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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 500,000
Max Cl/Cd: 94.75 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe142-il-500000-n5.txt
Download as CSV file: xf-goe142-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 142 (MVA H.19) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4029   0.09333   0.09110  -0.0097   1.0000   0.0073
  -7.750  -0.3989   0.08958   0.08738  -0.0119   1.0000   0.0074
  -7.500  -0.3947   0.08586   0.08370  -0.0145   1.0000   0.0076
  -7.250  -0.3872   0.08188   0.07974  -0.0179   1.0000   0.0076
  -7.000  -0.3781   0.07806   0.07593  -0.0214   1.0000   0.0077
  -6.750  -0.3676   0.07572   0.07362  -0.0230   1.0000   0.0080
  -6.500  -0.3578   0.07344   0.07135  -0.0244   1.0000   0.0083
  -6.250  -0.3358   0.06992   0.06782  -0.0295   0.9965   0.0091
  -6.000  -0.3051   0.06474   0.06260  -0.0377   0.9904   0.0097
  -5.750  -0.2721   0.05912   0.05691  -0.0462   0.9841   0.0093
  -5.500  -0.2387   0.05321   0.05088  -0.0542   0.9757   0.0089
  -5.250  -0.2022   0.04693   0.04446  -0.0621   0.9681   0.0088
  -5.000  -0.1669   0.04092   0.03826  -0.0682   0.9588   0.0090
  -4.750  -0.1323   0.03454   0.03160  -0.0732   0.9489   0.0096
  -4.500  -0.0947   0.01441   0.00955  -0.0795   0.9410   0.0113
  -4.250  -0.0673   0.01325   0.00815  -0.0795   0.9302   0.0119
  -4.000  -0.0402   0.01251   0.00722  -0.0792   0.9189   0.0125
  -3.750  -0.0132   0.01178   0.00630  -0.0789   0.9067   0.0133
  -3.500   0.0136   0.01110   0.00543  -0.0785   0.8936   0.0142
  -3.250   0.0403   0.01053   0.00468  -0.0780   0.8791   0.0150
  -3.000   0.0670   0.01004   0.00403  -0.0775   0.8636   0.0160
  -2.750   0.0938   0.00972   0.00363  -0.0772   0.8471   0.0178
  -2.500   0.1207   0.00946   0.00326  -0.0767   0.8299   0.0193
  -2.250   0.1478   0.00921   0.00288  -0.0764   0.8119   0.0210
  -2.000   0.1749   0.00893   0.00247  -0.0760   0.7928   0.0230
  -1.750   0.2020   0.00881   0.00227  -0.0757   0.7726   0.0265
  -1.500   0.2292   0.00874   0.00210  -0.0754   0.7507   0.0297
  -1.250   0.2564   0.00860   0.00185  -0.0751   0.7282   0.0335
  -1.000   0.2836   0.00857   0.00172  -0.0749   0.7041   0.0388
  -0.750   0.3109   0.00856   0.00159  -0.0746   0.6796   0.0427
  -0.500   0.3382   0.00853   0.00148  -0.0744   0.6554   0.0498
  -0.250   0.3654   0.00856   0.00140  -0.0742   0.6308   0.0574
   0.000   0.3928   0.00859   0.00135  -0.0741   0.6063   0.0665
   0.250   0.4201   0.00862   0.00132  -0.0739   0.5827   0.0784
   0.750   0.4748   0.00872   0.00130  -0.0737   0.5364   0.1115
   1.000   0.5021   0.00874   0.00133  -0.0736   0.5141   0.1487
   1.250   0.5293   0.00844   0.00141  -0.0738   0.4926   0.3358
   1.750   0.5791   0.00722   0.00153  -0.0726   0.4519   1.0000
   2.250   0.6335   0.00759   0.00166  -0.0723   0.4126   1.0000
   2.500   0.6607   0.00778   0.00174  -0.0722   0.3939   1.0000
   2.750   0.6878   0.00797   0.00185  -0.0720   0.3771   1.0000
   3.250   0.7419   0.00836   0.00208  -0.0718   0.3444   1.0000
   3.500   0.7690   0.00856   0.00221  -0.0716   0.3302   1.0000
   3.750   0.7960   0.00876   0.00236  -0.0715   0.3159   1.0000
   4.000   0.8228   0.00898   0.00252  -0.0714   0.3014   1.0000
   4.250   0.8497   0.00919   0.00269  -0.0712   0.2888   1.0000
   4.500   0.8764   0.00942   0.00287  -0.0711   0.2760   1.0000
   5.000   0.9297   0.00987   0.00328  -0.0707   0.2513   1.0000
   5.250   0.9562   0.01012   0.00350  -0.0705   0.2394   1.0000
   5.500   0.9826   0.01037   0.00374  -0.0704   0.2283   1.0000
   5.750   1.0086   0.01066   0.00401  -0.0701   0.2136   1.0000
   6.000   1.0340   0.01105   0.00430  -0.0699   0.1919   1.0000
   6.250   1.0596   0.01141   0.00459  -0.0696   0.1734   1.0000
   6.500   1.0848   0.01179   0.00492  -0.0693   0.1556   1.0000
   6.750   1.1097   0.01222   0.00529  -0.0690   0.1366   1.0000
   7.000   1.1343   0.01270   0.00569  -0.0686   0.1158   1.0000
   7.250   1.1581   0.01327   0.00616  -0.0682   0.0921   1.0000
   7.500   1.1802   0.01409   0.00680  -0.0676   0.0601   1.0000
   7.750   1.2022   0.01491   0.00749  -0.0669   0.0375   1.0000
   8.000   1.2250   0.01558   0.00815  -0.0663   0.0264   1.0000
   8.250   1.2479   0.01621   0.00878  -0.0657   0.0202   1.0000
   8.500   1.2705   0.01686   0.00946  -0.0650   0.0163   1.0000
   8.750   1.2932   0.01746   0.01014  -0.0644   0.0143   1.0000
   9.000   1.3157   0.01807   0.01083  -0.0637   0.0127   1.0000
   9.250   1.3371   0.01879   0.01161  -0.0629   0.0113   1.0000
   9.500   1.3565   0.01976   0.01269  -0.0619   0.0100   1.0000
   9.750   1.3775   0.02044   0.01348  -0.0610   0.0094   1.0000
  10.000   1.3976   0.02118   0.01431  -0.0601   0.0086   1.0000
  10.250   1.4168   0.02197   0.01519  -0.0591   0.0079   1.0000
  10.500   1.4344   0.02291   0.01622  -0.0579   0.0073   1.0000
  10.750   1.4487   0.02413   0.01755  -0.0563   0.0068   1.0000
  11.000   1.4601   0.02554   0.01910  -0.0544   0.0065   1.0000
  11.250   1.4739   0.02659   0.02031  -0.0528   0.0063   1.0000
  11.500   1.4857   0.02773   0.02157  -0.0510   0.0060   1.0000
  11.750   1.4940   0.02888   0.02285  -0.0486   0.0057   1.0000
  12.000   1.5006   0.03012   0.02420  -0.0462   0.0054   1.0000
  12.250   1.5058   0.03151   0.02572  -0.0441   0.0052   1.0000
  12.500   1.5104   0.03305   0.02738  -0.0421   0.0049   1.0000
  12.750   1.5134   0.03485   0.02930  -0.0405   0.0048   1.0000
  13.000   1.5139   0.03704   0.03162  -0.0391   0.0046   1.0000
  13.250   1.5124   0.03963   0.03434  -0.0382   0.0045   1.0000
  13.500   1.5081   0.04279   0.03765  -0.0378   0.0044   1.0000
  13.750   1.5007   0.04664   0.04165  -0.0380   0.0043   1.0000
  14.000   1.4907   0.05119   0.04636  -0.0390   0.0042   1.0000
  14.250   1.4775   0.05650   0.05185  -0.0406   0.0041   1.0000
  14.500   1.4642   0.06215   0.05766  -0.0426   0.0041   1.0000
  14.750   1.4539   0.06753   0.06320  -0.0448   0.0040   1.0000
  15.000   1.4413   0.07342   0.06927  -0.0472   0.0040   1.0000
  15.250   1.4269   0.07970   0.07571  -0.0498   0.0040   1.0000
  15.500   1.4122   0.08615   0.08230  -0.0525   0.0040   1.0000
  15.750   1.3964   0.09296   0.08925  -0.0555   0.0040   1.0000
  16.000   1.3804   0.09990   0.09632  -0.0586   0.0040   1.0000
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