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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.41 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe147-il-1000000-n5.txt
Download as CSV file: xf-goe147-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 147 (MVA H.6) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5186   0.10631   0.10478   0.0173   1.0000   0.0039
  -9.250  -0.5181   0.10150   0.09998   0.0151   1.0000   0.0039
  -9.000  -0.6422   0.05206   0.05027  -0.0303   1.0000   0.0039
  -8.750  -0.6321   0.02955   0.02690  -0.0522   1.0000   0.0039
  -8.500  -0.6095   0.02249   0.01939  -0.0559   1.0000   0.0039
  -8.250  -0.5849   0.01906   0.01558  -0.0573   1.0000   0.0040
  -8.000  -0.5590   0.01714   0.01342  -0.0579   1.0000   0.0042
  -7.750  -0.5323   0.01598   0.01210  -0.0582   1.0000   0.0043
  -7.500  -0.5052   0.01506   0.01106  -0.0583   1.0000   0.0045
  -7.250  -0.4779   0.01426   0.01013  -0.0584   1.0000   0.0046
  -7.000  -0.4504   0.01352   0.00929  -0.0584   1.0000   0.0048
  -6.750  -0.4229   0.01284   0.00849  -0.0584   1.0000   0.0050
  -6.500  -0.3918   0.01217   0.00772  -0.0592   0.9878   0.0052
  -6.250  -0.3579   0.01157   0.00699  -0.0605   0.9567   0.0055
  -6.000  -0.3309   0.01126   0.00652  -0.0600   0.9119   0.0058
  -5.750  -0.3059   0.01100   0.00604  -0.0591   0.8702   0.0060
  -5.500  -0.2797   0.01050   0.00527  -0.0586   0.8274   0.0066
  -5.250  -0.2528   0.01027   0.00483  -0.0582   0.7841   0.0070
  -5.000  -0.2252   0.01007   0.00442  -0.0580   0.7422   0.0075
  -4.750  -0.1974   0.00989   0.00403  -0.0578   0.7009   0.0080
  -4.500  -0.1694   0.00975   0.00368  -0.0577   0.6578   0.0085
  -4.250  -0.1412   0.00957   0.00330  -0.0576   0.6211   0.0092
  -4.000  -0.1129   0.00936   0.00297  -0.0575   0.5937   0.0106
  -3.750  -0.0845   0.00922   0.00272  -0.0575   0.5735   0.0119
  -3.500  -0.0560   0.00908   0.00250  -0.0574   0.5601   0.0129
  -3.250  -0.0274   0.00887   0.00222  -0.0574   0.5473   0.0163
  -3.000   0.0012   0.00874   0.00203  -0.0574   0.5350   0.0201
  -2.750   0.0297   0.00857   0.00183  -0.0573   0.5228   0.0287
  -2.500   0.0582   0.00838   0.00161  -0.0574   0.5087   0.0438
  -2.250   0.0866   0.00830   0.00164  -0.0574   0.4939   0.0844
  -2.000   0.1152   0.00831   0.00160  -0.0573   0.4823   0.0879
  -1.750   0.1438   0.00834   0.00160  -0.0573   0.4693   0.0916
  -1.500   0.1723   0.00842   0.00162  -0.0572   0.4535   0.0951
  -1.250   0.2008   0.00849   0.00159  -0.0571   0.4336   0.0965
  -1.000   0.2292   0.00854   0.00153  -0.0571   0.4080   0.0969
  -0.750   0.2574   0.00868   0.00152  -0.0571   0.3723   0.0975
  -0.500   0.2856   0.00879   0.00149  -0.0571   0.3407   0.0988
  -0.250   0.3139   0.00884   0.00144  -0.0571   0.3192   0.0994
   0.000   0.3422   0.00890   0.00141  -0.0571   0.3018   0.1002
   0.500   0.3991   0.00897   0.00138  -0.0571   0.2766   0.1019
   0.750   0.4275   0.00901   0.00139  -0.0571   0.2670   0.1028
   1.250   0.4842   0.00910   0.00142  -0.0571   0.2505   0.1050
   1.500   0.5125   0.00918   0.00146  -0.0570   0.2411   0.1063
   1.750   0.5408   0.00923   0.00150  -0.0570   0.2331   0.1074
   2.000   0.5691   0.00931   0.00154  -0.0570   0.2262   0.1083
   2.250   0.5974   0.00937   0.00160  -0.0570   0.2201   0.1093
   2.750   0.6537   0.00952   0.00173  -0.0570   0.2079   0.1109
   3.000   0.6818   0.00962   0.00181  -0.0569   0.2010   0.1121
   3.250   0.7099   0.00970   0.00191  -0.0569   0.1950   0.1151
   3.500   0.7379   0.00980   0.00201  -0.0569   0.1871   0.1189
   3.750   0.7659   0.00991   0.00212  -0.0569   0.1791   0.1236
   4.000   0.7938   0.01001   0.00228  -0.0569   0.1687   0.1591
   4.250   0.8214   0.01017   0.00245  -0.0569   0.1558   0.1942
   4.500   0.8489   0.01036   0.00263  -0.0569   0.1433   0.2097
   4.750   0.8766   0.01051   0.00282  -0.0569   0.1356   0.2312
   5.000   0.9043   0.01061   0.00303  -0.0569   0.1294   0.2881
   5.500   0.9542   0.00956   0.00348  -0.0560   0.1243   1.0000
   5.750   0.9814   0.00983   0.00372  -0.0559   0.1168   1.0000
   6.000   1.0088   0.01002   0.00392  -0.0558   0.1137   1.0000
   6.250   1.0360   0.01025   0.00414  -0.0557   0.1093   1.0000
   6.500   1.0629   0.01054   0.00441  -0.0556   0.1029   1.0000
   6.750   1.0901   0.01075   0.00463  -0.0556   0.0989   1.0000
   7.000   1.1165   0.01110   0.00492  -0.0554   0.0866   1.0000
   7.250   1.1380   0.01247   0.00594  -0.0549   0.0242   1.0000
   7.500   1.1633   0.01302   0.00646  -0.0546   0.0138   1.0000
   7.750   1.1890   0.01344   0.00690  -0.0544   0.0104   1.0000
   8.000   1.2145   0.01388   0.00736  -0.0541   0.0086   1.0000
   8.250   1.2398   0.01435   0.00786  -0.0538   0.0073   1.0000
   8.500   1.2652   0.01477   0.00832  -0.0535   0.0066   1.0000
   8.750   1.2901   0.01524   0.00883  -0.0532   0.0059   1.0000
   9.000   1.3142   0.01585   0.00948  -0.0528   0.0051   1.0000
   9.250   1.3388   0.01632   0.01000  -0.0525   0.0048   1.0000
   9.500   1.3629   0.01685   0.01060  -0.0521   0.0044   1.0000
   9.750   1.3865   0.01741   0.01122  -0.0517   0.0041   1.0000
  10.000   1.4096   0.01803   0.01189  -0.0512   0.0038   1.0000
  10.250   1.4314   0.01882   0.01275  -0.0506   0.0035   1.0000
  10.500   1.4528   0.01960   0.01361  -0.0499   0.0033   1.0000
  10.750   1.4743   0.02032   0.01442  -0.0493   0.0032   1.0000
  11.000   1.4949   0.02111   0.01529  -0.0486   0.0030   1.0000
  11.250   1.5147   0.02195   0.01621  -0.0478   0.0029   1.0000
  11.500   1.5337   0.02280   0.01715  -0.0470   0.0027   1.0000
  11.750   1.5521   0.02367   0.01811  -0.0461   0.0026   1.0000
  12.000   1.5694   0.02459   0.01910  -0.0451   0.0025   1.0000
  12.250   1.5847   0.02563   0.02023  -0.0440   0.0023   1.0000
  12.500   1.5963   0.02695   0.02165  -0.0425   0.0022   1.0000
  12.750   1.6010   0.02870   0.02353  -0.0404   0.0021   1.0000
  13.000   1.6035   0.03016   0.02510  -0.0379   0.0021   1.0000
  13.250   1.6043   0.03191   0.02696  -0.0360   0.0021   1.0000
  13.500   1.6020   0.03435   0.02954  -0.0351   0.0020   1.0000
  13.750   1.5991   0.03744   0.03277  -0.0353   0.0020   1.0000
  14.000   1.5939   0.04142   0.03689  -0.0368   0.0020   1.0000
  14.250   1.5854   0.04640   0.04203  -0.0392   0.0020   1.0000
  14.500   1.5727   0.05232   0.04811  -0.0423   0.0019   1.0000
  14.750   1.5550   0.05906   0.05501  -0.0455   0.0019   1.0000
  15.000   1.5327   0.06651   0.06261  -0.0488   0.0019   1.0000
  15.250   1.5070   0.07464   0.07089  -0.0524   0.0020   1.0000
  15.500   1.4798   0.08310   0.07950  -0.0559   0.0020   1.0000
  15.750   1.4522   0.09164   0.08817  -0.0594   0.0020   1.0000
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