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GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 200,000
Max Cl/Cd: 86.74 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe233-il-200000.txt
Download as CSV file: xf-goe233-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 233 (MVA CA4) 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2379   0.13882   0.13514  -0.0443   1.0000   0.0458
 -11.750  -0.2576   0.13864   0.13506  -0.0446   1.0000   0.0470
 -11.500  -0.2759   0.13830   0.13481  -0.0428   1.0000   0.0472
 -11.250  -0.2633   0.13483   0.13135  -0.0390   1.0000   0.0478
 -11.000  -0.2668   0.13391   0.13048  -0.0357   1.0000   0.0485
 -10.750  -0.2496   0.13064   0.12720  -0.0384   0.9979   0.0501
 -10.500  -0.2348   0.12683   0.12338  -0.0441   0.9951   0.0540
 -10.250  -0.2258   0.12232   0.11888  -0.0505   0.9917   0.0554
 -10.000  -0.2008   0.11865   0.11519  -0.0515   0.9892   0.0569
  -9.750  -0.1807   0.11521   0.11173  -0.0550   0.9862   0.0592
  -9.500  -0.1745   0.11218   0.10869  -0.0660   0.9816   0.0635
  -9.250  -0.1594   0.10717   0.10369  -0.0688   0.9771   0.0644
  -9.000  -0.1309   0.10344   0.09994  -0.0691   0.9751   0.0659
  -8.750  -0.1068   0.10020   0.09668  -0.0725   0.9724   0.0689
  -8.500  -0.1024   0.09756   0.09405  -0.0858   0.9628   0.0741
  -8.250  -0.0802   0.09215   0.08863  -0.0868   0.9605   0.0753
  -8.000  -0.0516   0.08874   0.08519  -0.0877   0.9583   0.0768
  -7.750  -0.0268   0.08557   0.08199  -0.0910   0.9550   0.0793
  -7.500  -0.0145   0.08293   0.07935  -0.0934   0.9454   0.0824
  -7.250  -0.0167   0.07894   0.07539  -0.1061   0.9292   0.0865
  -7.000   0.0024   0.07609   0.07252  -0.1026   0.9255   0.0878
  -6.750   0.0768   0.02930   0.02438  -0.1909   0.9091   0.0556
  -6.500   0.1300   0.02553   0.01997  -0.2006   0.9060   0.0549
  -6.250   0.1637   0.02313   0.01733  -0.2038   0.8983   0.0558
  -6.000   0.1983   0.02156   0.01558  -0.2060   0.8929   0.0567
  -5.750   0.2335   0.02015   0.01397  -0.2078   0.8888   0.0571
  -5.500   0.2628   0.01925   0.01295  -0.2084   0.8801   0.0578
  -5.250   0.2945   0.01838   0.01198  -0.2090   0.8745   0.0587
  -5.000   0.3246   0.01774   0.01128  -0.2094   0.8675   0.0600
  -4.750   0.3549   0.01721   0.01065  -0.2097   0.8604   0.0621
  -4.500   0.3862   0.01666   0.01002  -0.2101   0.8552   0.0643
  -4.250   0.4159   0.01623   0.00962  -0.2105   0.8463   0.0671
  -4.000   0.4475   0.01578   0.00908  -0.2110   0.8403   0.0711
  -3.750   0.4788   0.01534   0.00861  -0.2118   0.8317   0.0778
  -3.500   0.5137   0.01446   0.00776  -0.2136   0.8249   0.1077
  -3.250   0.5463   0.01381   0.00725  -0.2150   0.8175   0.1883
  -3.000   0.5751   0.01380   0.00733  -0.2149   0.8100   0.2306
  -2.750   0.6035   0.01395   0.00743  -0.2145   0.8040   0.2542
  -2.500   0.6307   0.01422   0.00767  -0.2140   0.7958   0.2702
  -2.250   0.6584   0.01453   0.00790  -0.2134   0.7899   0.2845
  -2.000   0.6859   0.01485   0.00814  -0.2130   0.7824   0.2972
  -1.750   0.7115   0.01538   0.00873  -0.2118   0.7758   0.3031
  -1.500   0.7394   0.01569   0.00895  -0.2113   0.7702   0.3142
  -1.250   0.7645   0.01618   0.00952  -0.2102   0.7625   0.3190
  -1.000   0.7930   0.01637   0.00958  -0.2099   0.7567   0.3299
  -0.750   0.8164   0.01702   0.01038  -0.2083   0.7500   0.3351
  -0.500   0.8447   0.01719   0.01047  -0.2082   0.7435   0.3467
  -0.250   0.8711   0.01741   0.01069  -0.2073   0.7385   0.3507
   0.000   0.9004   0.01745   0.01064  -0.2077   0.7310   0.3618
   0.250   0.9259   0.01755   0.01079  -0.2067   0.7243   0.3656
   0.500   0.9530   0.01762   0.01084  -0.2063   0.7168   0.3724
   0.750   0.9822   0.01750   0.01063  -0.2065   0.7093   0.3795
   1.000   1.0095   0.01751   0.01063  -0.2062   0.7029   0.3836
   1.250   1.0380   0.01748   0.01056  -0.2063   0.6953   0.3891
   1.500   1.0680   0.01736   0.01030  -0.2066   0.6891   0.3947
   1.750   1.0935   0.01743   0.01048  -0.2060   0.6805   0.3996
   2.000   1.1231   0.01743   0.01035  -0.2062   0.6738   0.4072
   2.250   1.1494   0.01744   0.01042  -0.2059   0.6660   0.4119
   2.500   1.1769   0.01745   0.01043  -0.2056   0.6587   0.4173
   2.750   1.2057   0.01749   0.01040  -0.2058   0.6515   0.4213
   3.000   1.2345   0.01748   0.01033  -0.2060   0.6436   0.4238
   3.250   1.2621   0.01745   0.01030  -0.2059   0.6363   0.4259
   3.500   1.2887   0.01747   0.01037  -0.2056   0.6278   0.4285
   3.750   1.3164   0.01752   0.01038  -0.2054   0.6201   0.4319
   4.000   1.3429   0.01756   0.01044  -0.2051   0.6105   0.4348
   4.250   1.3708   0.01764   0.01046  -0.2050   0.6028   0.4373
   4.500   1.3973   0.01771   0.01057  -0.2048   0.5941   0.4396
   4.750   1.4244   0.01778   0.01065  -0.2046   0.5869   0.4420
   5.000   1.4496   0.01787   0.01085  -0.2040   0.5778   0.4446
   5.250   1.4764   0.01799   0.01095  -0.2037   0.5703   0.4482
   5.500   1.5012   0.01812   0.01116  -0.2031   0.5607   0.4518
   5.750   1.5271   0.01826   0.01130  -0.2027   0.5519   0.4546
   6.000   1.5516   0.01832   0.01145  -0.2020   0.5418   0.4572
   6.250   1.5755   0.01846   0.01166  -0.2012   0.5310   0.4600
   6.500   1.5993   0.01858   0.01182  -0.2003   0.5193   0.4632
   6.750   1.6217   0.01873   0.01196  -0.1992   0.5051   0.4667
   7.000   1.6428   0.01894   0.01218  -0.1979   0.4887   0.4703
   7.250   1.6623   0.01918   0.01246  -0.1963   0.4702   0.4737
   7.500   1.6799   0.01954   0.01282  -0.1944   0.4490   0.4773
   7.750   1.6961   0.02003   0.01325  -0.1923   0.4271   0.4806
   8.000   1.7113   0.02061   0.01379  -0.1901   0.4051   0.4839
   8.250   1.7244   0.02126   0.01440  -0.1877   0.3814   0.4868
   8.500   1.7346   0.02202   0.01512  -0.1847   0.3571   0.4900
   8.750   1.7416   0.02287   0.01592  -0.1813   0.3324   0.4936
   9.000   1.7432   0.02389   0.01685  -0.1771   0.3114   0.4972
   9.250   1.7477   0.02504   0.01793  -0.1737   0.2920   0.5009
   9.500   1.7519   0.02628   0.01914  -0.1704   0.2757   0.5043
   9.750   1.7558   0.02765   0.02049  -0.1673   0.2616   0.5079
  10.000   1.7589   0.02914   0.02196  -0.1643   0.2485   0.5117
  10.250   1.7620   0.03073   0.02353  -0.1614   0.2351   0.5156
  10.500   1.7649   0.03238   0.02522  -0.1587   0.2204   0.5193
  10.750   1.7651   0.03433   0.02718  -0.1560   0.2034   0.5234
  11.000   1.7642   0.03652   0.02937  -0.1534   0.1752   0.5282
  11.250   1.7499   0.04004   0.03260  -0.1502   0.1253   0.5315
  11.500   1.7310   0.04424   0.03652  -0.1470   0.0955   0.5341
  11.750   1.7174   0.04810   0.04032  -0.1444   0.0827   0.5376
  12.000   1.7090   0.05160   0.04388  -0.1423   0.0752   0.5425
  12.250   1.6984   0.05546   0.04777  -0.1404   0.0703   0.5473
  12.500   1.6933   0.05887   0.05131  -0.1390   0.0662   0.5533
  12.750   1.6883   0.06237   0.05491  -0.1377   0.0627   0.5607
  13.000   1.6789   0.06646   0.05906  -0.1365   0.0600   0.5681
  13.250   1.6735   0.07014   0.06287  -0.1355   0.0575   0.5802
  13.500   1.6722   0.07341   0.06633  -0.1347   0.0550   0.6091
  13.750   1.6664   0.07649   0.06974  -0.1335   0.0530   1.0000
  14.000   1.6612   0.08021   0.07347  -0.1326   0.0511   1.0000
  14.250   1.6570   0.08365   0.07691  -0.1315   0.0492   1.0000
  14.500   1.6582   0.08670   0.08008  -0.1309   0.0474   1.0000
  14.750   1.6585   0.08981   0.08327  -0.1303   0.0455   1.0000
  15.000   1.6590   0.09283   0.08631  -0.1297   0.0439   1.0000
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