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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 200,000
Max Cl/Cd: 77.31 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe137-il-200000-n5.txt
Download as CSV file: xf-goe137-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 137 (MVA H.15) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3444   0.08791   0.08464  -0.0281   1.0000   0.0163
  -7.750  -0.3445   0.08478   0.08157  -0.0290   1.0000   0.0162
  -7.500  -0.3447   0.08147   0.07832  -0.0305   1.0000   0.0162
  -7.250  -0.3463   0.07826   0.07517  -0.0317   1.0000   0.0161
  -7.000  -0.3278   0.07240   0.06930  -0.0395   0.9928   0.0162
  -6.750  -0.3012   0.06592   0.06278  -0.0494   0.9832   0.0171
  -6.500  -0.2748   0.06448   0.06131  -0.0521   0.9761   0.0186
  -6.250  -0.2461   0.05908   0.05582  -0.0599   0.9655   0.0193
  -6.000  -0.2162   0.05273   0.04932  -0.0680   0.9539   0.0196
  -5.750  -0.1857   0.04621   0.04258  -0.0750   0.9418   0.0203
  -5.500  -0.1528   0.03746   0.03339  -0.0818   0.9297   0.0226
  -5.250  -0.1245   0.02778   0.02280  -0.0862   0.9176   0.0245
  -5.000  -0.0985   0.02621   0.02106  -0.0868   0.9039   0.0259
  -4.750  -0.0722   0.02539   0.02010  -0.0870   0.8889   0.0281
  -4.500  -0.0453   0.02278   0.01698  -0.0872   0.8731   0.0304
  -4.250  -0.0182   0.02087   0.01455  -0.0871   0.8563   0.0326
  -4.000   0.0091   0.02028   0.01357  -0.0866   0.8384   0.0343
  -3.750   0.0349   0.01783   0.01065  -0.0864   0.8211   0.0358
  -3.500   0.0612   0.01680   0.00939  -0.0861   0.8030   0.0376
  -3.250   0.0878   0.01614   0.00852  -0.0858   0.7857   0.0398
  -3.000   0.1148   0.01540   0.00753  -0.0853   0.7695   0.0408
  -2.750   0.1418   0.01477   0.00669  -0.0850   0.7544   0.0418
  -2.500   0.1689   0.01425   0.00598  -0.0846   0.7402   0.0427
  -2.250   0.1961   0.01381   0.00538  -0.0843   0.7271   0.0436
  -2.000   0.2233   0.01350   0.00494  -0.0840   0.7148   0.0454
  -1.750   0.2506   0.01323   0.00453  -0.0838   0.7035   0.0466
  -1.500   0.2781   0.01293   0.00415  -0.0836   0.6923   0.0470
  -1.250   0.3056   0.01269   0.00382  -0.0835   0.6819   0.0475
  -1.000   0.3332   0.01249   0.00352  -0.0833   0.6723   0.0484
  -0.750   0.3609   0.01229   0.00324  -0.0832   0.6624   0.0505
  -0.500   0.3886   0.01215   0.00304  -0.0831   0.6526   0.0542
  -0.250   0.4162   0.01205   0.00288  -0.0829   0.6420   0.0603
   0.000   0.4435   0.01186   0.00284  -0.0829   0.6303   0.1136
   0.250   0.4709   0.01174   0.00282  -0.0828   0.6183   0.1642
   0.500   0.4981   0.01158   0.00282  -0.0828   0.6070   0.2292
   1.000   0.5517   0.00988   0.00283  -0.0822   0.5861   1.0000
   1.250   0.5793   0.01000   0.00284  -0.0820   0.5755   1.0000
   1.500   0.6067   0.01012   0.00287  -0.0819   0.5651   1.0000
   1.750   0.6339   0.01026   0.00290  -0.0817   0.5539   1.0000
   2.000   0.6610   0.01040   0.00295  -0.0816   0.5417   1.0000
   2.250   0.6883   0.01053   0.00302  -0.0814   0.5297   1.0000
   2.500   0.7154   0.01068   0.00311  -0.0813   0.5177   1.0000
   2.750   0.7424   0.01084   0.00321  -0.0811   0.5059   1.0000
   3.000   0.7693   0.01102   0.00332  -0.0809   0.4940   1.0000
   3.250   0.7959   0.01121   0.00345  -0.0807   0.4808   1.0000
   3.500   0.8224   0.01141   0.00359  -0.0805   0.4668   1.0000
   3.750   0.8489   0.01162   0.00376  -0.0803   0.4543   1.0000
   4.000   0.8756   0.01183   0.00396  -0.0801   0.4432   1.0000
   4.250   0.9019   0.01205   0.00416  -0.0799   0.4316   1.0000
   4.500   0.9281   0.01230   0.00438  -0.0797   0.4192   1.0000
   4.750   0.9541   0.01256   0.00462  -0.0794   0.4079   1.0000
   5.000   0.9802   0.01281   0.00490  -0.0792   0.3973   1.0000
   5.250   1.0062   0.01306   0.00518  -0.0790   0.3867   1.0000
   5.500   1.0318   0.01335   0.00548  -0.0787   0.3737   1.0000
   5.750   1.0568   0.01367   0.00580  -0.0783   0.3572   1.0000
   6.000   1.0807   0.01407   0.00613  -0.0778   0.3328   1.0000
   6.250   1.1040   0.01454   0.00650  -0.0772   0.3031   1.0000
   6.500   1.1269   0.01504   0.00692  -0.0766   0.2716   1.0000
   6.750   1.1482   0.01571   0.00743  -0.0759   0.2307   1.0000
   7.000   1.1677   0.01659   0.00808  -0.0750   0.1922   1.0000
   7.250   1.1863   0.01754   0.00885  -0.0739   0.1645   1.0000
   7.500   1.2072   0.01824   0.00952  -0.0731   0.1447   1.0000
   7.750   1.2205   0.01969   0.01051  -0.0715   0.0768   1.0000
   8.000   1.2293   0.02156   0.01202  -0.0693   0.0237   1.0000
   8.250   1.2459   0.02258   0.01312  -0.0678   0.0189   1.0000
   8.500   1.2635   0.02345   0.01413  -0.0664   0.0169   1.0000
   8.750   1.2795   0.02440   0.01524  -0.0649   0.0152   1.0000
   9.000   1.2936   0.02545   0.01646  -0.0632   0.0142   1.0000
   9.250   1.3049   0.02665   0.01783  -0.0612   0.0134   1.0000
   9.500   1.3111   0.02798   0.01933  -0.0584   0.0128   1.0000
   9.750   1.3134   0.02962   0.02114  -0.0556   0.0123   1.0000
  10.000   1.3108   0.03174   0.02342  -0.0528   0.0117   1.0000
  10.250   1.3097   0.03392   0.02573  -0.0505   0.0113   1.0000
  10.500   1.3149   0.03570   0.02768  -0.0491   0.0108   1.0000
  10.750   1.3179   0.03781   0.02993  -0.0479   0.0104   1.0000
  11.000   1.3185   0.04027   0.03253  -0.0468   0.0101   1.0000
  11.250   1.3185   0.04295   0.03533  -0.0459   0.0099   1.0000
  11.500   1.3183   0.04575   0.03825  -0.0452   0.0097   1.0000
  11.750   1.3181   0.04863   0.04124  -0.0446   0.0095   1.0000
  12.000   1.3177   0.05156   0.04429  -0.0441   0.0093   1.0000
  12.250   1.3176   0.05453   0.04737  -0.0436   0.0091   1.0000
  12.500   1.3175   0.05751   0.05047  -0.0432   0.0089   1.0000
  12.750   1.3175   0.06051   0.05358  -0.0427   0.0088   1.0000
  13.000   1.3177   0.06353   0.05671  -0.0423   0.0086   1.0000
  13.250   1.3174   0.06664   0.05993  -0.0420   0.0085   1.0000
  13.500   1.3166   0.06984   0.06322  -0.0419   0.0083   1.0000
  13.750   1.3156   0.07310   0.06657  -0.0418   0.0081   1.0000
  14.000   1.3151   0.07630   0.06987  -0.0412   0.0078   1.0000
  14.250   1.3127   0.07994   0.07362  -0.0409   0.0076   1.0000
  14.500   1.3071   0.08423   0.07813  -0.0422   0.0075   1.0000
  14.750   1.3009   0.08878   0.08289  -0.0436   0.0073   1.0000
  15.000   1.2941   0.09357   0.08789  -0.0452   0.0072   1.0000
  15.250   1.2868   0.09854   0.09305  -0.0469   0.0071   1.0000
  15.500   1.2786   0.10381   0.09852  -0.0489   0.0071   1.0000
  15.750   1.2696   0.10942   0.10431  -0.0512   0.0071   1.0000
  16.000   1.2601   0.11530   0.11038  -0.0539   0.0070   1.0000
  16.250   1.2497   0.12155   0.11682  -0.0571   0.0070   1.0000
  16.500   1.2389   0.12809   0.12354  -0.0606   0.0070   1.0000
  16.750   1.2280   0.13492   0.13055  -0.0644   0.0070   1.0000
  17.000   1.2169   0.14209   0.13789  -0.0686   0.0070   1.0000
  17.250   1.2057   0.14957   0.14553  -0.0732   0.0070   1.0000
  17.500   1.1944   0.15741   0.15353  -0.0782   0.0071   1.0000
  17.750   1.1832   0.16558   0.16184  -0.0834   0.0071   1.0000
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