.250   1.2082   0.01200   0.00523  -0.0930   0.2589   1.0000
   6.500   1.2335   0.01238   0.00548  -0.0928   0.2381   1.0000
   6.750   1.2577   0.01291   0.00583  -0.0925   0.2053   1.0000
   7.000   1.2713   0.01485   0.00709  -0.0910   0.0976   1.0000
   7.250   1.2853   0.01668   0.00845  -0.0894   0.0225   1.0000
   7.500   1.3089   0.01719   0.00899  -0.0888   0.0188   1.0000
   7.750   1.3318   0.01775   0.00965  -0.0881   0.0174   1.0000
   8.000   1.3536   0.01840   0.01042  -0.0873   0.0163   1.0000
   8.250   1.3743   0.01915   0.01127  -0.0864   0.0154   1.0000
   8.500   1.3928   0.02008   0.01233  -0.0851   0.0148   1.0000
   8.750   1.4100   0.02105   0.01341  -0.0837   0.0144   1.0000
   9.000   1.4271   0.02195   0.01440  -0.0823   0.0142   1.0000
   9.250   1.4421   0.02296   0.01552  -0.0807   0.0138   1.0000
   9.500   1.4548   0.02405   0.01670  -0.0787   0.0133   1.0000
   9.750   1.4638   0.02527   0.01801  -0.0763   0.0129   1.0000
  10.000   1.4666   0.02660   0.01943  -0.0730   0.0126   1.0000
  10.250   1.4670   0.02817   0.02110  -0.0698   0.0124   1.0000
  10.500   1.4664   0.03003   0.02308  -0.0671   0.0122   1.0000
  10.750   1.4647   0.03226   0.02541  -0.0650   0.0121   1.0000
  11.000   1.4621   0.03488   0.02814  -0.0635   0.0120   1.0000
  11.250   1.4586   0.03788   0.03125  -0.0626   0.0118   1.0000
  11.500   1.4551   0.04110   0.03458  -0.0621   0.0118   1.0000
  11.750   1.4508   0.04458   0.03815  -0.0618   0.0117   1.0000
  12.000   1.4468   0.04808   0.04173  -0.0616   0.0116   1.0000
  12.250   1.4434   0.05153   0.04525  -0.0613   0.0115   1.0000
  12.500   1.4412   0.05477   0.04856  -0.0609   0.0115   1.0000
  12.750   1.4405   0.05776   0.05162  -0.0604   0.0115   1.0000
  13.000   1.4414   0.06049   0.05440  -0.0596   0.0115   1.0000
  13.250   1.4441   0.06307   0.05706  -0.0589   0.0116   1.0000
  13.500   1.4471   0.06571   0.05984  -0.0583   0.0119   1.0000
  13.750   1.4503   0.06826   0.06250  -0.0574   0.0121   1.0000
  14.000   1.4541   0.07066   0.06499  -0.0565   0.0121   1.0000
  14.250   1.4577   0.07322   0.06767  -0.0556   0.0124   1.0000
  14.500   1.5082   0.06996   0.06472  -0.0491   0.0210   1.0000
  14.750   1.5198   0.07173   0.06647  -0.0470   0.0201   1.0000
  15.000   1.4986   0.07783   0.07283  -0.0475   0.0184   1.0000
  15.250   1.4904   0.08207   0.07724  -0.0488   0.0181   1.0000
  15.500   1.4831   0.08645   0.08177  -0.0500   0.0178   1.0000
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