Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 561 AIRFOIL (goe561-il)
Reynolds number: 1,000,000
Max Cl/Cd: 49.08 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe561-il-1000000.txt
Download as CSV file: xf-goe561-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250   0.5019   0.11567   0.11099  -0.1677   0.5174   0.0224
 -14.000   0.5042   0.11285   0.10818  -0.1690   0.5164   0.0231
 -13.750   0.5066   0.11052   0.10586  -0.1703   0.5152   0.0231
 -13.500   0.5106   0.10824   0.10359  -0.1713   0.5139   0.0232
 -13.250   0.5135   0.10591   0.10127  -0.1724   0.5121   0.0232
 -13.000   0.5179   0.10353   0.09890  -0.1733   0.5107   0.0232
 -12.750   0.5248   0.10121   0.09656  -0.1740   0.5084   0.0232
 -12.500   0.5404   0.09888   0.09423  -0.1739   0.5068   0.0234
 -12.250   0.5495   0.09692   0.09226  -0.1743   0.5048   0.0234
 -12.000   0.5590   0.09511   0.09043  -0.1746   0.5022   0.0235
 -11.750   0.5680   0.09337   0.08868  -0.1750   0.5000   0.0236
 -11.500   0.5775   0.09171   0.08701  -0.1753   0.4979   0.0238
 -11.250   0.5854   0.08991   0.08524  -0.1757   0.4972   0.0240
 -11.000   0.5932   0.08814   0.08349  -0.1761   0.4965   0.0243
 -10.750   0.5992   0.08613   0.08150  -0.1765   0.4952   0.0245
 -10.500   0.6055   0.08425   0.07964  -0.1768   0.4941   0.0246
 -10.250   0.6114   0.08237   0.07777  -0.1771   0.4924   0.0246
 -10.000   0.6164   0.08039   0.07581  -0.1773   0.4914   0.0247
  -9.750   0.6203   0.07839   0.07381  -0.1775   0.4896   0.0257
  -9.500   0.6040   0.07461   0.07007  -0.1793   0.4888   0.0267
  -9.250   0.6014   0.07195   0.06744  -0.1798   0.4876   0.0267
  -9.000   0.6001   0.06962   0.06511  -0.1799   0.4856   0.0268
  -8.750   0.5990   0.06735   0.06285  -0.1799   0.4840   0.0268
  -8.500   0.5971   0.06503   0.06055  -0.1789   0.4826   0.0269
  -8.250   0.5970   0.06326   0.05878  -0.1783   0.4799   0.0270
  -8.000   0.5979   0.06163   0.05718  -0.1775   0.4785   0.0271
  -7.750   0.5969   0.05992   0.05550  -0.1767   0.4779   0.0272
  -7.500   0.5843   0.05738   0.05302  -0.1765   0.4770   0.0271
  -7.250   0.5739   0.05556   0.05125  -0.1757   0.4765   0.0273
  -7.000   0.5537   0.05368   0.04939  -0.1727   0.4755   0.0273
  -6.750   0.5298   0.05229   0.04803  -0.1675   0.4746   0.0274
  -6.500   0.4950   0.05114   0.04692  -0.1595   0.4739   0.0273
  -6.250   0.4753   0.04974   0.04552  -0.1537   0.4728   0.0274
  -6.000   0.4582   0.04834   0.04413  -0.1481   0.4717   0.0275
  -5.750   0.4465   0.04706   0.04284  -0.1431   0.4707   0.0276
  -5.500   0.4352   0.04563   0.04139  -0.1381   0.4694   0.0277
  -5.250   0.4252   0.04431   0.04004  -0.1330   0.4681   0.0278
  -5.000   0.4176   0.04310   0.03880  -0.1280   0.4665   0.0280
  -4.750   0.4102   0.04173   0.03737  -0.1230   0.4647   0.0282
  -4.500   0.4033   0.04030   0.03588  -0.1180   0.4630   0.0283
  -4.250   0.3985   0.03897   0.03448  -0.1131   0.4608   0.0286
  -4.000   0.3571   0.03361   0.02865  -0.1000   0.4600   0.0307
  -3.750   0.3558   0.03234   0.02733  -0.0951   0.4594   0.0307
  -3.500   0.3587   0.03140   0.02638  -0.0912   0.4584   0.0308
  -3.250   0.3633   0.03059   0.02554  -0.0874   0.4573   0.0309
  -3.000   0.3681   0.02997   0.02489  -0.0837   0.4559   0.0311
  -2.750   0.3721   0.02914   0.02400  -0.0795   0.4544   0.0311
  -2.500   0.3787   0.02854   0.02336  -0.0760   0.4530   0.0313
  -2.250   0.3840   0.02796   0.02273  -0.0721   0.4513   0.0315
  -2.000   0.3917   0.02758   0.02231  -0.0687   0.4496   0.0321
  -1.750   0.3954   0.02688   0.02151  -0.0643   0.4479   0.0322
  -1.500   0.3939   0.02590   0.02009  -0.0569   0.4462   0.0344
  -1.250   0.3984   0.02541   0.01946  -0.0525   0.4439   0.0345
  -1.000   0.3974   0.02375   0.01768  -0.0474   0.4418   0.0348
  -0.750   0.4065   0.02314   0.01705  -0.0441   0.4408   0.0350
  -0.500   0.4164   0.02269   0.01657  -0.0409   0.4395   0.0351
  -0.250   0.4271   0.02237   0.01623  -0.0380   0.4379   0.0353
   0.000   0.4388   0.02208   0.01591  -0.0352   0.4360   0.0356
   0.250   0.4505   0.02186   0.01565  -0.0325   0.4339   0.0359
   0.500   0.4602   0.02159   0.01530  -0.0293   0.4318   0.0365
   0.750   0.4710   0.02129   0.01491  -0.0262   0.4296   0.0370
   1.000   0.4770   0.02180   0.01507  -0.0215   0.4266   0.0387
   1.250   0.5056   0.01958   0.01272  -0.0218   0.4243   0.0355
   1.500   0.5244   0.01946   0.01260  -0.0206   0.4226   0.0361
   1.750   0.5331   0.02003   0.01326  -0.0178   0.4208   0.0401
   2.000   0.6208   0.01774   0.01061  -0.0293   0.4176   0.0328
   2.250   0.6489   0.01775   0.01058  -0.0301   0.4149   0.0334
   2.500   0.6772   0.01782   0.01061  -0.0311   0.4120   0.0338
   2.750   0.7002   0.01806   0.01080  -0.0312   0.4082   0.0341
   3.000   0.7273   0.01819   0.01093  -0.0319   0.4063   0.0345
   3.250   0.7679   0.01811   0.01091  -0.0355   0.4035   0.0359
   3.500   0.8029   0.01826   0.01107  -0.0380   0.4004   0.0366
   3.750   0.8313   0.01854   0.01133  -0.0394   0.3968   0.0370
   4.000   0.8495   0.01909   0.01183  -0.0390   0.3924   0.0382
   4.250   0.8748   0.01934   0.01210  -0.0396   0.3902   0.0387
   4.500   0.9012   0.01958   0.01237  -0.0405   0.3868   0.0406
   4.750   0.9214   0.02001   0.01280  -0.0404   0.3833   0.0407
   5.000   0.9360   0.02069   0.01346  -0.0395   0.3793   0.0421
   5.250   0.9511   0.02134   0.01410  -0.0387   0.3756   0.0431
   5.500   0.9730   0.02176   0.01456  -0.0390   0.3729   0.0455
   5.750   0.9898   0.02237   0.01517  -0.0385   0.3695   0.0467
   6.000   1.0048   0.02309   0.01589  -0.0378   0.3660   0.0490
   6.250   1.0125   0.02421   0.01699  -0.0364   0.3614   0.0518
   6.500   1.0311   0.02478   0.01759  -0.0362   0.3588   0.0541
   6.750   1.0475   0.02549   0.01833  -0.0359   0.3562   0.0608
   7.000   1.0604   0.02639   0.01925  -0.0352   0.3527   0.0680
   7.250   1.3670   0.02785   0.02272  -0.0952   0.3434   1.0000
   7.500   1.3793   0.02878   0.02365  -0.0943   0.3408   1.0000
   7.750   1.3865   0.03007   0.02493  -0.0930   0.3378   1.0000
   8.000   1.3930   0.03140   0.02626  -0.0916   0.3350   1.0000
   8.250   1.3919   0.03331   0.02815  -0.0896   0.3311   1.0000
   8.500   1.4047   0.03428   0.02914  -0.0889   0.3289   1.0000
   8.750   1.4149   0.03546   0.03034  -0.0881   0.3270   1.0000
   9.000   1.4224   0.03683   0.03172  -0.0871   0.3247   1.0000
   9.250   1.4263   0.03847   0.03336  -0.0858   0.3215   1.0000
   9.500   1.4252   0.04055   0.03544  -0.0842   0.3186   1.0000
   9.750   1.4291   0.04225   0.03714  -0.0830   0.3157   1.0000
  10.000   1.4370   0.04371   0.03863  -0.0822   0.3144   1.0000
  10.250   1.4468   0.04503   0.03998  -0.0817   0.3127   1.0000
  10.500   1.4539   0.04654   0.04151  -0.0809   0.3107   1.0000
  10.750   1.4569   0.04845   0.04345  -0.0799   0.3086   1.0000
  11.000   1.4601   0.05032   0.04532  -0.0790   0.3065   1.0000
  11.250   1.4542   0.05303   0.04802  -0.0776   0.3028   1.0000
  11.500   1.4622   0.05450   0.04951  -0.0770   0.3014   1.0000
  11.750   1.4686   0.05623   0.05129  -0.0765   0.3001   1.0000
  12.000   1.4738   0.05806   0.05316  -0.0759   0.2981   1.0000
  12.250   1.4812   0.05966   0.05479  -0.0755   0.2967   1.0000
  12.500   1.4831   0.06179   0.05695  -0.0748   0.2948   1.0000
  12.750   1.4845   0.06398   0.05914  -0.0741   0.2925   1.0000
  13.000   1.4835   0.06637   0.06153  -0.0733   0.2897   1.0000
  13.250   1.4881   0.06820   0.06335  -0.0728   0.2874   1.0000
  13.500   1.4963   0.06978   0.06498  -0.0726   0.2868   1.0000
  13.750   1.5018   0.07163   0.06688  -0.0723   0.2852   1.0000
  14.000   1.5048   0.07373   0.06902  -0.0719   0.2837   1.0000
  14.250   1.5103   0.07559   0.07092  -0.0716   0.2823   1.0000
  14.500   1.5152   0.07749   0.07283  -0.0714   0.2804   1.0000
  14.750   1.5200   0.07938   0.07473  -0.0711   0.2788   1.0000
  15.000   1.5203   0.08173   0.07709  -0.0707   0.2767   1.0000
  15.250   1.5304   0.08297   0.07830  -0.0706   0.2743   1.0000
  15.500   1.5366   0.08475   0.08013  -0.0705   0.2733   1.0000
  15.750   1.5434   0.08649   0.08191  -0.0705   0.2724   1.0000
  16.000   1.5488   0.08836   0.08383  -0.0704   0.2712   1.0000
  16.250   1.5486   0.09084   0.08637  -0.0702   0.2695   1.0000
  16.500   1.5541   0.09271   0.08826  -0.0701   0.2680   1.0000
  16.750   1.5597   0.09454   0.09011  -0.0701   0.2663   1.0000
  17.000   1.5661   0.09625   0.09183  -0.0702   0.2649   1.0000
  17.250   1.5704   0.09816   0.09374  -0.0702   0.2628   1.0000
  17.500   1.5847   0.09890   0.09446  -0.0704   0.2609   1.0000
  17.750   1.5811   0.10181   0.09745  -0.0703   0.2595   1.0000
  18.000   1.5898   0.10325   0.09893  -0.0705   0.2590   1.0000
  18.250   1.5910   0.10558   0.10132  -0.0706   0.2572   1.0000
  18.500   1.5888   0.10830   0.10410  -0.0706   0.2554   1.0000
<< Back to GOE 561 AIRFOIL (goe561-il)

Polar data table (+)

Polar graphs


<< Back to GOE 561 AIRFOIL (goe561-il)