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GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il)
Reynolds number: 50,000
Max Cl/Cd: 34.34 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe309-il-50000.txt
Download as CSV file: xf-goe309-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 309 (MVA H.41) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3566   0.10629   0.09996  -0.0167   1.0000   0.1353
  -8.000  -0.3617   0.10468   0.09845  -0.0192   1.0000   0.1394
  -7.750  -0.3737   0.10435   0.09826  -0.0240   1.0000   0.1408
  -7.500  -0.3513   0.09745   0.09135  -0.0196   1.0000   0.1491
  -7.250  -0.3574   0.09611   0.09011  -0.0231   1.0000   0.1543
  -7.000  -0.3501   0.09181   0.08588  -0.0223   1.0000   0.1593
  -6.750  -0.3479   0.08928   0.08342  -0.0229   1.0000   0.1671
  -6.500  -0.3534   0.08769   0.08193  -0.0253   1.0000   0.1710
  -6.250  -0.3450   0.08348   0.07779  -0.0221   1.0000   0.1784
  -6.000  -0.3561   0.08406   0.07837  -0.0252   1.0000   0.1847
  -5.750  -0.3493   0.07878   0.07326  -0.0203   1.0000   0.1907
  -5.500  -0.3582   0.07917   0.07359  -0.0220   1.0000   0.1994
  -5.250  -0.3565   0.07461   0.06920  -0.0173   1.0000   0.2050
  -5.000  -0.3602   0.07355   0.06810  -0.0177   1.0000   0.2151
  -4.750  -0.3597   0.07052   0.06515  -0.0145   1.0000   0.2244
  -4.500  -0.3591   0.06810   0.06275  -0.0131   1.0000   0.2360
  -4.250  -0.3571   0.06586   0.06052  -0.0119   1.0000   0.2528
  -4.000  -0.3536   0.06363   0.05823  -0.0115   1.0000   0.2740
  -3.750  -0.3491   0.06146   0.05602  -0.0106   1.0000   0.3010
  -3.500  -0.3455   0.05855   0.05316  -0.0086   1.0000   0.3297
  -3.250  -0.3431   0.05534   0.05005  -0.0054   1.0000   0.3622
  -3.000  -0.3421   0.05244   0.04724  -0.0017   1.0000   0.4093
  -2.750  -0.3381   0.04973   0.04456   0.0009   1.0000   0.4602
  -2.500  -0.3320   0.04674   0.04165   0.0042   1.0000   0.5011
  -2.250  -0.3246   0.04389   0.03888   0.0073   1.0000   0.5426
  -2.000  -0.2929   0.04066   0.03560   0.0054   0.9942   0.5842
  -1.750  -0.2026   0.03790   0.03221  -0.0129   0.9815   0.5608
  -1.500  -0.0386   0.03989   0.03141  -0.0425   0.9634   0.2122
  -1.250   0.0188   0.03776   0.02848  -0.0475   0.9519   0.1835
  -1.000   0.0708   0.03600   0.02628  -0.0520   0.9405   0.1786
  -0.750   0.1200   0.03498   0.02471  -0.0558   0.9279   0.1846
  -0.500   0.1629   0.03384   0.02336  -0.0587   0.9149   0.1884
  -0.250   0.2076   0.03315   0.02230  -0.0613   0.9021   0.1980
   0.000   0.2516   0.03256   0.02163  -0.0641   0.8893   0.2256
   0.250   0.2924   0.03182   0.02094  -0.0661   0.8773   0.2730
   0.500   0.3725   0.02847   0.01927  -0.0740   0.8702   1.0000
   0.750   0.4079   0.02899   0.01933  -0.0754   0.8563   1.0000
   1.000   0.4389   0.02956   0.01962  -0.0762   0.8426   1.0000
   1.250   0.4677   0.03016   0.02002  -0.0767   0.8290   1.0000
   1.500   0.4938   0.03084   0.02054  -0.0767   0.8156   1.0000
   1.750   0.5192   0.03154   0.02111  -0.0765   0.8024   1.0000
   2.000   0.5438   0.03228   0.02175  -0.0763   0.7896   1.0000
   2.250   0.5694   0.03297   0.02237  -0.0760   0.7771   1.0000
   2.500   0.5974   0.03355   0.02288  -0.0759   0.7651   1.0000
   2.750   0.6331   0.03371   0.02298  -0.0764   0.7540   1.0000
   3.000   0.6544   0.03444   0.02368  -0.0753   0.7403   1.0000
   3.250   0.6775   0.03501   0.02426  -0.0742   0.7262   1.0000
   3.500   0.7026   0.03538   0.02461  -0.0730   0.7118   1.0000
   3.750   0.7286   0.03560   0.02483  -0.0718   0.6971   1.0000
   4.000   0.7543   0.03578   0.02503  -0.0704   0.6824   1.0000
   4.250   0.7797   0.03595   0.02526  -0.0689   0.6677   1.0000
   4.500   0.8045   0.03613   0.02548  -0.0674   0.6531   1.0000
   4.750   0.8291   0.03633   0.02573  -0.0659   0.6385   1.0000
   5.000   0.8540   0.03649   0.02595  -0.0644   0.6238   1.0000
   5.250   0.8751   0.03694   0.02652  -0.0627   0.6078   1.0000
   5.500   0.8931   0.03768   0.02736  -0.0609   0.5908   1.0000
   5.750   0.9153   0.03804   0.02782  -0.0592   0.5741   1.0000
   6.000   0.9398   0.03818   0.02806  -0.0576   0.5576   1.0000
   6.250   0.9657   0.03826   0.02828  -0.0560   0.5414   1.0000
   6.500   0.9929   0.03826   0.02837  -0.0545   0.5254   1.0000
   6.750   1.0209   0.03822   0.02841  -0.0531   0.5095   1.0000
   7.000   1.0435   0.03881   0.02912  -0.0516   0.4933   1.0000
   7.250   1.0596   0.04022   0.03075  -0.0501   0.4776   1.0000
   7.500   1.0774   0.04134   0.03202  -0.0486   0.4621   1.0000
   7.750   1.1193   0.03762   0.02817  -0.0459   0.4346   1.0000
   8.000   1.1384   0.03778   0.02847  -0.0440   0.4152   1.0000
   8.250   1.1693   0.03602   0.02663  -0.0420   0.3927   1.0000
   8.500   1.1840   0.03636   0.02718  -0.0399   0.3737   1.0000
   8.750   1.2025   0.03639   0.02737  -0.0380   0.3565   1.0000
   9.000   1.2223   0.03570   0.02671  -0.0358   0.3370   1.0000
   9.250   1.2358   0.03599   0.02721  -0.0336   0.3206   1.0000
   9.500   1.2420   0.03619   0.02762  -0.0305   0.2993   1.0000
   9.750   1.2443   0.03653   0.02809  -0.0271   0.2757   1.0000
  10.000   1.2376   0.03750   0.02903  -0.0232   0.2478   1.0000
  10.250   1.2279   0.03907   0.03056  -0.0195   0.2219   1.0000
  10.500   1.2182   0.04135   0.03283  -0.0168   0.1947   1.0000
  10.750   1.2069   0.04443   0.03591  -0.0151   0.1633   1.0000
  11.000   1.1947   0.04816   0.03957  -0.0142   0.1309   1.0000
  11.250   1.1830   0.05221   0.04346  -0.0137   0.1095   1.0000
  11.500   1.1721   0.05637   0.04746  -0.0135   0.0989   1.0000
  11.750   1.1623   0.06056   0.05154  -0.0135   0.0925   1.0000
  12.000   1.1564   0.06437   0.05535  -0.0132   0.0873   1.0000
  12.250   1.1522   0.06800   0.05900  -0.0128   0.0830   1.0000
  12.500   1.1485   0.07146   0.06237  -0.0123   0.0795   1.0000
  12.750   1.1514   0.07439   0.06548  -0.0114   0.0759   1.0000
  13.000   1.1544   0.07730   0.06852  -0.0106   0.0724   1.0000
  13.250   1.1605   0.07974   0.07094  -0.0093   0.0691   1.0000
  13.500   1.1748   0.08163   0.07294  -0.0070   0.0667   1.0000
  13.750   1.1839   0.08470   0.07640  -0.0058   0.0658   1.0000
  14.000   1.1845   0.08891   0.08092  -0.0058   0.0654   1.0000
  14.250   1.1773   0.09411   0.08642  -0.0068   0.0654   1.0000
  14.500   1.1643   0.10018   0.09276  -0.0089   0.0657   1.0000
  14.750   1.1476   0.10701   0.09983  -0.0118   0.0661   1.0000
  15.000   1.1282   0.11465   0.10766  -0.0156   0.0666   1.0000
  15.250   1.1086   0.12284   0.11600  -0.0199   0.0672   1.0000
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