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GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 438 AIRFOIL (goe438-il)
Reynolds number: 100,000
Max Cl/Cd: 49.25 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe438-il-100000.txt
Download as CSV file: xf-goe438-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 438 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3395   0.09705   0.09199  -0.0333   1.0000   0.1180
  -8.500  -0.3707   0.09633   0.09144  -0.0353   1.0000   0.1207
  -8.250  -0.4063   0.09549   0.09077  -0.0359   1.0000   0.1212
  -8.000  -0.3601   0.08938   0.08457  -0.0316   1.0000   0.1256
  -7.750  -0.3605   0.08739   0.08264  -0.0295   1.0000   0.1297
  -7.500  -0.3798   0.08599   0.08136  -0.0271   1.0000   0.1325
  -7.250  -0.4078   0.08453   0.08002  -0.0267   1.0000   0.1352
  -7.000  -0.4538   0.08344   0.07884  -0.0320   1.0000   0.1373
  -6.750  -0.4387   0.07894   0.07452  -0.0263   1.0000   0.1394
  -6.500  -0.4326   0.07694   0.07258  -0.0221   1.0000   0.1424
  -6.250  -0.4356   0.07488   0.07054  -0.0204   1.0000   0.1466
  -6.000  -0.4544   0.07141   0.06688  -0.0262   1.0000   0.1546
  -5.750  -0.4476   0.06898   0.06459  -0.0217   1.0000   0.1570
  -5.500  -0.4440   0.06720   0.06285  -0.0191   1.0000   0.1618
  -5.250  -0.4455   0.06391   0.05938  -0.0222   1.0000   0.1721
  -5.000  -0.4116   0.06111   0.05651  -0.0259   0.9936   0.1841
  -4.750  -0.3803   0.05747   0.05285  -0.0293   0.9856   0.1945
  -4.500  -0.3464   0.05436   0.04962  -0.0338   0.9766   0.2117
  -4.250  -0.3095   0.05135   0.04636  -0.0400   0.9672   0.2384
  -4.000  -0.2768   0.04865   0.04365  -0.0424   0.9582   0.2565
  -3.750  -0.2468   0.04655   0.04157  -0.0436   0.9482   0.2785
  -3.500  -0.2095   0.04435   0.03935  -0.0462   0.9410   0.3126
  -3.250  -0.1386   0.03543   0.02792  -0.0585   0.9300   0.1533
  -3.000  -0.0949   0.03220   0.02464  -0.0621   0.9241   0.1478
  -2.750  -0.0580   0.03048   0.02214  -0.0630   0.9129   0.1368
  -2.500  -0.0201   0.02854   0.02003  -0.0648   0.9039   0.1346
  -2.250   0.0244   0.02694   0.01818  -0.0675   0.8962   0.1331
  -2.000   0.0613   0.02589   0.01689  -0.0687   0.8859   0.1345
  -1.750   0.1116   0.02468   0.01544  -0.0722   0.8798   0.1365
  -1.500   0.1488   0.02376   0.01438  -0.0733   0.8694   0.1373
  -1.250   0.1969   0.02226   0.01292  -0.0764   0.8635   0.1401
  -1.000   0.2299   0.02148   0.01219  -0.0768   0.8519   0.1442
  -0.750   0.2770   0.02050   0.01119  -0.0794   0.8458   0.1525
  -0.500   0.3053   0.01977   0.01060  -0.0789   0.8327   0.1589
  -0.250   0.3358   0.01919   0.01005  -0.0786   0.8202   0.1680
   0.000   0.3691   0.01847   0.00942  -0.0787   0.8092   0.1846
   0.250   0.4020   0.01711   0.00880  -0.0792   0.7979   0.3278
   0.500   0.5008   0.01510   0.00816  -0.0913   0.7848   1.0000
   0.750   0.5258   0.01508   0.00797  -0.0901   0.7688   1.0000
   1.000   0.5506   0.01507   0.00780  -0.0889   0.7524   1.0000
   1.250   0.5751   0.01507   0.00765  -0.0876   0.7357   1.0000
   1.500   0.5998   0.01508   0.00751  -0.0863   0.7188   1.0000
   1.750   0.6247   0.01511   0.00739  -0.0852   0.7017   1.0000
   2.000   0.6492   0.01520   0.00731  -0.0840   0.6843   1.0000
   2.250   0.6721   0.01537   0.00737  -0.0826   0.6656   1.0000
   2.500   0.6956   0.01558   0.00745  -0.0813   0.6473   1.0000
   2.750   0.7193   0.01585   0.00758  -0.0801   0.6295   1.0000
   3.000   0.7428   0.01617   0.00776  -0.0790   0.6121   1.0000
   3.250   0.7661   0.01651   0.00800  -0.0778   0.5952   1.0000
   3.500   0.7892   0.01688   0.00827  -0.0767   0.5792   1.0000
   3.750   0.8124   0.01725   0.00856  -0.0756   0.5642   1.0000
   4.000   0.8356   0.01762   0.00886  -0.0746   0.5499   1.0000
   4.250   0.8595   0.01798   0.00914  -0.0736   0.5367   1.0000
   4.500   0.8834   0.01835   0.00944  -0.0727   0.5242   1.0000
   4.750   0.9053   0.01876   0.00988  -0.0715   0.5115   1.0000
   5.000   0.9281   0.01919   0.01029  -0.0705   0.4997   1.0000
   5.250   0.9530   0.01960   0.01063  -0.0698   0.4895   1.0000
   5.500   0.9759   0.02005   0.01111  -0.0688   0.4787   1.0000
   5.750   0.9982   0.02056   0.01165  -0.0678   0.4682   1.0000
   6.000   1.0237   0.02100   0.01201  -0.0673   0.4586   1.0000
   6.250   1.0453   0.02141   0.01246  -0.0660   0.4468   1.0000
   6.500   1.0661   0.02182   0.01290  -0.0647   0.4343   1.0000
   6.750   1.0881   0.02221   0.01327  -0.0636   0.4223   1.0000
   7.000   1.1125   0.02259   0.01356  -0.0628   0.4113   1.0000
   7.250   1.1322   0.02308   0.01417  -0.0614   0.4004   1.0000
   7.500   1.1540   0.02365   0.01481  -0.0604   0.3911   1.0000
   7.750   1.1783   0.02412   0.01523  -0.0597   0.3817   1.0000
   8.000   1.1961   0.02467   0.01596  -0.0581   0.3712   1.0000
   8.250   1.2177   0.02513   0.01643  -0.0570   0.3609   1.0000
   8.500   1.2393   0.02553   0.01684  -0.0559   0.3506   1.0000
   8.750   1.2561   0.02609   0.01759  -0.0541   0.3403   1.0000
   9.000   1.2783   0.02658   0.01809  -0.0532   0.3311   1.0000
   9.250   1.2957   0.02697   0.01858  -0.0515   0.3200   1.0000
   9.500   1.3099   0.02739   0.01915  -0.0492   0.3081   1.0000
   9.750   1.3254   0.02777   0.01962  -0.0473   0.2965   1.0000
  10.000   1.3406   0.02809   0.01998  -0.0452   0.2843   1.0000
  10.250   1.3530   0.02840   0.02034  -0.0427   0.2712   1.0000
  10.500   1.3588   0.02879   0.02087  -0.0393   0.2566   1.0000
  10.750   1.3605   0.02926   0.02142  -0.0353   0.2403   1.0000
  11.000   1.3547   0.02992   0.02218  -0.0303   0.2225   1.0000
  11.250   1.3467   0.03088   0.02316  -0.0255   0.2023   1.0000
  11.500   1.3384   0.03229   0.02441  -0.0213   0.1831   1.0000
  11.750   1.3309   0.03411   0.02620  -0.0178   0.1644   1.0000
  12.000   1.3250   0.03612   0.02813  -0.0150   0.1500   1.0000
  12.250   1.3211   0.03825   0.03017  -0.0127   0.1389   1.0000
  12.500   1.3187   0.04043   0.03226  -0.0108   0.1296   1.0000
  12.750   1.3178   0.04270   0.03462  -0.0093   0.1212   1.0000
  13.000   1.3186   0.04498   0.03681  -0.0079   0.1140   1.0000
  13.250   1.3181   0.04739   0.03935  -0.0068   0.1074   1.0000
  13.500   1.3214   0.04969   0.04161  -0.0057   0.1013   1.0000
  13.750   1.3195   0.05239   0.04448  -0.0049   0.0957   1.0000
  14.000   1.3248   0.05467   0.04665  -0.0040   0.0898   1.0000
  14.250   1.3198   0.05785   0.05008  -0.0036   0.0854   1.0000
  14.500   1.3302   0.05985   0.05185  -0.0028   0.0793   1.0000
  14.750   1.3235   0.06345   0.05577  -0.0026   0.0763   1.0000
  15.000   1.3230   0.06655   0.05899  -0.0025   0.0727   1.0000
  15.250   1.3385   0.06868   0.06100  -0.0015   0.0681   1.0000
  15.500   1.3281   0.07289   0.06550  -0.0019   0.0664   1.0000
  15.750   1.3199   0.07711   0.06997  -0.0025   0.0645   1.0000
  16.000   1.3132   0.08125   0.07428  -0.0032   0.0625   1.0000
  16.250   1.3188   0.08437   0.07743  -0.0032   0.0604   1.0000
  16.500   1.3201   0.08886   0.08201  -0.0033   0.0587   1.0000
  16.750   1.2973   0.09499   0.08842  -0.0058   0.0585   1.0000
  17.000   1.2747   0.10160   0.09529  -0.0088   0.0584   1.0000
  17.250   1.2502   0.10902   0.10297  -0.0126   0.0585   1.0000
  17.500   1.2234   0.11727   0.11144  -0.0173   0.0586   1.0000
  17.750   1.1958   0.12632   0.12069  -0.0226   0.0589   1.0000
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