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GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.33 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe308-il-1000000.txt
Download as CSV file: xf-goe308-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 308 (MVA H.40) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2530   0.09504   0.09359  -0.0273   1.0000   0.0128
  -9.250  -0.3365   0.10014   0.09858  -0.0261   1.0000   0.0124
  -9.000  -0.3362   0.09748   0.09594  -0.0259   1.0000   0.0125
  -8.750  -0.3338   0.09555   0.09403  -0.0251   1.0000   0.0126
  -8.500  -0.3314   0.09401   0.09251  -0.0241   1.0000   0.0130
  -8.250  -0.3187   0.09054   0.08904  -0.0276   0.9989   0.0132
  -8.000  -0.3003   0.08693   0.08543  -0.0324   0.9969   0.0140
  -7.500  -0.2650   0.07601   0.07449  -0.0499   0.9865   0.0158
  -7.250  -0.2417   0.07074   0.06920  -0.0573   0.9837   0.0158
  -7.000  -0.2250   0.06539   0.06381  -0.0630   0.9761   0.0159
  -6.250  -0.1580   0.05435   0.05267  -0.0756   0.9586   0.0175
  -6.000  -0.1183   0.04920   0.04739  -0.0835   0.9497   0.0204
  -5.500  -0.0928   0.02076   0.01770  -0.0929   0.9106   0.0200
  -5.250  -0.0787   0.01661   0.01288  -0.0914   0.8904   0.0214
  -5.000  -0.0532   0.01626   0.01245  -0.0911   0.8735   0.0221
  -4.750  -0.0290   0.01582   0.01190  -0.0905   0.8577   0.0228
  -4.500  -0.0061   0.01505   0.01093  -0.0895   0.8437   0.0236
  -4.250   0.0168   0.01425   0.00992  -0.0885   0.8306   0.0245
  -4.000   0.0409   0.01373   0.00922  -0.0876   0.8179   0.0255
  -3.750   0.0710   0.01528   0.01080  -0.0876   0.8047   0.0267
  -3.500   0.0901   0.01315   0.00827  -0.0859   0.7930   0.0269
  -3.250   0.1107   0.01110   0.00588  -0.0844   0.7810   0.0278
  -3.000   0.1349   0.01045   0.00514  -0.0836   0.7674   0.0288
  -2.750   0.1595   0.01002   0.00459  -0.0828   0.7522   0.0294
  -2.500   0.1841   0.00965   0.00409  -0.0820   0.7353   0.0298
  -2.250   0.2087   0.00930   0.00363  -0.0812   0.7164   0.0301
  -2.000   0.2328   0.00901   0.00321  -0.0802   0.6944   0.0304
  -1.750   0.2566   0.00879   0.00286  -0.0792   0.6709   0.0310
  -1.250   0.3044   0.00851   0.00236  -0.0773   0.6265   0.0327
  -1.000   0.3285   0.00841   0.00214  -0.0763   0.6061   0.0333
  -0.750   0.3526   0.00835   0.00197  -0.0755   0.5852   0.0338
  -0.500   0.3769   0.00830   0.00183  -0.0746   0.5632   0.0343
  -0.250   0.4011   0.00830   0.00172  -0.0737   0.5412   0.0347
   0.000   0.4255   0.00830   0.00163  -0.0729   0.5193   0.0349
   0.500   0.4739   0.00831   0.00143  -0.0713   0.4806   0.0375
   0.750   0.4985   0.00835   0.00139  -0.0705   0.4645   0.0406
   1.000   0.5232   0.00838   0.00137  -0.0698   0.4514   0.0457
   1.250   0.5478   0.00838   0.00146  -0.0691   0.4413   0.0936
   1.500   0.5735   0.00842   0.00152  -0.0686   0.4329   0.1026
   2.000   0.6246   0.00855   0.00160  -0.0676   0.4179   0.1128
   2.250   0.6496   0.00862   0.00165  -0.0671   0.4103   0.1178
   2.500   0.6755   0.00866   0.00169  -0.0667   0.4039   0.1217
   2.750   0.7008   0.00870   0.00174  -0.0661   0.3978   0.1291
   3.000   0.7261   0.00875   0.00181  -0.0656   0.3926   0.1357
   3.250   0.7513   0.00873   0.00190  -0.0651   0.3878   0.1789
   3.500   0.7673   0.00811   0.00207  -0.0629   0.3832   0.5664
   3.750   0.8215   0.00743   0.00240  -0.0689   0.3770   0.9741
   4.000   0.8631   0.00762   0.00258  -0.0719   0.3706   0.9848
   4.250   0.9045   0.00781   0.00272  -0.0751   0.3639   0.9887
   4.500   0.9421   0.00794   0.00286  -0.0773   0.3569   0.9922
   4.750   0.9780   0.00811   0.00298  -0.0793   0.3442   0.9947
   5.000   1.0217   0.00827   0.00309  -0.0830   0.3329   0.9973
   5.250   1.0611   0.00845   0.00322  -0.0858   0.3204   0.9994
   5.500   1.0890   0.00862   0.00335  -0.0861   0.3042   1.0000
   5.750   1.1087   0.00885   0.00349  -0.0845   0.2837   1.0000
   6.000   1.1266   0.00917   0.00370  -0.0827   0.2584   1.0000
   6.250   1.1413   0.00969   0.00401  -0.0802   0.2206   1.0000
   6.500   1.1534   0.01035   0.00443  -0.0773   0.1782   1.0000
   6.750   1.1640   0.01110   0.00492  -0.0742   0.1350   1.0000
   7.000   1.1559   0.01298   0.00616  -0.0677   0.0243   1.0000
   7.250   1.1717   0.01340   0.00658  -0.0654   0.0186   1.0000
   7.500   1.1887   0.01375   0.00698  -0.0633   0.0169   1.0000
   7.750   1.2042   0.01420   0.00745  -0.0610   0.0152   1.0000
   8.000   1.2181   0.01474   0.00808  -0.0584   0.0139   1.0000
   8.250   1.2349   0.01510   0.00847  -0.0564   0.0134   1.0000
   8.500   1.2509   0.01551   0.00891  -0.0543   0.0127   1.0000
   8.750   1.2660   0.01596   0.00941  -0.0521   0.0120   1.0000
   9.000   1.2800   0.01648   0.00997  -0.0497   0.0113   1.0000
   9.250   1.2901   0.01705   0.01060  -0.0465   0.0109   1.0000
   9.500   1.2924   0.01792   0.01157  -0.0420   0.0103   1.0000
   9.750   1.2958   0.01883   0.01257  -0.0379   0.0099   1.0000
  10.000   1.3059   0.01947   0.01327  -0.0352   0.0097   1.0000
  10.250   1.3171   0.02009   0.01395  -0.0327   0.0094   1.0000
  10.500   1.3242   0.02097   0.01491  -0.0298   0.0092   1.0000
  10.750   1.3389   0.02148   0.01544  -0.0282   0.0085   1.0000
  11.000   1.3438   0.02257   0.01662  -0.0253   0.0085   1.0000
  11.250   1.3508   0.02360   0.01770  -0.0230   0.0081   1.0000
  11.500   1.3572   0.02474   0.01891  -0.0208   0.0079   1.0000
  11.750   1.3596   0.02624   0.02048  -0.0185   0.0077   1.0000
  12.000   1.3529   0.02857   0.02290  -0.0159   0.0073   1.0000
  12.250   1.3454   0.03121   0.02565  -0.0137   0.0072   1.0000
  12.500   1.3311   0.03470   0.02927  -0.0116   0.0071   1.0000
  12.750   1.3349   0.03671   0.03136  -0.0108   0.0071   1.0000
  13.000   1.3353   0.03913   0.03387  -0.0100   0.0070   1.0000
  13.250   1.3415   0.04111   0.03594  -0.0097   0.0068   1.0000
  13.500   1.3423   0.04368   0.03860  -0.0094   0.0067   1.0000
  13.750   1.3424   0.04639   0.04141  -0.0092   0.0066   1.0000
  14.000   1.3408   0.04937   0.04447  -0.0090   0.0065   1.0000
  14.250   1.3420   0.05217   0.04737  -0.0092   0.0062   1.0000
  14.500   1.3366   0.05554   0.05083  -0.0088   0.0063   1.0000
  14.750   1.3356   0.05867   0.05405  -0.0091   0.0062   1.0000
  15.000   1.3340   0.06188   0.05735  -0.0094   0.0061   1.0000
  15.250   1.3326   0.06519   0.06075  -0.0099   0.0059   1.0000
  15.500   1.3292   0.06857   0.06424  -0.0099   0.0059   1.0000
  15.750   1.3298   0.07223   0.06796  -0.0119   0.0056   1.0000
  16.000   1.3233   0.07558   0.07144  -0.0108   0.0058   1.0000
  16.250   1.3210   0.07935   0.07528  -0.0121   0.0056   1.0000
  16.500   1.3187   0.08342   0.07942  -0.0140   0.0055   1.0000
  16.750   1.3130   0.08749   0.08359  -0.0148   0.0054   1.0000
  17.000   1.3088   0.09159   0.08777  -0.0161   0.0053   1.0000
  17.250   1.3020   0.09562   0.09193  -0.0164   0.0054   1.0000
  17.500   1.2984   0.10026   0.09660  -0.0192   0.0051   1.0000
  17.750   1.2918   0.10464   0.10109  -0.0203   0.0052   1.0000
  18.000   1.2868   0.10911   0.10561  -0.0222   0.0050   1.0000
  18.250   1.2760   0.11412   0.11073  -0.0236   0.0049   1.0000
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