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GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 648 AIRFOIL (goe648-il)
Reynolds number: 100,000
Max Cl/Cd: 43.21 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe648-il-100000.txt
Download as CSV file: xf-goe648-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 648 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3364   0.09897   0.09439  -0.0272   1.0000   0.1685
  -8.500  -0.4115   0.09866   0.09430  -0.0271   1.0000   0.1720
  -8.250  -0.4711   0.09749   0.09329  -0.0256   1.0000   0.1723
  -8.000  -0.3799   0.09303   0.08872  -0.0210   1.0000   0.1777
  -7.750  -0.3893   0.09157   0.08732  -0.0183   1.0000   0.1816
  -7.500  -0.4221   0.09021   0.08607  -0.0160   1.0000   0.1854
  -7.250  -0.6084   0.05180   0.04599  -0.0391   0.9943   0.1000
  -7.000  -0.5864   0.04690   0.04044  -0.0421   0.9864   0.1005
  -6.750  -0.5521   0.04409   0.03772  -0.0451   0.9805   0.1029
  -6.500  -0.5252   0.04121   0.03453  -0.0467   0.9720   0.1044
  -6.250  -0.4944   0.03894   0.03190  -0.0486   0.9644   0.1077
  -6.000  -0.4641   0.03644   0.02883  -0.0501   0.9562   0.1107
  -5.750  -0.4353   0.03436   0.02625  -0.0510   0.9479   0.1138
  -5.500  -0.3986   0.03320   0.02515  -0.0532   0.9406   0.1189
  -5.250  -0.3684   0.03198   0.02360  -0.0538   0.9318   0.1237
  -5.000  -0.3312   0.03066   0.02213  -0.0557   0.9246   0.1298
  -4.750  -0.3001   0.02990   0.02126  -0.0564   0.9153   0.1370
  -4.500  -0.2583   0.02875   0.02005  -0.0588   0.9076   0.1457
  -4.250  -0.2256   0.02807   0.01919  -0.0594   0.8964   0.1555
  -4.000  -0.1751   0.02688   0.01808  -0.0630   0.8893   0.1694
  -3.750  -0.1442   0.02606   0.01735  -0.0632   0.8768   0.1814
  -3.500  -0.0885   0.02485   0.01619  -0.0673   0.8711   0.2027
  -3.250  -0.0615   0.02418   0.01562  -0.0667   0.8581   0.2209
  -3.000  -0.0101   0.02296   0.01460  -0.0701   0.8537   0.2602
  -2.750   0.0107   0.02226   0.01425  -0.0686   0.8415   0.3049
  -2.500   0.0550   0.02093   0.01350  -0.0708   0.8367   0.4063
  -2.250   0.0767   0.02047   0.01341  -0.0689   0.8249   0.4877
  -2.000   0.1188   0.01969   0.01293  -0.0701   0.8190   0.5812
  -1.750   0.1421   0.01939   0.01284  -0.0681   0.8072   0.6436
  -1.500   0.1837   0.01876   0.01236  -0.0687   0.8006   0.7123
  -1.250   0.2077   0.01854   0.01225  -0.0665   0.7879   0.7657
  -1.000   0.2544   0.01791   0.01168  -0.0676   0.7809   0.8299
  -0.750   0.2931   0.01772   0.01154  -0.0678   0.7671   0.8833
  -0.500   0.3639   0.01747   0.01117  -0.0741   0.7540   0.9225
  -0.250   0.4401   0.01720   0.01069  -0.0818   0.7382   0.9495
   0.000   0.5145   0.01691   0.01019  -0.0898   0.7177   0.9704
   0.250   0.5846   0.01657   0.00961  -0.0975   0.6944   0.9912
   0.500   0.6246   0.01628   0.00907  -0.1001   0.6715   1.0000
   0.750   0.6317   0.01620   0.00885  -0.0968   0.6488   1.0000
   1.000   0.6420   0.01621   0.00867  -0.0937   0.6257   1.0000
   1.250   0.6561   0.01631   0.00852  -0.0911   0.6030   1.0000
   1.500   0.6723   0.01653   0.00848  -0.0889   0.5808   1.0000
   1.750   0.6872   0.01682   0.00858  -0.0865   0.5587   1.0000
   2.000   0.7048   0.01714   0.00870  -0.0845   0.5389   1.0000
   2.250   0.7239   0.01749   0.00885  -0.0827   0.5217   1.0000
   2.500   0.7447   0.01786   0.00901  -0.0813   0.5069   1.0000
   2.750   0.7657   0.01823   0.00922  -0.0800   0.4933   1.0000
   3.000   0.7850   0.01864   0.00954  -0.0783   0.4805   1.0000
   3.250   0.8071   0.01906   0.00981  -0.0772   0.4697   1.0000
   3.500   0.8292   0.01946   0.01010  -0.0761   0.4593   1.0000
   3.750   0.8503   0.01992   0.01049  -0.0748   0.4497   1.0000
   4.000   0.8742   0.02034   0.01079  -0.0740   0.4408   1.0000
   4.250   0.8950   0.02084   0.01126  -0.0728   0.4323   1.0000
   4.500   0.9187   0.02129   0.01161  -0.0720   0.4242   1.0000
   4.750   0.9412   0.02184   0.01212  -0.0711   0.4167   1.0000
   5.000   0.9628   0.02234   0.01260  -0.0700   0.4091   1.0000
   5.250   0.9899   0.02291   0.01301  -0.0699   0.4025   1.0000
   5.500   1.0073   0.02348   0.01370  -0.0681   0.3951   1.0000
   5.750   1.0330   0.02402   0.01413  -0.0677   0.3885   1.0000
   6.000   1.0546   0.02472   0.01484  -0.0668   0.3822   1.0000
   6.250   1.0739   0.02535   0.01553  -0.0654   0.3755   1.0000
   6.500   1.1030   0.02598   0.01600  -0.0657   0.3694   1.0000
   6.750   1.1187   0.02676   0.01693  -0.0638   0.3632   1.0000
   7.000   1.1386   0.02747   0.01769  -0.0626   0.3571   1.0000
   7.250   1.1688   0.02822   0.01828  -0.0631   0.3515   1.0000
   7.500   1.1813   0.02913   0.01939  -0.0608   0.3457   1.0000
   7.750   1.1992   0.02991   0.02024  -0.0593   0.3397   1.0000
   8.000   1.2286   0.03068   0.02089  -0.0598   0.3343   1.0000
   8.250   1.2403   0.03178   0.02218  -0.0575   0.3292   1.0000
   8.500   1.2538   0.03278   0.02332  -0.0555   0.3238   1.0000
   8.750   1.2773   0.03357   0.02410  -0.0550   0.3187   1.0000
   9.000   1.2990   0.03473   0.02526  -0.0544   0.3139   1.0000
   9.250   1.3019   0.03597   0.02677  -0.0509   0.3088   1.0000
   9.500   1.3174   0.03699   0.02787  -0.0494   0.3040   1.0000
   9.750   1.3442   0.03790   0.02874  -0.0495   0.2998   1.0000
  10.000   1.3540   0.03949   0.03047  -0.0474   0.2960   1.0000
  10.250   1.3462   0.04122   0.03250  -0.0428   0.2919   1.0000
  10.500   1.3534   0.04254   0.03394  -0.0404   0.2876   1.0000
  10.750   1.3787   0.04335   0.03474  -0.0403   0.2835   1.0000
  11.000   1.3987   0.04475   0.03614  -0.0398   0.2797   1.0000
  11.250   1.3659   0.04733   0.03907  -0.0326   0.2769   1.0000
  11.500   1.3286   0.05021   0.04221  -0.0255   0.2742   1.0000
  11.750   1.2874   0.05402   0.04624  -0.0198   0.2716   1.0000
  12.000   1.2458   0.05869   0.05109  -0.0158   0.2690   1.0000
  12.250   1.1790   0.06679   0.05936  -0.0134   0.2664   1.0000
  12.500   1.1317   0.07525   0.06792  -0.0136   0.2633   1.0000
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