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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 50,000
Max Cl/Cd: 29.21 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe182-il-50000.txt
Download as CSV file: xf-goe182-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2870   0.09837   0.09201  -0.0161   1.0000   0.1850
  -7.000  -0.3025   0.09979   0.09363  -0.0209   1.0000   0.1891
  -6.750  -0.2808   0.09317   0.08702  -0.0159   1.0000   0.1965
  -6.500  -0.2877   0.09295   0.08694  -0.0188   1.0000   0.2044
  -6.250  -0.2781   0.08868   0.08276  -0.0163   1.0000   0.2101
  -6.000  -0.2787   0.08732   0.08150  -0.0172   1.0000   0.2195
  -5.750  -0.2767   0.08451   0.07882  -0.0166   1.0000   0.2246
  -5.500  -0.2737   0.08229   0.07669  -0.0152   1.0000   0.2335
  -5.250  -0.2767   0.08059   0.07512  -0.0161   1.0000   0.2400
  -5.000  -0.2758   0.07830   0.07291  -0.0132   1.0000   0.2478
  -4.750  -0.2800   0.07700   0.07170  -0.0144   1.0000   0.2559
  -4.500  -0.2815   0.07501   0.06981  -0.0113   1.0000   0.2643
  -4.250  -0.2828   0.07327   0.06815  -0.0113   1.0000   0.2738
  -4.000  -0.2805   0.07177   0.06669  -0.0125   1.0000   0.2875
  -3.750  -0.2764   0.07011   0.06508  -0.0130   1.0000   0.3026
  -3.500  -0.2714   0.06827   0.06329  -0.0129   1.0000   0.3183
  -3.250  -0.2658   0.06630   0.06138  -0.0126   1.0000   0.3344
  -3.000  -0.2441   0.06326   0.05837  -0.0133   0.9942   0.3559
  -2.750  -0.1953   0.05953   0.05460  -0.0192   0.9774   0.4037
  -2.500  -0.1595   0.05618   0.05129  -0.0201   0.9606   0.4684
  -2.000   0.1417   0.04049   0.03309  -0.0922   0.9235   0.2043
  -1.750   0.2100   0.03655   0.02839  -0.1004   0.9051   0.1884
  -1.500   0.2720   0.03357   0.02494  -0.1062   0.8862   0.1866
  -1.250   0.3266   0.03130   0.02235  -0.1100   0.8665   0.1957
  -1.000   0.3798   0.02921   0.01968  -0.1127   0.8474   0.2051
  -0.750   0.4160   0.02790   0.01828  -0.1127   0.8232   0.2237
  -0.500   0.4559   0.02653   0.01669  -0.1126   0.8014   0.2516
  -0.250   0.4883   0.02548   0.01559  -0.1115   0.7761   0.2947
   0.000   0.5199   0.02402   0.01446  -0.1099   0.7530   0.4017
   0.250   0.5471   0.02174   0.01336  -0.1075   0.7274   1.0000
   0.500   0.5754   0.02201   0.01298  -0.1059   0.7026   1.0000
   0.750   0.6002   0.02250   0.01309  -0.1044   0.6754   1.0000
   1.000   0.6255   0.02298   0.01322  -0.1031   0.6512   1.0000
   1.250   0.6507   0.02350   0.01345  -0.1019   0.6286   1.0000
   1.500   0.6767   0.02397   0.01361  -0.1007   0.6095   1.0000
   1.750   0.7026   0.02448   0.01384  -0.0998   0.5922   1.0000
   2.000   0.7282   0.02509   0.01424  -0.0989   0.5760   1.0000
   2.250   0.7536   0.02580   0.01478  -0.0983   0.5613   1.0000
   2.500   0.7783   0.02670   0.01559  -0.0979   0.5480   1.0000
   2.750   0.8029   0.02771   0.01653  -0.0975   0.5368   1.0000
   3.000   0.8299   0.02841   0.01703  -0.0970   0.5287   1.0000
   3.250   0.8523   0.02977   0.01848  -0.0969   0.5186   1.0000
   3.500   0.8782   0.03066   0.01925  -0.0964   0.5117   1.0000
   3.750   0.8993   0.03222   0.02094  -0.0963   0.5034   1.0000
   4.000   0.9255   0.03308   0.02170  -0.0959   0.4978   1.0000
   4.250   0.9437   0.03514   0.02394  -0.0960   0.4913   1.0000
   4.500   0.9641   0.03692   0.02582  -0.0959   0.4864   1.0000
   4.750   0.9874   0.03835   0.02728  -0.0957   0.4828   1.0000
   5.000   1.0063   0.04048   0.02951  -0.0958   0.4797   1.0000
   5.250   1.0125   0.04438   0.03369  -0.0965   0.4765   1.0000
   5.500   1.0151   0.04876   0.03828  -0.0973   0.4742   1.0000
   5.750   1.0107   0.05401   0.04371  -0.0985   0.4724   1.0000
   6.000   0.9817   0.06249   0.05234  -0.1013   0.4732   1.0000
   6.250   0.9560   0.07043   0.06033  -0.1041   0.4782   1.0000
   6.500   0.9691   0.07394   0.06389  -0.1048   0.4809   1.0000
   6.750   0.7549   0.09987   0.08997  -0.1218   0.6587   1.0000
   7.000   0.7684   0.10285   0.09295  -0.1219   0.6533   1.0000
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