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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 500,000
Max Cl/Cd: 106.15 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe144-il-500000.txt
Download as CSV file: xf-goe144-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3448   0.08855   0.08645  -0.0227   1.0000   0.0223
  -7.500  -0.3533   0.08687   0.08482  -0.0207   1.0000   0.0232
  -7.250  -0.3693   0.08579   0.08380  -0.0170   1.0000   0.0234
  -7.000  -0.3530   0.08089   0.07890  -0.0261   0.9968   0.0254
  -6.750  -0.3245   0.07533   0.07332  -0.0356   0.9933   0.0257
  -6.500  -0.2980   0.06946   0.06742  -0.0441   0.9890   0.0258
  -6.250  -0.2670   0.06264   0.06054  -0.0539   0.9855   0.0258
  -6.000  -0.2446   0.01912   0.01502  -0.0895   0.9747   0.0201
  -5.750  -0.2095   0.01839   0.01426  -0.0915   0.9727   0.0217
  -5.500  -0.1731   0.01713   0.01277  -0.0937   0.9711   0.0235
  -5.250  -0.1468   0.01594   0.01132  -0.0935   0.9654   0.0249
  -5.000  -0.1134   0.01448   0.00952  -0.0948   0.9622   0.0263
  -4.750  -0.0791   0.01284   0.00766  -0.0965   0.9598   0.0295
  -4.500  -0.0416   0.01207   0.00676  -0.0984   0.9580   0.0322
  -4.250  -0.0126   0.01144   0.00600  -0.0984   0.9520   0.0340
  -4.000   0.0222   0.01050   0.00489  -0.0998   0.9480   0.0367
  -3.750   0.0592   0.00985   0.00420  -0.1015   0.9445   0.0401
  -3.500   0.0896   0.00945   0.00373  -0.1018   0.9367   0.0428
  -3.250   0.1263   0.00899   0.00321  -0.1034   0.9308   0.0466
  -3.000   0.1573   0.00870   0.00293  -0.1038   0.9210   0.0528
  -2.750   0.1901   0.00851   0.00275  -0.1045   0.9109   0.0658
  -2.500   0.2211   0.00839   0.00256  -0.1049   0.8992   0.0795
  -2.250   0.2492   0.00822   0.00235  -0.1046   0.8851   0.0883
  -2.000   0.2758   0.00815   0.00220  -0.1041   0.8675   0.0937
  -1.750   0.3019   0.00803   0.00205  -0.1034   0.8448   0.0991
  -1.500   0.3275   0.00797   0.00191  -0.1026   0.8100   0.1037
  -1.250   0.3518   0.00805   0.00174  -0.1015   0.7601   0.1090
  -1.000   0.3757   0.00823   0.00173  -0.1003   0.7221   0.1156
  -0.750   0.4003   0.00837   0.00170  -0.0994   0.6948   0.1213
  -0.500   0.4253   0.00847   0.00172  -0.0987   0.6720   0.1296
  -0.250   0.4508   0.00855   0.00173  -0.0980   0.6517   0.1405
   0.000   0.4765   0.00863   0.00175  -0.0974   0.6334   0.1528
   0.250   0.5024   0.00871   0.00177  -0.0969   0.6174   0.1640
   0.500   0.5283   0.00875   0.00177  -0.0964   0.6027   0.1730
   0.750   0.5542   0.00879   0.00177  -0.0958   0.5889   0.1799
   1.000   0.5801   0.00884   0.00179  -0.0953   0.5750   0.1865
   1.250   0.6060   0.00891   0.00182  -0.0948   0.5610   0.1926
   1.500   0.6319   0.00896   0.00186  -0.0943   0.5483   0.2007
   1.750   0.6579   0.00904   0.00191  -0.0938   0.5368   0.2081
   2.000   0.6839   0.00909   0.00197  -0.0934   0.5250   0.2185
   2.500   0.7359   0.00917   0.00215  -0.0925   0.5022   0.2662
   2.750   0.7613   0.00911   0.00224  -0.0920   0.4919   0.3368
   3.000   0.7988   0.00795   0.00243  -0.0944   0.4803   1.0000
   3.250   0.8244   0.00808   0.00253  -0.0939   0.4683   1.0000
   3.500   0.8500   0.00822   0.00263  -0.0933   0.4560   1.0000
   3.750   0.8754   0.00838   0.00275  -0.0927   0.4438   1.0000
   4.000   0.9007   0.00854   0.00287  -0.0921   0.4317   1.0000
   4.250   0.9256   0.00872   0.00301  -0.0915   0.4141   1.0000
   4.500   0.9497   0.00897   0.00315  -0.0907   0.3887   1.0000
   4.750   0.9737   0.00923   0.00331  -0.0899   0.3645   1.0000
   5.000   0.9978   0.00951   0.00350  -0.0892   0.3391   1.0000
   5.250   1.0201   0.00994   0.00376  -0.0882   0.3005   1.0000
   5.500   1.0417   0.01046   0.00407  -0.0872   0.2617   1.0000
   5.750   1.0639   0.01095   0.00441  -0.0862   0.2309   1.0000
   6.000   1.0854   0.01150   0.00479  -0.0852   0.1959   1.0000
   6.250   1.1001   0.01275   0.00550  -0.0832   0.1081   1.0000
   6.500   1.1173   0.01376   0.00620  -0.0815   0.0595   1.0000
   6.750   1.1342   0.01479   0.00704  -0.0796   0.0231   1.0000
   7.000   1.1557   0.01531   0.00766  -0.0785   0.0208   1.0000
   7.250   1.1759   0.01597   0.00841  -0.0771   0.0187   1.0000
   7.500   1.1940   0.01681   0.00939  -0.0753   0.0170   1.0000
   7.750   1.2137   0.01745   0.01010  -0.0739   0.0162   1.0000
   8.000   1.2315   0.01821   0.01095  -0.0722   0.0155   1.0000
   8.250   1.2479   0.01906   0.01189  -0.0703   0.0148   1.0000
   8.500   1.2624   0.02000   0.01291  -0.0682   0.0142   1.0000
   8.750   1.2751   0.02103   0.01401  -0.0658   0.0138   1.0000
   9.000   1.2857   0.02214   0.01522  -0.0631   0.0134   1.0000
   9.250   1.2914   0.02340   0.01653  -0.0597   0.0129   1.0000
   9.500   1.2895   0.02523   0.01842  -0.0553   0.0123   1.0000
   9.750   1.2911   0.02727   0.02054  -0.0517   0.0119   1.0000
  10.000   1.3019   0.02833   0.02169  -0.0494   0.0117   1.0000
  10.250   1.3119   0.02962   0.02306  -0.0472   0.0116   1.0000
  10.500   1.3218   0.03090   0.02445  -0.0450   0.0113   1.0000
  10.750   1.3317   0.03251   0.02616  -0.0430   0.0111   1.0000
  11.000   1.3421   0.03431   0.02808  -0.0411   0.0111   1.0000
  11.250   1.3513   0.03607   0.02997  -0.0393   0.0108   1.0000
  11.500   1.3618   0.03832   0.03237  -0.0376   0.0109   1.0000
  11.750   1.3712   0.04089   0.03510  -0.0360   0.0110   1.0000
  12.000   1.3783   0.04403   0.03844  -0.0344   0.0112   1.0000
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