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GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 623 AIRFOIL (goe623-il)
Reynolds number: 200,000
Max Cl/Cd: 72.25 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe623-il-200000-n5.txt
Download as CSV file: xf-goe623-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 623 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4145   0.08779   0.08421  -0.0427   1.0000   0.0245
  -9.750  -0.4312   0.08047   0.07696  -0.0465   1.0000   0.0248
  -9.250  -0.5655   0.04144   0.03728  -0.0753   0.9839   0.0243
  -9.000  -0.5581   0.03441   0.02932  -0.0795   0.9740   0.0254
  -8.750  -0.5390   0.03136   0.02584  -0.0807   0.9653   0.0265
  -8.500  -0.5118   0.02993   0.02431  -0.0821   0.9595   0.0274
  -8.250  -0.4866   0.02833   0.02248  -0.0829   0.9520   0.0284
  -8.000  -0.4594   0.02651   0.02034  -0.0839   0.9463   0.0295
  -7.750  -0.4342   0.02502   0.01851  -0.0842   0.9383   0.0309
  -7.500  -0.4049   0.02375   0.01685  -0.0850   0.9328   0.0321
  -7.250  -0.3806   0.02213   0.01505  -0.0850   0.9246   0.0332
  -7.000  -0.3524   0.02103   0.01385  -0.0855   0.9183   0.0342
  -6.750  -0.3258   0.02024   0.01295  -0.0855   0.9106   0.0356
  -6.500  -0.2982   0.01943   0.01199  -0.0856   0.9036   0.0370
  -6.250  -0.2714   0.01862   0.01103  -0.0854   0.8959   0.0380
  -6.000  -0.2446   0.01789   0.01014  -0.0852   0.8882   0.0390
  -5.750  -0.2178   0.01732   0.00942  -0.0849   0.8805   0.0400
  -5.500  -0.1923   0.01650   0.00859  -0.0846   0.8725   0.0416
  -5.250  -0.1661   0.01595   0.00799  -0.0843   0.8644   0.0429
  -5.000  -0.1396   0.01547   0.00743  -0.0839   0.8560   0.0441
  -4.750  -0.1132   0.01505   0.00693  -0.0836   0.8474   0.0456
  -4.500  -0.0864   0.01466   0.00645  -0.0832   0.8392   0.0472
  -4.250  -0.0598   0.01431   0.00603  -0.0829   0.8302   0.0494
  -4.000  -0.0329   0.01395   0.00562  -0.0826   0.8218   0.0529
  -3.750  -0.0062   0.01366   0.00528  -0.0823   0.8116   0.0571
  -3.500   0.0207   0.01333   0.00494  -0.0820   0.8024   0.0647
  -3.250   0.0475   0.01300   0.00462  -0.0817   0.7926   0.0806
  -3.000   0.0742   0.01270   0.00445  -0.0815   0.7826   0.1105
  -2.750   0.1017   0.01257   0.00429  -0.0813   0.7726   0.1376
  -2.500   0.1288   0.01242   0.00414  -0.0811   0.7612   0.1558
  -2.250   0.1561   0.01228   0.00398  -0.0809   0.7500   0.1711
  -2.000   0.1833   0.01213   0.00382  -0.0807   0.7393   0.1872
  -1.750   0.2105   0.01199   0.00367  -0.0805   0.7281   0.2025
  -1.500   0.2375   0.01183   0.00357  -0.0803   0.7163   0.2279
  -1.000   0.2903   0.01131   0.00340  -0.0799   0.6949   0.3553
  -0.750   0.3148   0.01084   0.00337  -0.0793   0.6842   0.4856
  -0.500   0.3371   0.01033   0.00340  -0.0780   0.6743   0.6483
   0.000   0.3896   0.00993   0.00349  -0.0759   0.6548   0.8915
   0.250   0.4295   0.00998   0.00345  -0.0782   0.6428   0.9511
   0.500   0.4682   0.01007   0.00340  -0.0804   0.6307   0.9843
   0.750   0.5046   0.01018   0.00337  -0.0822   0.6193   1.0000
   1.000   0.5295   0.01030   0.00339  -0.0816   0.6081   1.0000
   1.250   0.5545   0.01043   0.00341  -0.0810   0.5967   1.0000
   1.500   0.5796   0.01058   0.00344  -0.0804   0.5856   1.0000
   1.750   0.6050   0.01071   0.00349  -0.0800   0.5749   1.0000
   2.000   0.6307   0.01084   0.00356  -0.0795   0.5654   1.0000
   2.250   0.6563   0.01099   0.00363  -0.0791   0.5562   1.0000
   2.500   0.6822   0.01112   0.00374  -0.0787   0.5469   1.0000
   2.750   0.7079   0.01128   0.00383  -0.0783   0.5380   1.0000
   3.000   0.7339   0.01142   0.00395  -0.0779   0.5286   1.0000
   3.250   0.7597   0.01158   0.00407  -0.0775   0.5193   1.0000
   3.500   0.7853   0.01175   0.00420  -0.0771   0.5085   1.0000
   3.750   0.8109   0.01191   0.00434  -0.0767   0.4965   1.0000
   4.000   0.8363   0.01208   0.00450  -0.0763   0.4840   1.0000
   4.250   0.8616   0.01227   0.00466  -0.0758   0.4708   1.0000
   4.500   0.8865   0.01247   0.00483  -0.0753   0.4561   1.0000
   4.750   0.9112   0.01269   0.00502  -0.0748   0.4390   1.0000
   5.000   0.9351   0.01295   0.00522  -0.0741   0.4186   1.0000
   5.250   0.9581   0.01326   0.00545  -0.0733   0.3949   1.0000
   5.750   1.0018   0.01408   0.00605  -0.0714   0.3461   1.0000
   6.000   1.0232   0.01454   0.00642  -0.0705   0.3263   1.0000
   6.250   1.0447   0.01501   0.00682  -0.0696   0.3095   1.0000
   6.500   1.0662   0.01546   0.00723  -0.0687   0.2947   1.0000
   6.750   1.0879   0.01591   0.00766  -0.0678   0.2818   1.0000
   7.000   1.1094   0.01637   0.00811  -0.0669   0.2707   1.0000
   7.250   1.1301   0.01687   0.00859  -0.0659   0.2609   1.0000
   7.500   1.1513   0.01733   0.00907  -0.0650   0.2517   1.0000
   7.750   1.1717   0.01782   0.00957  -0.0640   0.2439   1.0000
   8.000   1.1922   0.01831   0.01008  -0.0629   0.2366   1.0000
   8.250   1.2117   0.01884   0.01064  -0.0618   0.2297   1.0000
   8.500   1.2314   0.01933   0.01118  -0.0607   0.2222   1.0000
   8.750   1.2494   0.01991   0.01176  -0.0594   0.2155   1.0000
   9.000   1.2682   0.02041   0.01232  -0.0582   0.2079   1.0000
   9.250   1.2832   0.02101   0.01294  -0.0564   0.2006   1.0000
   9.500   1.2994   0.02155   0.01354  -0.0549   0.1920   1.0000
   9.750   1.3141   0.02219   0.01421  -0.0532   0.1837   1.0000
  10.000   1.3273   0.02291   0.01494  -0.0514   0.1739   1.0000
  10.250   1.3428   0.02356   0.01567  -0.0500   0.1644   1.0000
  10.500   1.3560   0.02436   0.01652  -0.0484   0.1558   1.0000
  10.750   1.3685   0.02523   0.01742  -0.0469   0.1453   1.0000
  11.000   1.3809   0.02615   0.01839  -0.0454   0.1320   1.0000
  11.250   1.3891   0.02741   0.01960  -0.0437   0.1076   1.0000
  11.500   1.3813   0.02997   0.02180  -0.0409   0.0664   1.0000
  11.750   1.3789   0.03228   0.02403  -0.0388   0.0523   1.0000
  12.000   1.3803   0.03436   0.02616  -0.0372   0.0433   1.0000
  12.250   1.3822   0.03647   0.02835  -0.0358   0.0366   1.0000
  12.500   1.3834   0.03874   0.03069  -0.0346   0.0318   1.0000
  12.750   1.3837   0.04117   0.03319  -0.0335   0.0282   1.0000
  13.000   1.3841   0.04367   0.03580  -0.0327   0.0257   1.0000
  13.250   1.3834   0.04639   0.03862  -0.0321   0.0237   1.0000
  13.500   1.3799   0.04951   0.04184  -0.0317   0.0224   1.0000
  13.750   1.3770   0.05268   0.04514  -0.0315   0.0213   1.0000
  14.000   1.3733   0.05607   0.04868  -0.0315   0.0205   1.0000
  14.250   1.3683   0.05973   0.05248  -0.0317   0.0198   1.0000
  14.500   1.3619   0.06370   0.05659  -0.0322   0.0191   1.0000
  14.750   1.3541   0.06801   0.06103  -0.0329   0.0186   1.0000
  15.000   1.3443   0.07270   0.06583  -0.0339   0.0182   1.0000
  15.250   1.3325   0.07782   0.07110  -0.0351   0.0178   1.0000
  15.500   1.3215   0.08297   0.07637  -0.0365   0.0174   1.0000
  15.750   1.3124   0.08792   0.08147  -0.0378   0.0171   1.0000
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