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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 200,000
Max Cl/Cd: 78.23 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe117-il-200000.txt
Download as CSV file: xf-goe117-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 117 (MVA MK.4) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3414   0.08855   0.08536  -0.0381   1.0000   0.0452
  -7.750  -0.3541   0.08726   0.08415  -0.0352   1.0000   0.0458
  -7.500  -0.3752   0.08669   0.08368  -0.0308   1.0000   0.0461
  -7.250  -0.3847   0.08496   0.08201  -0.0298   0.9983   0.0471
  -7.000  -0.3580   0.07901   0.07604  -0.0412   0.9906   0.0510
  -6.750  -0.3250   0.06796   0.06489  -0.0642   0.9802   0.0544
  -6.500  -0.3073   0.06634   0.06329  -0.0613   0.9758   0.0566
  -6.250  -0.2597   0.05777   0.05432  -0.0819   0.9667   0.0668
  -6.000  -0.2480   0.05575   0.05252  -0.0777   0.9623   0.0700
  -5.750  -0.2067   0.04762   0.04404  -0.0912   0.9572   0.0818
  -5.500  -0.1844   0.04641   0.04289  -0.0901   0.9498   0.0849
  -5.250  -0.1462   0.02762   0.02248  -0.1026   0.9440   0.0502
  -5.000  -0.1161   0.02423   0.01845  -0.1039   0.9365   0.0509
  -4.750  -0.0792   0.02113   0.01474  -0.1059   0.9318   0.0507
  -4.500  -0.0445   0.01922   0.01237  -0.1071   0.9256   0.0520
  -4.250  -0.0105   0.01751   0.01032  -0.1082   0.9186   0.0551
  -4.000   0.0231   0.01600   0.00870  -0.1092   0.9115   0.0575
  -3.750   0.0562   0.01505   0.00765  -0.1101   0.9030   0.0612
  -3.500   0.0861   0.01435   0.00684  -0.1101   0.8922   0.0651
  -3.250   0.1157   0.01362   0.00601  -0.1101   0.8810   0.0677
  -3.000   0.1439   0.01290   0.00527  -0.1099   0.8690   0.0726
  -2.500   0.1979   0.01187   0.00433  -0.1090   0.8417   0.1202
  -2.250   0.2238   0.01157   0.00423  -0.1084   0.8265   0.2112
  -2.000   0.2503   0.01158   0.00417  -0.1079   0.8106   0.2420
  -1.750   0.2767   0.01161   0.00411  -0.1074   0.7947   0.2657
  -1.500   0.3030   0.01163   0.00403  -0.1069   0.7793   0.2885
  -1.250   0.3290   0.01154   0.00392  -0.1065   0.7649   0.3109
  -1.000   0.3551   0.01142   0.00375  -0.1060   0.7515   0.3328
  -0.750   0.3808   0.01124   0.00361  -0.1056   0.7390   0.3601
  -0.500   0.4063   0.01105   0.00351  -0.1051   0.7278   0.3954
  -0.250   0.4314   0.01084   0.00345  -0.1046   0.7172   0.4444
   0.000   0.4512   0.01013   0.00346  -0.1030   0.7074   0.6392
   0.250   0.5108   0.00962   0.00335  -0.1092   0.6985   1.0000
   0.500   0.5367   0.00976   0.00335  -0.1088   0.6899   1.0000
   0.750   0.5625   0.00993   0.00341  -0.1084   0.6822   1.0000
   1.000   0.5887   0.01009   0.00346  -0.1080   0.6750   1.0000
   1.250   0.6144   0.01027   0.00357  -0.1076   0.6678   1.0000
   1.500   0.6407   0.01046   0.00367  -0.1073   0.6612   1.0000
   1.750   0.6665   0.01066   0.00384  -0.1069   0.6546   1.0000
   2.000   0.6926   0.01086   0.00398  -0.1066   0.6480   1.0000
   2.250   0.7187   0.01108   0.00417  -0.1063   0.6418   1.0000
   2.500   0.7445   0.01128   0.00438  -0.1059   0.6354   1.0000
   2.750   0.7715   0.01154   0.00460  -0.1057   0.6302   1.0000
   3.000   0.7966   0.01175   0.00488  -0.1053   0.6240   1.0000
   3.250   0.8231   0.01199   0.00512  -0.1050   0.6184   1.0000
   3.500   0.8477   0.01219   0.00536  -0.1044   0.6095   1.0000
   3.750   0.8720   0.01234   0.00551  -0.1035   0.5974   1.0000
   4.000   0.8962   0.01247   0.00564  -0.1026   0.5850   1.0000
   4.250   0.9189   0.01254   0.00572  -0.1014   0.5694   1.0000
   4.500   0.9404   0.01255   0.00575  -0.0999   0.5502   1.0000
   4.750   0.9613   0.01255   0.00576  -0.0982   0.5280   1.0000
   5.000   0.9787   0.01251   0.00572  -0.0958   0.4898   1.0000
   5.250   0.9766   0.01359   0.00589  -0.0901   0.3064   1.0000
   5.500   0.9634   0.01679   0.00781  -0.0840   0.0775   1.0000
   5.750   0.9772   0.01786   0.00889  -0.0816   0.0592   1.0000
   6.000   0.9858   0.01914   0.01023  -0.0784   0.0506   1.0000
   6.250   0.9985   0.02007   0.01128  -0.0759   0.0468   1.0000
   6.500   1.0079   0.02118   0.01247  -0.0729   0.0435   1.0000
   6.750   1.0123   0.02251   0.01381  -0.0693   0.0403   1.0000
   7.000   1.0173   0.02407   0.01540  -0.0657   0.0378   1.0000
   7.250   1.0310   0.02530   0.01670  -0.0634   0.0364   1.0000
   7.500   1.0495   0.02677   0.01822  -0.0619   0.0350   1.0000
   7.750   1.0776   0.02856   0.02007  -0.0618   0.0337   1.0000
   8.000   1.1038   0.03013   0.02169  -0.0618   0.0312   1.0000
   8.250   1.1409   0.03277   0.02436  -0.0635   0.0295   1.0000
   8.500   1.1789   0.03572   0.02753  -0.0644   0.0301   1.0000
   8.750   1.2560   0.04599   0.03909  -0.0645   0.0720   1.0000
   9.000   1.2711   0.04871   0.04186  -0.0633   0.0659   1.0000
   9.250   1.2693   0.05103   0.04459  -0.0597   0.0583   1.0000
   9.500   1.2785   0.05365   0.04739  -0.0576   0.0549   1.0000
   9.750   1.2939   0.05809   0.05186  -0.0572   0.0525   1.0000
  10.000   1.2908   0.06796   0.06191  -0.0562   0.0504   1.0000
  10.250   1.2742   0.06362   0.05816  -0.0489   0.0475   1.0000
  10.500   1.2670   0.06582   0.06063  -0.0452   0.0455   1.0000
  10.750   1.2579   0.06854   0.06356  -0.0419   0.0442   1.0000
  11.000   1.2451   0.07120   0.06638  -0.0382   0.0434   1.0000
  11.250   1.2308   0.07405   0.06939  -0.0352   0.0427   1.0000
  11.500   1.2163   0.07725   0.07272  -0.0329   0.0422   1.0000
  11.750   1.2007   0.08075   0.07637  -0.0312   0.0418   1.0000
  12.000   1.1844   0.08459   0.08033  -0.0303   0.0414   1.0000
  12.250   1.1669   0.08881   0.08469  -0.0300   0.0411   1.0000
  12.500   1.1456   0.09346   0.08948  -0.0305   0.0410   1.0000
  12.750   1.1195   0.09872   0.09491  -0.0321   0.0412   1.0000
  13.000   1.0867   0.10536   0.10173  -0.0355   0.0417   1.0000
  13.250   1.0523   0.11363   0.11016  -0.0407   0.0424   1.0000
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