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GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 561 AIRFOIL (goe561-il)
Reynolds number: 1,000,000
Max Cl/Cd: 42.02 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe561-il-1000000-n5.txt
Download as CSV file: xf-goe561-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 561 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500   0.5413   0.09905   0.09420  -0.1726   0.4814   0.0190
 -12.250   0.5484   0.09711   0.09225  -0.1734   0.4792   0.0210
 -12.000   0.5532   0.09473   0.08987  -0.1741   0.4779   0.0211
 -11.750   0.5635   0.09327   0.08841  -0.1742   0.4760   0.0200
 -11.500   0.5692   0.09116   0.08629  -0.1747   0.4743   0.0205
 -11.250   0.5748   0.08911   0.08425  -0.1751   0.4729   0.0199
 -11.000   0.5793   0.08682   0.08198  -0.1756   0.4723   0.0206
 -10.750   0.5845   0.08474   0.07992  -0.1759   0.4718   0.0198
 -10.500   0.5893   0.08267   0.07787  -0.1762   0.4709   0.0200
 -10.250   0.5944   0.08068   0.07590  -0.1765   0.4697   0.0201
 -10.000   0.5964   0.07835   0.07358  -0.1767   0.4689   0.0197
  -9.750   0.5982   0.07608   0.07134  -0.1769   0.4679   0.0195
  -9.500   0.6014   0.07409   0.06936  -0.1770   0.4660   0.0198
  -9.250   0.6017   0.07183   0.06712  -0.1770   0.4641   0.0202
  -9.000   0.6036   0.06990   0.06521  -0.1769   0.4627   0.0201
  -8.750   0.6013   0.06757   0.06290  -0.1767   0.4614   0.0200
  -8.500   0.5975   0.06524   0.06058  -0.1763   0.4599   0.0201
  -8.250   0.5914   0.06286   0.05822  -0.1758   0.4582   0.0198
  -8.000   0.5832   0.06043   0.05583  -0.1753   0.4569   0.0199
  -7.750   0.5698   0.05782   0.05325  -0.1746   0.4555   0.0199
  -7.500   0.5418   0.05447   0.04996  -0.1746   0.4549   0.0202
  -7.250   0.5121   0.05216   0.04768  -0.1710   0.4536   0.0200
  -7.000   0.4695   0.05019   0.04573  -0.1635   0.4533   0.0204
  -6.750   0.4353   0.04887   0.04444  -0.1555   0.4528   0.0204
  -6.500   0.4061   0.04689   0.04246  -0.1483   0.4521   0.0204
  -6.250   0.3810   0.04476   0.04030  -0.1416   0.4514   0.0204
  -6.000   0.3576   0.04244   0.03793  -0.1348   0.4507   0.0205
  -5.750   0.3373   0.04032   0.03575  -0.1279   0.4499   0.0205
  -5.250   0.1543   0.02374   0.01805  -0.0882   0.4502   0.0215
  -5.000   0.1674   0.02366   0.01794  -0.0855   0.4487   0.0215
  -4.750   0.1774   0.02329   0.01752  -0.0823   0.4469   0.0216
  -4.500   0.1576   0.02004   0.01383  -0.0733   0.4461   0.0220
  -4.250   0.1709   0.01992   0.01367  -0.0705   0.4442   0.0221
  -4.000   0.1854   0.01994   0.01367  -0.0680   0.4425   0.0222
  -3.750   0.1961   0.01948   0.01311  -0.0647   0.4409   0.0223
  -3.500   0.2033   0.01851   0.01193  -0.0608   0.4391   0.0226
  -3.250   0.2146   0.01777   0.01101  -0.0576   0.4367   0.0227
  -3.000   0.2302   0.01753   0.01070  -0.0553   0.4354   0.0229
  -2.750   0.2482   0.01712   0.01020  -0.0535   0.4340   0.0231
  -2.500   0.2669   0.01681   0.00983  -0.0518   0.4324   0.0233
  -2.250   0.2868   0.01649   0.00943  -0.0503   0.4308   0.0234
  -2.000   0.3065   0.01626   0.00914  -0.0489   0.4291   0.0237
  -1.750   0.3260   0.01609   0.00890  -0.0474   0.4270   0.0238
  -1.500   0.3455   0.01600   0.00876  -0.0460   0.4251   0.0240
  -1.250   0.3637   0.01595   0.00866  -0.0444   0.4222   0.0242
  -1.000   0.3799   0.01607   0.00875  -0.0425   0.4199   0.0244
  -0.750   0.4021   0.01595   0.00858  -0.0417   0.4180   0.0244
  -0.500   0.4242   0.01595   0.00857  -0.0409   0.4159   0.0246
  -0.250   0.4490   0.01581   0.00841  -0.0407   0.4139   0.0248
   0.000   0.4715   0.01581   0.00840  -0.0401   0.4116   0.0250
   0.250   0.4906   0.01597   0.00855  -0.0389   0.4084   0.0253
   0.500   0.5106   0.01610   0.00866  -0.0380   0.4050   0.0257
   0.750   0.5317   0.01624   0.00877  -0.0373   0.4020   0.0257
   1.000   0.5547   0.01636   0.00891  -0.0369   0.4005   0.0261
   1.250   0.5795   0.01645   0.00899  -0.0369   0.3968   0.0264
   1.500   0.6031   0.01661   0.00913  -0.0368   0.3941   0.0267
   1.750   0.6254   0.01683   0.00933  -0.0365   0.3904   0.0271
   2.000   0.6473   0.01713   0.00960  -0.0364   0.3869   0.0275
   2.250   0.6788   0.01726   0.00974  -0.0379   0.3839   0.0277
   2.500   0.7051   0.01750   0.00997  -0.0385   0.3807   0.0280
   2.750   0.7307   0.01781   0.01026  -0.0393   0.3753   0.0283
   3.000   0.7501   0.01827   0.01071  -0.0389   0.3717   0.0288
   3.250   0.7734   0.01858   0.01103  -0.0391   0.3689   0.0295
   3.500   0.7951   0.01892   0.01138  -0.0390   0.3656   0.0299
   3.750   0.8136   0.01941   0.01186  -0.0385   0.3618   0.0305
   4.000   0.8306   0.01996   0.01240  -0.0378   0.3584   0.0309
   4.250   0.8472   0.02055   0.01298  -0.0371   0.3551   0.0318
   4.500   0.8668   0.02103   0.01348  -0.0369   0.3521   0.0327
   4.750   0.8850   0.02156   0.01402  -0.0365   0.3490   0.0331
   5.000   0.8991   0.02232   0.01478  -0.0356   0.3451   0.0343
   5.250   0.9125   0.02311   0.01556  -0.0347   0.3419   0.0355
   5.500   0.9280   0.02383   0.01630  -0.0341   0.3394   0.0365
   5.750   0.9433   0.02458   0.01706  -0.0335   0.3357   0.0371
   6.000   0.9593   0.02527   0.01777  -0.0330   0.3334   0.0396
   6.250   0.9698   0.02633   0.01883  -0.0320   0.3299   0.0411
   6.500   0.9790   0.02744   0.01994  -0.0308   0.3261   0.0433
   6.750   0.9926   0.02833   0.02086  -0.0302   0.3243   0.0452
   7.000   1.0034   0.02939   0.02192  -0.0294   0.3191   0.0484
   7.500   1.0271   0.03145   0.02404  -0.0280   0.3154   0.0595
   7.750   1.0349   0.03276   0.02536  -0.0270   0.3124   0.0660
   8.250   1.3482   0.03612   0.03079  -0.0857   0.3028   1.0000
   8.500   1.3507   0.03789   0.03256  -0.0843   0.2994   1.0000
   8.750   1.3573   0.03938   0.03407  -0.0832   0.2985   1.0000
   9.000   1.3590   0.04129   0.03599  -0.0819   0.2954   1.0000
   9.250   1.3682   0.04264   0.03736  -0.0811   0.2941   1.0000
   9.500   1.3747   0.04424   0.03898  -0.0802   0.2923   1.0000
   9.750   1.3831   0.04567   0.04044  -0.0795   0.2910   1.0000
  10.000   1.3848   0.04771   0.04250  -0.0784   0.2884   1.0000
  10.250   1.3886   0.04957   0.04437  -0.0775   0.2865   1.0000
  10.500   1.3869   0.05198   0.04680  -0.0763   0.2843   1.0000
  10.750   1.3876   0.05417   0.04901  -0.0753   0.2821   1.0000
  11.000   1.3899   0.05629   0.05116  -0.0745   0.2803   1.0000
  11.250   1.3967   0.05798   0.05288  -0.0740   0.2782   1.0000
  11.500   1.4000   0.06001   0.05494  -0.0733   0.2765   1.0000
  11.750   1.4031   0.06207   0.05702  -0.0727   0.2748   1.0000
  12.000   1.4061   0.06414   0.05912  -0.0720   0.2728   1.0000
  12.250   1.4040   0.06675   0.06176  -0.0712   0.2710   1.0000
  12.500   1.4017   0.06937   0.06438  -0.0704   0.2682   1.0000
  12.750   1.4034   0.07161   0.06666  -0.0698   0.2669   1.0000
  13.000   1.4096   0.07342   0.06850  -0.0695   0.2657   1.0000
  13.250   1.4181   0.07499   0.07010  -0.0693   0.2650   1.0000
  13.500   1.4255   0.07668   0.07182  -0.0691   0.2635   1.0000
  13.750   1.4297   0.07871   0.07387  -0.0688   0.2619   1.0000
  14.000   1.4310   0.08105   0.07624  -0.0684   0.2600   1.0000
  14.250   1.4351   0.08309   0.07829  -0.0681   0.2582   1.0000
  14.500   1.4382   0.08522   0.08044  -0.0678   0.2563   1.0000
  14.750   1.4331   0.08824   0.08348  -0.0672   0.2540   1.0000
  15.000   1.4405   0.08995   0.08522  -0.0672   0.2529   1.0000
  15.250   1.4497   0.09146   0.08676  -0.0672   0.2520   1.0000
  15.500   1.4579   0.09308   0.08841  -0.0672   0.2508   1.0000
  15.750   1.4645   0.09485   0.09021  -0.0672   0.2492   1.0000
  16.000   1.4670   0.09710   0.09249  -0.0671   0.2479   1.0000
  16.250   1.4697   0.09933   0.09474  -0.0670   0.2458   1.0000
  16.500   1.4743   0.10129   0.09672  -0.0670   0.2442   1.0000
  16.750   1.4759   0.10360   0.09904  -0.0670   0.2421   1.0000
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