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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 200,000
Max Cl/Cd: 64.23 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe54-il-200000-n5.txt
Download as CSV file: xf-goe54-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5327   0.10548   0.10213   0.0370   1.0000   0.0234
  -8.000  -0.5267   0.10210   0.09878   0.0349   1.0000   0.0239
  -7.750  -0.5207   0.09874   0.09545   0.0321   1.0000   0.0244
  -7.500  -0.5126   0.09519   0.09192   0.0276   1.0000   0.0246
  -7.250  -0.4962   0.09084   0.08756   0.0177   1.0000   0.0248
  -7.000  -0.4789   0.08618   0.08288   0.0111   1.0000   0.0249
  -6.750  -0.4707   0.08238   0.07911   0.0129   1.0000   0.0251
  -6.500  -0.4579   0.07870   0.07545   0.0117   1.0000   0.0254
  -6.250  -0.4418   0.07499   0.07174   0.0089   1.0000   0.0258
  -6.000  -0.4229   0.07121   0.06794   0.0053   1.0000   0.0263
  -5.750  -0.4013   0.06735   0.06405   0.0013   1.0000   0.0271
  -5.500  -0.3747   0.06342   0.06004  -0.0036   1.0000   0.0286
  -5.250  -0.3304   0.05913   0.05540  -0.0124   1.0000   0.0295
  -5.000  -0.3005   0.05540   0.05146  -0.0158   1.0000   0.0296
  -4.750  -0.2848   0.05135   0.04751  -0.0163   1.0000   0.0299
  -4.500  -0.2636   0.04884   0.04424  -0.0168   0.6746   0.0303
  -4.250  -0.2416   0.04639   0.04144  -0.0177   0.5982   0.0310
  -4.000  -0.2156   0.04399   0.03869  -0.0191   0.5512   0.0325
  -3.500  -0.1450   0.04022   0.03387  -0.0220   0.5050   0.0352
  -3.250  -0.1180   0.03734   0.03074  -0.0229   0.4899   0.0355
  -3.000  -0.0944   0.03438   0.02774  -0.0238   0.4765   0.0360
  -2.750  -0.0687   0.03233   0.02557  -0.0246   0.4646   0.0370
  -2.500  -0.0403   0.03068   0.02370  -0.0251   0.4537   0.0390
  -2.250  -0.0058   0.03028   0.02275  -0.0249   0.4430   0.0416
  -2.000   0.0243   0.02878   0.02089  -0.0251   0.4328   0.0420
  -1.750   0.0505   0.02625   0.01835  -0.0259   0.4229   0.0427
  -1.500   0.0785   0.02475   0.01674  -0.0262   0.4126   0.0439
  -1.250   0.1075   0.02365   0.01542  -0.0264   0.4032   0.0459
  -1.000   0.1379   0.02282   0.01426  -0.0262   0.3934   0.0496
  -0.750   0.1660   0.02162   0.01299  -0.0265   0.3833   0.0522
  -0.500   0.1960   0.02110   0.01213  -0.0263   0.3732   0.0567
  -0.250   0.2242   0.01994   0.01092  -0.0265   0.3619   0.0589
   0.250   0.2818   0.01868   0.00935  -0.0263   0.3385   0.0706
   0.500   0.3125   0.01817   0.00853  -0.0254   0.3268   0.0478
   0.750   0.3412   0.01733   0.00761  -0.0252   0.3146   0.0443
   1.000   0.3697   0.01690   0.00707  -0.0250   0.3032   0.0455
   1.250   0.3984   0.01658   0.00656  -0.0246   0.2934   0.0429
   1.500   0.4268   0.01636   0.00621  -0.0243   0.2840   0.0412
   1.750   0.4549   0.01596   0.00578  -0.0242   0.2755   0.0407
   2.000   0.4829   0.01569   0.00546  -0.0240   0.2671   0.0405
   2.250   0.5110   0.01547   0.00522  -0.0238   0.2604   0.0405
   2.500   0.5390   0.01531   0.00505  -0.0237   0.2545   0.0407
   2.750   0.5669   0.01529   0.00497  -0.0235   0.2497   0.0421
   3.000   0.5949   0.01507   0.00484  -0.0235   0.2455   0.0441
   3.250   0.6231   0.01500   0.00482  -0.0234   0.2411   0.0445
   3.500   0.6511   0.01501   0.00482  -0.0234   0.2368   0.0451
   3.750   0.6789   0.01511   0.00486  -0.0233   0.2326   0.0459
   4.000   0.7069   0.01520   0.00495  -0.0232   0.2285   0.0470
   4.250   0.7348   0.01531   0.00507  -0.0230   0.2239   0.0488
   4.500   0.7626   0.01544   0.00518  -0.0229   0.2195   0.0534
   4.750   0.7899   0.01569   0.00536  -0.0227   0.2155   0.0558
   5.000   0.8176   0.01585   0.00557  -0.0226   0.2117   0.0600
   5.250   0.8455   0.01588   0.00588  -0.0225   0.2075   0.2290
   5.750   0.8954   0.01500   0.00641  -0.0213   0.1996   1.0000
   6.000   0.9227   0.01530   0.00676  -0.0211   0.1956   1.0000
   6.250   0.9501   0.01559   0.00710  -0.0210   0.1911   1.0000
   6.500   0.9771   0.01590   0.00743  -0.0208   0.1869   1.0000
   6.750   1.0038   0.01630   0.00780  -0.0207   0.1832   1.0000
   7.000   1.0310   0.01658   0.00822  -0.0205   0.1780   1.0000
   7.250   1.0579   0.01683   0.00851  -0.0204   0.1720   1.0000
   7.500   1.0846   0.01714   0.00886  -0.0203   0.1664   1.0000
   7.750   1.1113   0.01746   0.00929  -0.0201   0.1611   1.0000
   8.000   1.1377   0.01780   0.00964  -0.0200   0.1564   1.0000
   8.250   1.1641   0.01816   0.01011  -0.0198   0.1507   1.0000
   8.500   1.1902   0.01853   0.01055  -0.0197   0.1452   1.0000
   8.750   1.2159   0.01898   0.01105  -0.0195   0.1410   1.0000
   9.000   1.2416   0.01943   0.01164  -0.0193   0.1364   1.0000
   9.250   1.2669   0.01992   0.01220  -0.0191   0.1314   1.0000
   9.500   1.2919   0.02046   0.01284  -0.0189   0.1267   1.0000
   9.750   1.3167   0.02101   0.01352  -0.0188   0.1208   1.0000
  10.000   1.3405   0.02169   0.01424  -0.0186   0.1148   1.0000
  10.250   1.3650   0.02228   0.01504  -0.0184   0.1084   1.0000
  10.500   1.3879   0.02308   0.01590  -0.0182   0.1008   1.0000
  10.750   1.4111   0.02383   0.01679  -0.0180   0.0895   1.0000
  11.000   1.4329   0.02479   0.01782  -0.0178   0.0745   1.0000
  11.250   1.4518   0.02619   0.01919  -0.0177   0.0641   1.0000
  11.500   1.4687   0.02784   0.02089  -0.0175   0.0578   1.0000
  11.750   1.4858   0.02932   0.02253  -0.0172   0.0536   1.0000
  12.000   1.4994   0.03121   0.02456  -0.0169   0.0501   1.0000
  12.250   1.5113   0.03319   0.02670  -0.0167   0.0473   1.0000
  12.500   1.5225   0.03510   0.02883  -0.0165   0.0448   1.0000
  12.750   1.5279   0.03763   0.03154  -0.0166   0.0426   1.0000
  13.000   1.5232   0.04117   0.03527  -0.0174   0.0411   1.0000
  13.250   1.5057   0.04863   0.04300  -0.0244   0.0408   1.0000
  13.500   1.4837   0.05715   0.05172  -0.0310   0.0406   1.0000
  13.750   1.4584   0.06510   0.05982  -0.0357   0.0406   1.0000
  14.000   1.4328   0.07280   0.06765  -0.0398   0.0406   1.0000
  14.250   1.4082   0.08029   0.07525  -0.0434   0.0405   1.0000
  14.500   1.3858   0.08744   0.08249  -0.0468   0.0402   1.0000
  14.750   1.3661   0.09417   0.08927  -0.0499   0.0397   1.0000
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