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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 200,000
Max Cl/Cd: 64.3 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe147-il-200000.txt
Download as CSV file: xf-goe147-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3724   0.09388   0.09076   0.0036   1.0000   0.0505
  -8.250  -0.3690   0.09039   0.08729   0.0027   1.0000   0.0524
  -8.000  -0.4785   0.09791   0.09467   0.0099   1.0000   0.0482
  -7.750  -0.4694   0.09492   0.09170   0.0097   1.0000   0.0497
  -7.500  -0.4628   0.09181   0.08862   0.0082   1.0000   0.0516
  -7.250  -0.4568   0.08837   0.08521   0.0051   1.0000   0.0541
  -7.000  -0.4376   0.08240   0.07920  -0.0162   1.0000   0.0571
  -6.750  -0.4338   0.07799   0.07485  -0.0115   1.0000   0.0582
  -6.500  -0.4215   0.07535   0.07223  -0.0095   1.0000   0.0596
  -6.250  -0.4059   0.07219   0.06908  -0.0113   1.0000   0.0622
  -6.000  -0.3737   0.06464   0.06135  -0.0279   1.0000   0.0686
  -5.750  -0.3615   0.06166   0.05842  -0.0259   1.0000   0.0696
  -5.500  -0.3258   0.03302   0.02872  -0.0462   1.0000   0.0358
  -5.250  -0.2991   0.02542   0.02018  -0.0496   1.0000   0.0358
  -5.000  -0.2720   0.02129   0.01532  -0.0506   1.0000   0.0364
  -4.750  -0.2446   0.01833   0.01186  -0.0508   1.0000   0.0369
  -4.500  -0.2175   0.01634   0.00963  -0.0507   1.0000   0.0385
  -4.250  -0.1903   0.01511   0.00826  -0.0504   1.0000   0.0408
  -4.000  -0.1631   0.01422   0.00723  -0.0501   1.0000   0.0452
  -3.750  -0.1362   0.01315   0.00612  -0.0497   1.0000   0.0502
  -3.500  -0.1093   0.01245   0.00542  -0.0493   1.0000   0.0595
  -3.250  -0.0826   0.01288   0.00593  -0.0485   1.0000   0.0917
  -3.000  -0.0581   0.01366   0.00669  -0.0478   1.0000   0.1173
  -2.750  -0.0302   0.01398   0.00702  -0.0481   0.9968   0.1321
  -2.500   0.0170   0.01405   0.00709  -0.0522   0.9759   0.1457
  -2.250   0.0602   0.01404   0.00712  -0.0552   0.9462   0.1571
  -2.000   0.0976   0.01385   0.00683  -0.0568   0.9080   0.1654
  -1.750   0.1257   0.01362   0.00643  -0.0560   0.8662   0.1685
  -1.500   0.1507   0.01335   0.00594  -0.0547   0.8272   0.1695
  -1.250   0.1759   0.01314   0.00551  -0.0535   0.7934   0.1707
  -1.000   0.2019   0.01296   0.00512  -0.0527   0.7634   0.1722
  -0.750   0.2285   0.01281   0.00479  -0.0520   0.7361   0.1739
  -0.500   0.2554   0.01265   0.00449  -0.0514   0.7110   0.1763
  -0.250   0.2822   0.01249   0.00425  -0.0509   0.6884   0.1791
   0.000   0.3094   0.01237   0.00406  -0.0504   0.6665   0.1817
   0.250   0.3366   0.01230   0.00389  -0.0500   0.6465   0.1851
   0.500   0.3640   0.01225   0.00375  -0.0496   0.6256   0.1891
   0.750   0.3912   0.01216   0.00362  -0.0493   0.6041   0.1939
   1.000   0.4185   0.01213   0.00354  -0.0489   0.5813   0.2012
   1.250   0.4457   0.01208   0.00345  -0.0486   0.5579   0.2114
   1.500   0.4732   0.01200   0.00338  -0.0483   0.5336   0.2321
   1.750   0.5004   0.01169   0.00334  -0.0483   0.5090   0.3090
   2.000   0.5215   0.01019   0.00324  -0.0463   0.4836   1.0000
   2.250   0.5488   0.01040   0.00324  -0.0460   0.4536   1.0000
   2.500   0.5762   0.01064   0.00329  -0.0458   0.4246   1.0000
   2.750   0.6035   0.01090   0.00340  -0.0456   0.3990   1.0000
   3.000   0.6307   0.01121   0.00354  -0.0454   0.3782   1.0000
   3.250   0.6578   0.01153   0.00372  -0.0452   0.3604   1.0000
   3.500   0.6849   0.01187   0.00395  -0.0450   0.3452   1.0000
   3.750   0.7120   0.01221   0.00421  -0.0448   0.3317   1.0000
   4.000   0.7390   0.01258   0.00449  -0.0446   0.3197   1.0000
   4.250   0.7658   0.01297   0.00478  -0.0444   0.3086   1.0000
   4.500   0.7930   0.01328   0.00511  -0.0443   0.2973   1.0000
   4.750   0.8199   0.01364   0.00546  -0.0441   0.2866   1.0000
   5.000   0.8466   0.01403   0.00581  -0.0439   0.2761   1.0000
   5.250   0.8732   0.01445   0.00617  -0.0437   0.2655   1.0000
   5.500   0.9000   0.01478   0.00658  -0.0435   0.2542   1.0000
   5.750   0.9264   0.01522   0.00703  -0.0432   0.2433   1.0000
   6.000   0.9525   0.01573   0.00751  -0.0430   0.2337   1.0000
   6.250   0.9788   0.01618   0.00799  -0.0427   0.2248   1.0000
   6.500   1.0050   0.01676   0.00863  -0.0424   0.2176   1.0000
   6.750   1.0311   0.01722   0.00911  -0.0422   0.2108   1.0000
   7.000   1.0569   0.01748   0.00946  -0.0419   0.2011   1.0000
   7.250   1.0825   0.01769   0.00969  -0.0417   0.1912   1.0000
   7.500   1.1084   0.01788   0.01000  -0.0415   0.1823   1.0000
   7.750   1.1343   0.01812   0.01037  -0.0413   0.1732   1.0000
   8.000   1.1599   0.01833   0.01067  -0.0410   0.1628   1.0000
   8.250   1.1857   0.01844   0.01083  -0.0409   0.1410   1.0000
   8.500   1.2041   0.02015   0.01194  -0.0403   0.0520   1.0000
   8.750   1.2219   0.02205   0.01395  -0.0392   0.0393   1.0000
   9.000   1.2394   0.02378   0.01588  -0.0382   0.0344   1.0000
   9.250   1.2575   0.02520   0.01751  -0.0372   0.0319   1.0000
   9.500   1.2728   0.02686   0.01931  -0.0360   0.0300   1.0000
   9.750   1.2844   0.02882   0.02137  -0.0346   0.0285   1.0000
  10.000   1.2897   0.03145   0.02405  -0.0326   0.0270   1.0000
  10.250   1.3007   0.03336   0.02607  -0.0310   0.0259   1.0000
  10.500   1.3127   0.03504   0.02792  -0.0296   0.0249   1.0000
  10.750   1.3226   0.03703   0.03003  -0.0279   0.0243   1.0000
  11.000   1.3315   0.03913   0.03225  -0.0262   0.0237   1.0000
  11.250   1.3377   0.04133   0.03458  -0.0243   0.0233   1.0000
  11.500   1.3424   0.04374   0.03716  -0.0225   0.0230   1.0000
  11.750   1.3456   0.04640   0.03999  -0.0211   0.0228   1.0000
  12.000   1.3469   0.04933   0.04312  -0.0199   0.0226   1.0000
  12.250   1.3458   0.05250   0.04649  -0.0193   0.0225   1.0000
  12.500   1.3425   0.05593   0.05013  -0.0192   0.0222   1.0000
  12.750   1.3380   0.05960   0.05397  -0.0196   0.0219   1.0000
  13.000   1.3323   0.06358   0.05812  -0.0205   0.0216   1.0000
  13.250   1.3245   0.06796   0.06268  -0.0219   0.0213   1.0000
  13.500   1.3145   0.07281   0.06770  -0.0239   0.0211   1.0000
  13.750   1.3025   0.07816   0.07324  -0.0264   0.0211   1.0000
  14.000   1.2884   0.08404   0.07932  -0.0295   0.0211   1.0000
  14.250   1.2715   0.09066   0.08617  -0.0332   0.0213   1.0000
  14.500   1.2476   0.09887   0.09462  -0.0386   0.0216   1.0000
  14.750   1.2214   0.10808   0.10409  -0.0448   0.0221   1.0000
  15.000   1.1925   0.11882   0.11507  -0.0521   0.0229   1.0000
  15.250   1.1649   0.13002   0.12645  -0.0595   0.0237   1.0000
  15.500   1.1386   0.14160   0.13818  -0.0670   0.0246   1.0000
  15.750   1.1127   0.15362   0.15030  -0.0745   0.0255   1.0000
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