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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 1,000,000
Max Cl/Cd: 53.37 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe411-il-1000000-n5.txt
Download as CSV file: xf-goe411-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7132   0.09547   0.09361  -0.0331   1.0000   0.0017
 -14.000  -0.7270   0.08845   0.08653  -0.0374   1.0000   0.0017
 -13.750  -0.7487   0.08037   0.07833  -0.0422   1.0000   0.0017
 -13.500  -0.7707   0.07305   0.07087  -0.0465   1.0000   0.0017
 -13.250  -0.7916   0.06663   0.06432  -0.0498   1.0000   0.0017
 -13.000  -0.8196   0.05973   0.05723  -0.0526   1.0000   0.0017
 -12.750  -0.8278   0.05643   0.05385  -0.0537   1.0000   0.0016
 -12.500  -0.8546   0.05094   0.04815  -0.0540   1.0000   0.0017
 -12.250  -0.8752   0.04684   0.04386  -0.0529   1.0000   0.0017
 -12.000  -0.9034   0.04165   0.03839  -0.0500   1.0000   0.0018
 -11.750  -0.9122   0.03977   0.03639  -0.0476   1.0000   0.0016
 -11.500  -0.9361   0.03502   0.03130  -0.0427   1.0000   0.0018
 -11.250  -0.9605   0.02914   0.02495  -0.0367   1.0000   0.0020
 -11.000  -0.9580   0.02797   0.02365  -0.0335   1.0000   0.0021
 -10.750  -0.9616   0.02633   0.02185  -0.0292   1.0000   0.0021
 -10.500  -0.9654   0.02484   0.02021  -0.0245   1.0000   0.0021
 -10.250  -0.9682   0.02376   0.01900  -0.0197   1.0000   0.0022
 -10.000  -0.9598   0.02269   0.01783  -0.0172   0.9993   0.0023
  -9.750  -0.9458   0.02094   0.01589  -0.0159   0.9974   0.0023
  -9.500  -0.9243   0.02019   0.01507  -0.0157   0.9956   0.0024
  -9.250  -0.9032   0.01954   0.01436  -0.0152   0.9936   0.0024
  -9.000  -0.8831   0.01873   0.01347  -0.0145   0.9912   0.0025
  -8.750  -0.8591   0.01789   0.01256  -0.0145   0.9890   0.0026
  -8.500  -0.8332   0.01693   0.01152  -0.0150   0.9872   0.0027
  -8.250  -0.8053   0.01661   0.01118  -0.0156   0.9845   0.0030
  -8.000  -0.7837   0.01561   0.01007  -0.0150   0.9808   0.0031
  -7.750  -0.7575   0.01482   0.00920  -0.0153   0.9787   0.0033
  -7.500  -0.7337   0.01423   0.00852  -0.0150   0.9755   0.0034
  -7.250  -0.7098   0.01361   0.00783  -0.0146   0.9717   0.0036
  -7.000  -0.6842   0.01284   0.00699  -0.0146   0.9693   0.0040
  -6.750  -0.6596   0.01236   0.00646  -0.0143   0.9654   0.0042
  -6.500  -0.6318   0.01201   0.00610  -0.0147   0.9613   0.0046
  -6.250  -0.5997   0.01160   0.00566  -0.0160   0.9589   0.0051
  -6.000  -0.5724   0.01122   0.00523  -0.0161   0.9532   0.0054
  -5.750  -0.5405   0.01079   0.00475  -0.0174   0.9487   0.0061
  -5.500  -0.5117   0.01044   0.00438  -0.0179   0.9425   0.0071
  -5.250  -0.4795   0.01012   0.00402  -0.0191   0.9366   0.0078
  -5.000  -0.4502   0.00987   0.00373  -0.0197   0.9285   0.0087
  -4.750  -0.4196   0.00959   0.00339  -0.0205   0.9201   0.0103
  -4.500  -0.3897   0.00935   0.00310  -0.0211   0.9094   0.0137
  -4.250  -0.3616   0.00918   0.00287  -0.0214   0.8960   0.0164
  -4.000  -0.3393   0.00873   0.00252  -0.0204   0.8809   0.0700
  -3.750  -0.3215   0.00814   0.00219  -0.0187   0.8637   0.1464
  -3.500  -0.2989   0.00792   0.00202  -0.0177   0.8481   0.1726
  -3.250  -0.2780   0.00766   0.00185  -0.0165   0.8323   0.2098
  -3.000  -0.2595   0.00728   0.00166  -0.0147   0.8167   0.2688
  -2.750  -0.2411   0.00694   0.00150  -0.0130   0.8008   0.3294
  -2.500  -0.2198   0.00678   0.00141  -0.0117   0.7846   0.3645
  -2.000  -0.1756   0.00668   0.00127  -0.0094   0.7402   0.4005
  -1.750  -0.1556   0.00671   0.00121  -0.0077   0.7016   0.4173
  -1.500  -0.1351   0.00679   0.00117  -0.0062   0.6647   0.4299
  -1.250  -0.1141   0.00685   0.00115  -0.0048   0.6322   0.4439
  -1.000  -0.0912   0.00688   0.00113  -0.0039   0.6102   0.4576
  -0.500  -0.0447   0.00694   0.00111  -0.0021   0.5697   0.4830
  -0.250  -0.0220   0.00694   0.00110  -0.0011   0.5487   0.5023
   0.000  -0.0001   0.00695   0.00110   0.0000   0.5233   0.5245
   0.250   0.0218   0.00695   0.00111   0.0012   0.5009   0.5485
   0.500   0.0447   0.00693   0.00111   0.0021   0.4836   0.5705
   0.750   0.0683   0.00692   0.00112   0.0029   0.4702   0.5886
   1.000   0.0912   0.00689   0.00113   0.0039   0.4567   0.6093
   1.250   0.1140   0.00685   0.00115   0.0049   0.4438   0.6327
   1.500   0.1351   0.00678   0.00117   0.0062   0.4302   0.6652
   1.750   0.1550   0.00671   0.00121   0.0079   0.4154   0.7052
   2.000   0.1757   0.00668   0.00127   0.0093   0.4008   0.7395
   2.500   0.2199   0.00677   0.00141   0.0117   0.3650   0.7846
   2.750   0.2402   0.00699   0.00151   0.0131   0.3210   0.8008
   3.000   0.2592   0.00731   0.00167   0.0148   0.2646   0.8163
   3.250   0.2777   0.00769   0.00185   0.0165   0.2059   0.8319
   3.500   0.2990   0.00792   0.00201   0.0177   0.1729   0.8479
   3.750   0.3215   0.00814   0.00219   0.0187   0.1462   0.8638
   4.250   0.3615   0.00918   0.00287   0.0214   0.0163   0.8958
   4.500   0.3897   0.00935   0.00310   0.0211   0.0135   0.9093
   4.750   0.4195   0.00960   0.00340   0.0205   0.0105   0.9200
   5.000   0.4506   0.00987   0.00373   0.0196   0.0088   0.9291
   5.250   0.4797   0.01012   0.00401   0.0191   0.0076   0.9367
   5.500   0.5117   0.01043   0.00436   0.0179   0.0070   0.9422
   5.750   0.5399   0.01086   0.00483   0.0175   0.0058   0.9487
   6.000   0.5729   0.01119   0.00520   0.0160   0.0053   0.9532
   6.250   0.5999   0.01157   0.00562   0.0159   0.0049   0.9589
   6.500   0.6325   0.01197   0.00604   0.0145   0.0045   0.9613
   6.750   0.6590   0.01243   0.00655   0.0145   0.0043   0.9656
   7.000   0.6847   0.01283   0.00698   0.0145   0.0040   0.9694
   7.250   0.7103   0.01359   0.00781   0.0145   0.0037   0.9718
   7.500   0.7319   0.01434   0.00865   0.0153   0.0036   0.9758
   7.750   0.7566   0.01493   0.00933   0.0154   0.0034   0.9788
   8.000   0.7848   0.01551   0.00996   0.0148   0.0031   0.9808
   8.250   0.8059   0.01656   0.01112   0.0155   0.0030   0.9845
   8.500   0.8315   0.01718   0.01180   0.0153   0.0028   0.9873
   8.750   0.8607   0.01775   0.01240   0.0142   0.0026   0.9889
   9.000   0.8819   0.01889   0.01365   0.0146   0.0026   0.9913
   9.250   0.9049   0.01941   0.01422   0.0149   0.0024   0.9935
   9.500   0.9239   0.02029   0.01518   0.0157   0.0024   0.9956
   9.750   0.9467   0.02091   0.01585   0.0157   0.0023   0.9974
  10.000   0.9611   0.02259   0.01772   0.0170   0.0023   0.9993
  10.250   0.9650   0.02406   0.01933   0.0202   0.0021   1.0000
  10.500   0.9618   0.02526   0.02066   0.0251   0.0021   1.0000
  10.750   0.9650   0.02599   0.02148   0.0287   0.0020   1.0000
  11.000   0.9635   0.02742   0.02306   0.0328   0.0020   1.0000
  11.250   0.9554   0.02982   0.02568   0.0373   0.0020   1.0000
  11.500   0.9486   0.03245   0.02854   0.0412   0.0019   1.0000
  11.750   0.9113   0.03987   0.03650   0.0476   0.0017   1.0000
  12.000   0.9072   0.04115   0.03786   0.0497   0.0018   1.0000
  12.250   0.8724   0.04727   0.04431   0.0530   0.0017   1.0000
  12.500   0.8568   0.05078   0.04797   0.0539   0.0017   1.0000
  12.750   0.8360   0.05536   0.05273   0.0537   0.0017   1.0000
  13.000   0.8170   0.06031   0.05783   0.0524   0.0016   1.0000
  13.250   0.7972   0.06592   0.06358   0.0500   0.0017   1.0000
  13.500   0.7775   0.07209   0.06989   0.0468   0.0017   1.0000
  13.750   0.7488   0.08067   0.07863   0.0419   0.0016   1.0000
  14.000   0.7399   0.08597   0.08399   0.0385   0.0017   1.0000
  14.250   0.7101   0.09664   0.09480   0.0322   0.0017   1.0000
  14.500   0.6953   0.10449   0.10273   0.0275   0.0018   1.0000
  14.750   0.6799   0.11305   0.11133   0.0227   0.0018   1.0000
  15.000   0.6637   0.12229   0.12062   0.0181   0.0019   1.0000
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