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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 50,000
Max Cl/Cd: 35.17 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe137-il-50000.txt
Download as CSV file: xf-goe137-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 137 (MVA H.15) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3697   0.11829   0.11149  -0.0138   1.0000   0.1437
  -9.000  -0.3702   0.11640   0.10967  -0.0157   1.0000   0.1489
  -8.750  -0.3832   0.11674   0.11015  -0.0194   1.0000   0.1508
  -8.500  -0.3561   0.10915   0.10251  -0.0166   1.0000   0.1585
  -8.250  -0.3614   0.10793   0.10140  -0.0188   1.0000   0.1643
  -8.000  -0.3519   0.10356   0.09709  -0.0186   1.0000   0.1695
  -7.750  -0.3499   0.10115   0.09473  -0.0192   1.0000   0.1775
  -7.500  -0.3669   0.10150   0.09529  -0.0241   1.0000   0.1803
  -7.250  -0.3436   0.09512   0.08887  -0.0194   1.0000   0.1901
  -7.000  -0.3592   0.09539   0.08931  -0.0258   1.0000   0.1952
  -6.750  -0.3391   0.08946   0.08339  -0.0203   1.0000   0.2038
  -6.500  -0.3497   0.08859   0.08268  -0.0250   1.0000   0.2106
  -6.250  -0.3373   0.08422   0.07836  -0.0207   1.0000   0.2200
  -6.000  -0.3398   0.08182   0.07607  -0.0216   1.0000   0.2279
  -5.750  -0.3449   0.08091   0.07521  -0.0250   1.0000   0.2399
  -5.500  -0.3382   0.07695   0.07136  -0.0196   1.0000   0.2516
  -5.250  -0.3381   0.07441   0.06891  -0.0177   1.0000   0.2642
  -5.000  -0.3395   0.07216   0.06675  -0.0162   1.0000   0.2789
  -4.750  -0.3428   0.07082   0.06544  -0.0181   1.0000   0.2990
  -4.500  -0.3430   0.06805   0.06274  -0.0146   1.0000   0.3149
  -4.250  -0.3430   0.06560   0.06037  -0.0112   1.0000   0.3324
  -4.000  -0.3434   0.06359   0.05842  -0.0094   1.0000   0.3599
  -3.750  -0.3440   0.06146   0.05637  -0.0058   1.0000   0.3903
  -3.500  -0.3456   0.05971   0.05469  -0.0016   1.0000   0.4317
  -3.250  -0.3510   0.05769   0.05280   0.0051   1.0000   0.4785
  -3.000  -0.3578   0.05559   0.05083   0.0138   1.0000   0.5260
  -2.750  -0.3636   0.05362   0.04897   0.0221   1.0000   0.5768
  -2.500  -0.3671   0.05156   0.04699   0.0289   1.0000   0.6234
  -2.250  -0.3651   0.04929   0.04478   0.0326   1.0000   0.6587
  -2.000  -0.0815   0.03885   0.03045  -0.0530   1.0000   0.1802
  -1.750  -0.0444   0.03649   0.02780  -0.0560   0.9969   0.1710
  -1.500   0.0167   0.03441   0.02492  -0.0624   0.9867   0.1629
  -1.250   0.0712   0.03296   0.02296  -0.0678   0.9755   0.1675
  -1.000   0.1225   0.03189   0.02159  -0.0725   0.9635   0.1749
  -0.750   0.1730   0.03096   0.02034  -0.0766   0.9516   0.1839
  -0.500   0.2253   0.03025   0.01941  -0.0809   0.9396   0.2084
  -0.250   0.2749   0.02902   0.01847  -0.0847   0.9279   0.2821
   0.000   0.3123   0.02639   0.01748  -0.0853   0.9155   1.0000
   0.250   0.3540   0.02695   0.01757  -0.0881   0.9007   1.0000
   0.500   0.3940   0.02748   0.01780  -0.0907   0.8858   1.0000
   0.750   0.4328   0.02799   0.01806  -0.0929   0.8712   1.0000
   1.000   0.4703   0.02849   0.01838  -0.0948   0.8568   1.0000
   1.250   0.5057   0.02897   0.01872  -0.0963   0.8425   1.0000
   1.500   0.5383   0.02950   0.01914  -0.0972   0.8285   1.0000
   1.750   0.5694   0.03004   0.01959  -0.0978   0.8145   1.0000
   2.000   0.5991   0.03062   0.02010  -0.0981   0.8008   1.0000
   2.250   0.6277   0.03125   0.02067  -0.0983   0.7874   1.0000
   2.500   0.6559   0.03188   0.02128  -0.0983   0.7743   1.0000
   2.750   0.6849   0.03246   0.02184  -0.0983   0.7621   1.0000
   3.000   0.7193   0.03271   0.02208  -0.0986   0.7513   1.0000
   3.250   0.7412   0.03367   0.02308  -0.0979   0.7378   1.0000
   3.500   0.7631   0.03462   0.02405  -0.0972   0.7243   1.0000
   3.750   0.7863   0.03542   0.02488  -0.0964   0.7105   1.0000
   4.000   0.8111   0.03601   0.02551  -0.0954   0.6963   1.0000
   4.250   0.8379   0.03627   0.02584  -0.0942   0.6814   1.0000
   4.500   0.8664   0.03622   0.02583  -0.0927   0.6659   1.0000
   4.750   0.8940   0.03618   0.02585  -0.0911   0.6504   1.0000
   5.000   0.9187   0.03655   0.02630  -0.0897   0.6357   1.0000
   5.250   0.9406   0.03733   0.02721  -0.0885   0.6217   1.0000
   5.500   0.9627   0.03807   0.02806  -0.0872   0.6075   1.0000
   5.750   0.9858   0.03865   0.02877  -0.0859   0.5929   1.0000
   6.000   1.0097   0.03909   0.02933  -0.0844   0.5779   1.0000
   6.250   1.0344   0.03943   0.02984  -0.0829   0.5626   1.0000
   6.500   1.0594   0.03977   0.03032  -0.0814   0.5472   1.0000
   6.750   1.0862   0.03992   0.03061  -0.0799   0.5314   1.0000
   7.000   1.1084   0.04049   0.03137  -0.0783   0.5139   1.0000
   7.250   1.1239   0.04176   0.03283  -0.0765   0.4946   1.0000
   7.500   1.1477   0.04226   0.03349  -0.0749   0.4772   1.0000
   7.750   1.1703   0.04314   0.03454  -0.0735   0.4614   1.0000
   8.000   1.1962   0.04350   0.03504  -0.0720   0.4454   1.0000
   8.250   1.2283   0.04290   0.03455  -0.0704   0.4284   1.0000
   8.500   1.2396   0.04417   0.03606  -0.0682   0.4092   1.0000
   8.750   1.2769   0.04107   0.03290  -0.0657   0.3815   1.0000
   9.000   1.3053   0.03921   0.03099  -0.0634   0.3550   1.0000
   9.250   1.3204   0.03893   0.03088  -0.0608   0.3304   1.0000
   9.500   1.3319   0.03787   0.02981  -0.0574   0.2998   1.0000
   9.750   1.3306   0.03793   0.02995  -0.0534   0.2676   1.0000
  10.000   1.3217   0.03898   0.03104  -0.0491   0.2327   1.0000
  10.250   1.3040   0.04110   0.03289  -0.0444   0.1963   1.0000
  10.500   1.2841   0.04455   0.03589  -0.0405   0.1622   1.0000
  10.750   1.2706   0.04837   0.03950  -0.0377   0.1350   1.0000
  11.000   1.2649   0.05163   0.04259  -0.0358   0.1185   1.0000
  11.250   1.2641   0.05463   0.04557  -0.0343   0.1067   1.0000
  11.500   1.2672   0.05752   0.04853  -0.0329   0.0975   1.0000
  11.750   1.2753   0.06024   0.05126  -0.0313   0.0899   1.0000
  12.000   1.2965   0.06244   0.05340  -0.0293   0.0831   1.0000
  12.250   1.3128   0.06604   0.05732  -0.0277   0.0800   1.0000
  12.500   1.3127   0.07026   0.06195  -0.0268   0.0786   1.0000
  12.750   1.3052   0.07491   0.06695  -0.0264   0.0778   1.0000
  13.000   1.2915   0.08007   0.07244  -0.0266   0.0775   1.0000
  13.250   1.2727   0.08590   0.07857  -0.0278   0.0777   1.0000
  13.500   1.2498   0.09250   0.08545  -0.0300   0.0782   1.0000
  13.750   1.2241   0.09995   0.09314  -0.0332   0.0790   1.0000
  14.000   1.1971   0.10819   0.10155  -0.0373   0.0800   1.0000
  14.250   1.1707   0.11708   0.11058  -0.0421   0.0810   1.0000
  14.500   1.1479   0.12619   0.11975  -0.0470   0.0819   1.0000
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