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GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 200,000
Max Cl/Cd: 60.91 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe114-il-200000.txt
Download as CSV file: xf-goe114-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 114 (MVA MK.1) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3872   0.08887   0.08562  -0.0451   1.0000   0.0349
  -8.500  -0.3886   0.08617   0.08297  -0.0450   1.0000   0.0365
  -8.250  -0.3944   0.08326   0.08013  -0.0449   1.0000   0.0377
  -8.000  -0.4047   0.08068   0.07764  -0.0440   1.0000   0.0382
  -7.750  -0.4233   0.07885   0.07592  -0.0413   1.0000   0.0384
  -7.500  -0.4502   0.07801   0.07519  -0.0366   1.0000   0.0376
  -7.250  -0.4734   0.07647   0.07374  -0.0337   1.0000   0.0370
  -7.000  -0.4576   0.06932   0.06659  -0.0444   0.9947   0.0391
  -6.750  -0.4335   0.05681   0.05388  -0.0633   0.9862   0.0402
  -6.500  -0.4120   0.04694   0.04295  -0.0792   0.9758   0.0445
  -6.250  -0.3876   0.04324   0.03959  -0.0808   0.9725   0.0515
  -4.500  -0.1569   0.02042   0.01343  -0.0952   0.9424   0.0380
  -4.000  -0.0898   0.01771   0.01038  -0.0957   0.9325   0.0280
  -3.750  -0.0520   0.01647   0.00907  -0.0975   0.9299   0.0299
  -3.500  -0.0247   0.01569   0.00821  -0.0973   0.9231   0.0315
  -3.250   0.0092   0.01480   0.00711  -0.0984   0.9187   0.0318
  -3.000   0.0466   0.01407   0.00607  -0.1000   0.9157   0.0351
  -2.750   0.0718   0.01354   0.00546  -0.0993   0.9077   0.0621
  -2.500   0.1034   0.01279   0.00558  -0.1004   0.9035   0.3299
  -2.250   0.1302   0.01311   0.00576  -0.1000   0.8960   0.3596
  -2.000   0.1604   0.01337   0.00607  -0.1003   0.8908   0.3952
  -1.750   0.1870   0.01338   0.00603  -0.1000   0.8837   0.4111
  -1.500   0.2172   0.01315   0.00571  -0.1004   0.8780   0.4172
  -1.250   0.2447   0.01304   0.00554  -0.1003   0.8711   0.4241
  -1.000   0.2736   0.01285   0.00532  -0.1005   0.8648   0.4300
  -0.750   0.3007   0.01274   0.00520  -0.1003   0.8576   0.4370
  -0.500   0.3292   0.01257   0.00503  -0.1004   0.8510   0.4437
  -0.250   0.3556   0.01248   0.00495  -0.1001   0.8433   0.4498
   0.000   0.3844   0.01232   0.00478  -0.1002   0.8369   0.4557
   0.250   0.4102   0.01223   0.00476  -0.0998   0.8284   0.4615
   0.500   0.4394   0.01209   0.00463  -0.0999   0.8224   0.4685
   0.750   0.4643   0.01202   0.00466  -0.0994   0.8131   0.4762
   1.000   0.4913   0.01191   0.00468  -0.0992   0.8054   0.4845
   1.250   0.5168   0.01165   0.00447  -0.0982   0.7904   0.4946
   1.500   0.5396   0.01113   0.00393  -0.0961   0.7611   0.5067
   1.750   0.5645   0.01091   0.00385  -0.0952   0.7451   0.5238
   2.000   0.5877   0.01064   0.00378  -0.0939   0.7238   0.5553
   2.250   0.6018   0.00988   0.00340  -0.0900   0.6560   0.7180
   2.500   0.6328   0.01048   0.00341  -0.0902   0.4684   1.0000
   2.750   0.6209   0.01363   0.00455  -0.0839   0.0527   1.0000
   3.000   0.6433   0.01413   0.00503  -0.0827   0.0350   1.0000
   3.250   0.6651   0.01469   0.00574  -0.0813   0.0308   1.0000
   3.500   0.6860   0.01528   0.00645  -0.0799   0.0263   1.0000
   3.750   0.7049   0.01603   0.00735  -0.0781   0.0260   1.0000
   4.000   0.7210   0.01699   0.00839  -0.0758   0.0264   1.0000
   4.250   0.7358   0.01810   0.00954  -0.0733   0.0277   1.0000
   4.500   0.7507   0.01950   0.01098  -0.0708   0.0296   1.0000
   4.750   0.7720   0.02098   0.01239  -0.0693   0.0322   1.0000
   5.000   0.8003   0.02173   0.01331  -0.0681   0.0396   1.0000
   6.500   0.9841   0.03466   0.02722  -0.0644   0.0514   1.0000
   6.750   0.9963   0.03757   0.03041  -0.0627   0.0398   1.0000
   7.000   1.0125   0.03997   0.03293  -0.0614   0.0337   1.0000
   7.250   1.0209   0.04304   0.03642  -0.0586   0.0284   1.0000
   7.500   1.0337   0.04499   0.03870  -0.0560   0.0253   1.0000
   7.750   1.0440   0.04799   0.04189  -0.0541   0.0230   1.0000
   8.000   1.0559   0.05291   0.04681  -0.0535   0.0214   1.0000
   8.250   1.0497   0.06217   0.05634  -0.0513   0.0202   1.0000
   8.500   1.0502   0.06424   0.05874  -0.0480   0.0201   1.0000
   8.750   1.0475   0.06457   0.05945  -0.0438   0.0196   1.0000
   9.000   1.0455   0.06571   0.06091  -0.0400   0.0189   1.0000
   9.250   1.0396   0.06796   0.06341  -0.0365   0.0184   1.0000
   9.500   1.0282   0.07042   0.06607  -0.0328   0.0181   1.0000
   9.750   1.0135   0.07313   0.06894  -0.0295   0.0179   1.0000
  10.000   0.9979   0.07621   0.07218  -0.0272   0.0178   1.0000
  10.250   0.9809   0.07974   0.07585  -0.0259   0.0178   1.0000
  10.500   0.9633   0.08374   0.07998  -0.0255   0.0179   1.0000
  10.750   0.9444   0.08832   0.08469  -0.0262   0.0179   1.0000
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