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GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 562 AIRFOIL (goe562-il)
Reynolds number: 100,000
Max Cl/Cd: 49.98 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe562-il-100000-n5.txt
Download as CSV file: xf-goe562-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 562 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1635   0.11114   0.10681  -0.0528   0.9443   0.0473
  -9.500  -0.1586   0.10795   0.10362  -0.0599   0.9199   0.0495
  -9.250  -0.1472   0.10384   0.09948  -0.0692   0.9031   0.0500
  -9.000  -0.1173   0.09738   0.09296  -0.0714   0.8911   0.0513
  -8.750  -0.0831   0.09239   0.08786  -0.0765   0.8763   0.0535
  -8.500  -0.0509   0.08741   0.08272  -0.0848   0.8585   0.0562
  -8.250  -0.0225   0.08239   0.07755  -0.0954   0.8383   0.0595
  -8.000  -0.0233   0.07852   0.07354  -0.1076   0.8107   0.0615
  -7.500   0.0220   0.07045   0.06523  -0.1110   0.7743   0.0658
  -7.250   0.0319   0.06756   0.06222  -0.1130   0.7574   0.0680
  -7.000   0.0390   0.06452   0.05906  -0.1153   0.7424   0.0701
  -6.750   0.0317   0.06195   0.05616  -0.1194   0.7296   0.0752
  -6.500   0.0330   0.05953   0.05341  -0.1194   0.7180   0.0756
  -6.250   0.0525   0.05504   0.04910  -0.1192   0.7078   0.0778
  -5.500   0.0719   0.04271   0.03547  -0.1151   0.6834   0.0501
  -5.250   0.0833   0.04007   0.03270  -0.1137   0.6755   0.0510
  -5.000   0.1017   0.03905   0.03172  -0.1132   0.6673   0.0538
  -4.750   0.1148   0.03693   0.02929  -0.1113   0.6602   0.0540
  -4.500   0.1270   0.03451   0.02644  -0.1088   0.6533   0.0529
  -4.250   0.1429   0.03241   0.02384  -0.1066   0.6475   0.0521
  -4.000   0.1587   0.03090   0.02205  -0.1045   0.6405   0.0524
  -3.750   0.1785   0.02981   0.02073  -0.1032   0.6344   0.0541
  -3.500   0.1980   0.02867   0.01930  -0.1017   0.6283   0.0553
  -3.250   0.2177   0.02749   0.01781  -0.1000   0.6220   0.0556
  -3.000   0.2409   0.02638   0.01633  -0.0989   0.6167   0.0557
  -2.750   0.2626   0.02545   0.01514  -0.0975   0.6107   0.0561
  -2.500   0.2863   0.02463   0.01408  -0.0965   0.6051   0.0565
  -2.250   0.3126   0.02399   0.01317  -0.0961   0.6002   0.0584
  -2.000   0.3359   0.02348   0.01249  -0.0950   0.5943   0.0600
  -1.750   0.3611   0.02296   0.01179  -0.0943   0.5888   0.0609
  -1.500   0.3890   0.02245   0.01109  -0.0942   0.5842   0.0616
  -1.250   0.4132   0.02194   0.01055  -0.0935   0.5790   0.0624
  -1.000   0.4372   0.02144   0.01006  -0.0928   0.5739   0.0636
  -0.750   0.4621   0.02106   0.00964  -0.0922   0.5695   0.0654
  -0.500   0.4854   0.02084   0.00939  -0.0913   0.5649   0.0690
  -0.250   0.5068   0.02071   0.00923  -0.0900   0.5596   0.0727
   0.000   0.5313   0.02059   0.00900  -0.0893   0.5551   0.0753
   0.250   0.5591   0.02041   0.00871  -0.0893   0.5516   0.0795
   0.500   0.5827   0.02040   0.00870  -0.0886   0.5465   0.0853
   0.750   0.6111   0.02033   0.00866  -0.0888   0.5416   0.1025
   1.000   0.7993   0.01867   0.00887  -0.1239   0.5320   1.0000
   1.250   0.8190   0.01888   0.00899  -0.1223   0.5263   1.0000
   1.500   0.8414   0.01901   0.00894  -0.1212   0.5210   1.0000
   1.750   0.8596   0.01922   0.00910  -0.1194   0.5147   1.0000
   2.000   0.8792   0.01938   0.00916  -0.1178   0.5082   1.0000
   2.250   0.9004   0.01952   0.00917  -0.1165   0.5026   1.0000
   2.500   0.9178   0.01976   0.00940  -0.1146   0.4962   1.0000
   2.750   0.9388   0.01995   0.00951  -0.1133   0.4913   1.0000
   3.000   0.9602   0.02017   0.00964  -0.1121   0.4871   1.0000
   3.250   0.9778   0.02046   0.00997  -0.1103   0.4819   1.0000
   3.500   0.9976   0.02069   0.01015  -0.1088   0.4769   1.0000
   3.750   1.0201   0.02088   0.01025  -0.1079   0.4730   1.0000
   4.000   1.0361   0.02122   0.01065  -0.1058   0.4676   1.0000
   4.250   1.0544   0.02148   0.01092  -0.1041   0.4623   1.0000
   4.500   1.0756   0.02169   0.01106  -0.1029   0.4581   1.0000
   4.750   1.0916   0.02203   0.01145  -0.1009   0.4528   1.0000
   5.000   1.1085   0.02234   0.01180  -0.0990   0.4475   1.0000
   5.250   1.1284   0.02258   0.01200  -0.0976   0.4431   1.0000
   5.500   1.1443   0.02293   0.01240  -0.0955   0.4381   1.0000
   5.750   1.1592   0.02330   0.01282  -0.0933   0.4326   1.0000
   6.000   1.1775   0.02356   0.01309  -0.0917   0.4279   1.0000
   6.250   1.1921   0.02395   0.01352  -0.0895   0.4226   1.0000
   6.500   1.2052   0.02437   0.01402  -0.0870   0.4170   1.0000
   6.750   1.2221   0.02467   0.01432  -0.0852   0.4122   1.0000
   7.000   1.2334   0.02512   0.01484  -0.0824   0.4066   1.0000
   7.250   1.2428   0.02554   0.01534  -0.0793   0.4009   1.0000
   7.500   1.2577   0.02583   0.01562  -0.0771   0.3961   1.0000
   7.750   1.2636   0.02639   0.01629  -0.0735   0.3901   1.0000
   8.000   1.2727   0.02687   0.01685  -0.0706   0.3844   1.0000
   8.250   1.2871   0.02724   0.01720  -0.0685   0.3796   1.0000
   8.500   1.2904   0.02799   0.01809  -0.0648   0.3731   1.0000
   8.750   1.3008   0.02852   0.01867  -0.0623   0.3678   1.0000
   9.000   1.3106   0.02916   0.01938  -0.0599   0.3626   1.0000
   9.250   1.3152   0.03002   0.02036  -0.0568   0.3565   1.0000
   9.500   1.3274   0.03062   0.02098  -0.0549   0.3520   1.0000
   9.750   1.3334   0.03157   0.02204  -0.0523   0.3470   1.0000
  10.000   1.3385   0.03262   0.02321  -0.0498   0.3420   1.0000
  10.250   1.3498   0.03340   0.02404  -0.0481   0.3380   1.0000
  10.500   1.3567   0.03446   0.02520  -0.0460   0.3335   1.0000
  10.750   1.3564   0.03595   0.02683  -0.0434   0.3282   1.0000
  11.000   1.3649   0.03672   0.02758  -0.0416   0.3217   1.0000
  11.250   1.3557   0.03898   0.03001  -0.0389   0.3155   1.0000
  11.500   1.3575   0.04036   0.03138  -0.0371   0.3081   1.0000
  11.750   1.3504   0.04281   0.03398  -0.0351   0.3022   1.0000
  12.000   1.3476   0.04492   0.03616  -0.0336   0.2958   1.0000
  12.250   1.3448   0.04716   0.03849  -0.0322   0.2896   1.0000
  12.500   1.3363   0.05014   0.04161  -0.0310   0.2837   1.0000
  12.750   1.3397   0.05186   0.04332  -0.0300   0.2771   1.0000
  13.000   1.3257   0.05575   0.04739  -0.0292   0.2717   1.0000
  13.250   1.3219   0.05842   0.05012  -0.0284   0.2651   1.0000
  13.500   1.3112   0.06210   0.05390  -0.0279   0.2585   1.0000
  13.750   1.2998   0.06603   0.05795  -0.0276   0.2525   1.0000
  14.000   1.3030   0.06804   0.05998  -0.0270   0.2462   1.0000
  14.250   1.2856   0.07308   0.06523  -0.0272   0.2419   1.0000
  14.500   1.2739   0.07736   0.06962  -0.0273   0.2353   1.0000
  14.750   1.2660   0.08116   0.07350  -0.0273   0.2281   1.0000
  15.000   1.2467   0.08688   0.07939  -0.0280   0.2225   1.0000
  15.250   1.2354   0.09136   0.08393  -0.0285   0.2123   1.0000
  15.500   1.2174   0.09721   0.08997  -0.0294   0.2086   1.0000
  15.750   1.2025   0.10255   0.09543  -0.0304   0.1987   1.0000
  16.000   1.1771   0.10991   0.10301  -0.0320   0.1962   1.0000
  16.250   1.1482   0.11808   0.11134  -0.0340   0.1935   1.0000
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