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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 500,000
Max Cl/Cd: 107.45 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe184-il-500000.txt
Download as CSV file: xf-goe184-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 184 (MVA H.29) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3191   0.09284   0.09067  -0.0231   1.0000   0.0230
  -8.000  -0.3133   0.08994   0.08780  -0.0244   1.0000   0.0237
  -7.750  -0.3098   0.08703   0.08492  -0.0257   1.0000   0.0245
  -7.500  -0.2305   0.06529   0.06337  -0.0410   0.9874   0.0267
  -7.250  -0.2127   0.06190   0.05997  -0.0428   0.9803   0.0272
  -7.000  -0.1944   0.05861   0.05667  -0.0455   0.9706   0.0280
  -6.750  -0.1789   0.05503   0.05308  -0.0491   0.9560   0.0293
  -6.500  -0.1671   0.05044   0.04844  -0.0543   0.9368   0.0313
  -6.250  -0.1466   0.04309   0.04097  -0.0665   0.9183   0.0327
  -6.000  -0.1398   0.03826   0.03609  -0.0677   0.8998   0.0338
  -5.750  -0.1238   0.03631   0.03405  -0.0678   0.8813   0.0347
  -5.500  -0.1047   0.03353   0.03117  -0.0699   0.8644   0.0364
  -5.250  -0.0718   0.02074   0.01678  -0.0998   0.9021   0.0333
  -5.000  -0.0461   0.01808   0.01361  -0.1001   0.8852   0.0331
  -4.750  -0.0205   0.01521   0.01019  -0.1003   0.8688   0.0336
  -4.500   0.0057   0.01378   0.00846  -0.1001   0.8522   0.0345
  -4.250   0.0326   0.01282   0.00722  -0.0998   0.8358   0.0350
  -4.000   0.0597   0.01207   0.00625  -0.0995   0.8198   0.0356
  -3.750   0.0871   0.01147   0.00546  -0.0992   0.8046   0.0363
  -3.500   0.1147   0.01100   0.00484  -0.0989   0.7904   0.0374
  -3.250   0.1426   0.01057   0.00426  -0.0987   0.7777   0.0382
  -3.000   0.1705   0.01019   0.00377  -0.0985   0.7653   0.0388
  -2.750   0.1984   0.00989   0.00335  -0.0983   0.7528   0.0394
  -2.500   0.2263   0.00966   0.00299  -0.0981   0.7404   0.0400
  -2.250   0.2544   0.00943   0.00268  -0.0979   0.7278   0.0409
  -2.000   0.2827   0.00923   0.00243  -0.0978   0.7151   0.0434
  -1.750   0.3108   0.00910   0.00225  -0.0976   0.7019   0.0460
  -1.500   0.3389   0.00902   0.00219  -0.0975   0.6877   0.0521
  -1.250   0.3670   0.00905   0.00220  -0.0973   0.6722   0.0657
  -1.000   0.3950   0.00909   0.00218  -0.0971   0.6547   0.0726
  -0.750   0.4228   0.00920   0.00219  -0.0969   0.6355   0.0788
  -0.500   0.4505   0.00921   0.00213  -0.0967   0.6147   0.0847
  -0.250   0.4780   0.00929   0.00211  -0.0966   0.5938   0.0897
   0.000   0.5055   0.00940   0.00211  -0.0964   0.5761   0.0929
   0.250   0.5331   0.00942   0.00206  -0.0963   0.5615   0.0960
   0.500   0.5609   0.00944   0.00204  -0.0962   0.5493   0.0994
   0.750   0.5886   0.00950   0.00206  -0.0961   0.5386   0.1029
   1.000   0.6163   0.00957   0.00207  -0.0960   0.5289   0.1051
   1.250   0.6442   0.00962   0.00211  -0.0959   0.5198   0.1077
   1.500   0.6719   0.00966   0.00213  -0.0959   0.5108   0.1124
   1.750   0.6997   0.00970   0.00218  -0.0958   0.4999   0.1179
   2.000   0.7275   0.00975   0.00222  -0.0957   0.4890   0.1234
   2.250   0.7552   0.00979   0.00229  -0.0956   0.4786   0.1399
   2.500   0.7831   0.00957   0.00244  -0.0958   0.4682   0.2976
   2.750   0.8047   0.00822   0.00258  -0.0946   0.4587   1.0000
   3.000   0.8322   0.00837   0.00266  -0.0945   0.4485   1.0000
   3.250   0.8598   0.00851   0.00274  -0.0943   0.4372   1.0000
   3.500   0.8873   0.00865   0.00283  -0.0942   0.4253   1.0000
   3.750   0.9146   0.00882   0.00294  -0.0941   0.4124   1.0000
   4.000   0.9417   0.00900   0.00307  -0.0940   0.4002   1.0000
   4.250   0.9687   0.00921   0.00321  -0.0938   0.3893   1.0000
   4.500   0.9958   0.00939   0.00337  -0.0937   0.3797   1.0000
   4.750   1.0227   0.00959   0.00355  -0.0935   0.3715   1.0000
   5.250   1.0758   0.01005   0.00393  -0.0931   0.3503   1.0000
   5.500   1.1024   0.01028   0.00414  -0.0929   0.3416   1.0000
   5.750   1.1285   0.01054   0.00438  -0.0927   0.3320   1.0000
   6.000   1.1551   0.01075   0.00459  -0.0925   0.3223   1.0000
   6.250   1.1812   0.01100   0.00484  -0.0923   0.3118   1.0000
   6.500   1.2069   0.01128   0.00510  -0.0920   0.2993   1.0000
   6.750   1.2327   0.01155   0.00535  -0.0917   0.2838   1.0000
   7.000   1.2579   0.01188   0.00562  -0.0914   0.2606   1.0000
   7.250   1.2803   0.01253   0.00602  -0.0908   0.2099   1.0000
   7.500   1.2997   0.01354   0.00674  -0.0898   0.1669   1.0000
   7.750   1.3214   0.01424   0.00735  -0.0890   0.1476   1.0000
   8.000   1.3431   0.01492   0.00792  -0.0883   0.1197   1.0000
   8.250   1.3581   0.01633   0.00894  -0.0867   0.0654   1.0000
   8.500   1.3716   0.01782   0.01019  -0.0849   0.0320   1.0000
   8.750   1.3916   0.01856   0.01102  -0.0838   0.0289   1.0000
   9.000   1.4088   0.01951   0.01206  -0.0823   0.0262   1.0000
   9.250   1.4235   0.02064   0.01328  -0.0806   0.0240   1.0000
   9.500   1.4413   0.02140   0.01412  -0.0792   0.0227   1.0000
   9.750   1.4565   0.02230   0.01511  -0.0776   0.0213   1.0000
  10.000   1.4681   0.02341   0.01629  -0.0755   0.0202   1.0000
  10.250   1.4694   0.02493   0.01790  -0.0720   0.0193   1.0000
  10.500   1.4674   0.02674   0.01983  -0.0685   0.0186   1.0000
  10.750   1.4765   0.02790   0.02109  -0.0666   0.0182   1.0000
  11.000   1.4831   0.02932   0.02261  -0.0647   0.0176   1.0000
  11.250   1.4886   0.03094   0.02433  -0.0630   0.0169   1.0000
  11.500   1.4938   0.03271   0.02618  -0.0616   0.0163   1.0000
  11.750   1.4976   0.03471   0.02827  -0.0604   0.0157   1.0000
  12.000   1.4991   0.03710   0.03073  -0.0594   0.0153   1.0000
  12.250   1.4963   0.04003   0.03374  -0.0585   0.0149   1.0000
  12.500   1.4887   0.04358   0.03739  -0.0575   0.0146   1.0000
  12.750   1.4812   0.04712   0.04103  -0.0564   0.0143   1.0000
  13.000   1.4844   0.04968   0.04371  -0.0561   0.0141   1.0000
  13.250   1.4857   0.05245   0.04659  -0.0558   0.0138   1.0000
  13.500   1.4859   0.05539   0.04964  -0.0555   0.0136   1.0000
  13.750   1.4855   0.05843   0.05279  -0.0553   0.0133   1.0000
  14.000   1.4846   0.06153   0.05600  -0.0551   0.0131   1.0000
  14.250   1.4836   0.06471   0.05928  -0.0550   0.0128   1.0000
  14.500   1.4827   0.06797   0.06264  -0.0551   0.0125   1.0000
  14.750   1.4814   0.07136   0.06612  -0.0554   0.0123   1.0000
  15.000   1.4796   0.07490   0.06976  -0.0559   0.0120   1.0000
  15.250   1.4776   0.07855   0.07349  -0.0566   0.0118   1.0000
  15.500   1.4753   0.08223   0.07725  -0.0572   0.0116   1.0000
  15.750   1.4727   0.08584   0.08093  -0.0577   0.0113   1.0000
  16.000   1.4696   0.08920   0.08436  -0.0573   0.0111   1.0000
  16.250   1.4637   0.09299   0.08829  -0.0565   0.0108   1.0000
  16.500   1.4573   0.09770   0.09315  -0.0581   0.0108   1.0000
  16.750   1.4500   0.10264   0.09825  -0.0599   0.0107   1.0000
  17.000   1.4423   0.10770   0.10347  -0.0618   0.0106   1.0000
  17.250   1.4337   0.11305   0.10898  -0.0640   0.0105   1.0000
  17.500   1.4244   0.11861   0.11470  -0.0664   0.0105   1.0000
  17.750   1.4142   0.12451   0.12077  -0.0692   0.0104   1.0000
  18.000   1.4030   0.13074   0.12716  -0.0723   0.0104   1.0000
  18.250   1.3909   0.13736   0.13395  -0.0758   0.0103   1.0000
  18.500   1.3788   0.14423   0.14099  -0.0798   0.0103   1.0000
  18.750   1.3656   0.15158   0.14850  -0.0842   0.0103   1.0000
  19.000   1.3517   0.15934   0.15641  -0.0891   0.0103   1.0000
  19.250   1.3371   0.16759   0.16482  -0.0945   0.0103   1.0000
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