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GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 650 AIRFOIL (goe650-il)
Reynolds number: 100,000
Max Cl/Cd: 53.93 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe650-il-100000-n5.txt
Download as CSV file: xf-goe650-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 650 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3979   0.10384   0.09818  -0.0494   1.0000   0.0586
 -11.000  -0.4107   0.09909   0.09347  -0.0501   1.0000   0.0592
 -10.500  -0.7134   0.05498   0.04944  -0.0660   0.9999   0.0583
 -10.250  -0.7175   0.04383   0.03773  -0.0833   0.9881   0.0592
 -10.000  -0.6997   0.03972   0.03322  -0.0889   0.9817   0.0607
  -9.750  -0.6828   0.03653   0.02962  -0.0919   0.9748   0.0626
  -9.500  -0.6552   0.03512   0.02816  -0.0942   0.9709   0.0645
  -9.250  -0.6342   0.03378   0.02671  -0.0950   0.9646   0.0667
  -9.000  -0.6082   0.03199   0.02464  -0.0969   0.9598   0.0699
  -8.750  -0.5823   0.03068   0.02321  -0.0982   0.9551   0.0726
  -8.500  -0.5584   0.02969   0.02213  -0.0986   0.9491   0.0757
  -8.250  -0.5297   0.02843   0.02064  -0.1001   0.9452   0.0809
  -8.000  -0.5018   0.02777   0.01995  -0.1010   0.9411   0.0860
  -7.750  -0.4796   0.02695   0.01898  -0.1008   0.9349   0.0920
  -7.500  -0.4496   0.02636   0.01828  -0.1018   0.9309   0.0992
  -7.250  -0.4164   0.02579   0.01761  -0.1034   0.9279   0.1063
  -7.000  -0.3954   0.02532   0.01693  -0.1026   0.9212   0.1134
  -6.750  -0.3676   0.02502   0.01662  -0.1029   0.9167   0.1196
  -6.500  -0.3358   0.02456   0.01590  -0.1040   0.9136   0.1275
  -6.250  -0.3018   0.02425   0.01561  -0.1055   0.9112   0.1339
  -6.000  -0.2834   0.02404   0.01523  -0.1039   0.9036   0.1409
  -5.750  -0.2544   0.02386   0.01505  -0.1044   0.8994   0.1485
  -5.500  -0.2214   0.02360   0.01456  -0.1056   0.8965   0.1583
  -5.250  -0.1869   0.02322   0.01426  -0.1069   0.8943   0.1647
  -5.000  -0.1696   0.02298   0.01393  -0.1050   0.8859   0.1693
  -4.750  -0.1368   0.02247   0.01326  -0.1059   0.8815   0.1752
  -4.500  -0.0992   0.02194   0.01275  -0.1076   0.8784   0.1808
  -4.250  -0.0745   0.02162   0.01236  -0.1069   0.8712   0.1864
  -4.000  -0.0454   0.02126   0.01193  -0.1070   0.8658   0.1925
  -3.750  -0.0112   0.02090   0.01158  -0.1081   0.8625   0.1993
  -3.500   0.0258   0.02052   0.01109  -0.1097   0.8600   0.2075
  -3.250   0.0425   0.02043   0.01108  -0.1076   0.8519   0.2131
  -3.000   0.0734   0.02018   0.01079  -0.1080   0.8474   0.2227
  -2.750   0.1079   0.01987   0.01052  -0.1091   0.8442   0.2323
  -2.500   0.1383   0.01965   0.01028  -0.1094   0.8399   0.2434
  -2.250   0.1590   0.01961   0.01029  -0.1080   0.8322   0.2538
  -2.000   0.1918   0.01937   0.01009  -0.1087   0.8283   0.2676
  -1.750   0.2281   0.01909   0.00985  -0.1100   0.8253   0.2837
  -1.500   0.2461   0.01916   0.00995  -0.1080   0.8167   0.2976
  -1.250   0.2775   0.01900   0.00982  -0.1084   0.8118   0.3153
  -1.000   0.3136   0.01877   0.00964  -0.1096   0.8084   0.3343
  -0.750   0.3337   0.01886   0.00976  -0.1080   0.8000   0.3503
  -0.500   0.3650   0.01873   0.00967  -0.1083   0.7945   0.3688
  -0.250   0.4033   0.01845   0.00941  -0.1098   0.7904   0.3882
   0.000   0.4234   0.01847   0.00947  -0.1080   0.7795   0.4042
   0.250   0.4647   0.01800   0.00901  -0.1098   0.7726   0.4237
   0.500   0.4861   0.01793   0.00896  -0.1081   0.7597   0.4395
   0.750   0.5152   0.01774   0.00881  -0.1078   0.7497   0.4564
   1.000   0.5449   0.01759   0.00869  -0.1076   0.7406   0.4742
   1.250   0.5710   0.01754   0.00869  -0.1069   0.7303   0.4922
   1.500   0.6038   0.01736   0.00854  -0.1073   0.7211   0.5131
   1.750   0.6270   0.01735   0.00861  -0.1061   0.7090   0.5328
   2.000   0.6564   0.01721   0.00854  -0.1059   0.6982   0.5549
   2.250   0.6837   0.01711   0.00850  -0.1053   0.6860   0.5783
   2.500   0.7069   0.01708   0.00857  -0.1041   0.6719   0.6032
   2.750   0.7317   0.01699   0.00859  -0.1032   0.6578   0.6336
   3.250   0.7820   0.01654   0.00858  -0.1012   0.6266   0.7549
   3.500   0.8254   0.01636   0.00854  -0.1040   0.6061   1.0000
   3.750   0.8499   0.01648   0.00854  -0.1030   0.5867   1.0000
   4.000   0.8747   0.01662   0.00852  -0.1021   0.5665   1.0000
   4.250   0.8980   0.01684   0.00858  -0.1009   0.5452   1.0000
   4.500   0.9203   0.01712   0.00872  -0.0996   0.5239   1.0000
   4.750   0.9415   0.01746   0.00891  -0.0981   0.5021   1.0000
   5.000   0.9616   0.01783   0.00915  -0.0965   0.4803   1.0000
   5.250   0.9804   0.01824   0.00944  -0.0947   0.4581   1.0000
   5.500   0.9977   0.01867   0.00977  -0.0927   0.4348   1.0000
   5.750   1.0144   0.01913   0.01011  -0.0906   0.4121   1.0000
   6.000   1.0301   0.01962   0.01047  -0.0884   0.3910   1.0000
   6.250   1.0450   0.02014   0.01085  -0.0860   0.3719   1.0000
   6.500   1.0599   0.02069   0.01128  -0.0837   0.3547   1.0000
   7.000   1.0910   0.02185   0.01228  -0.0796   0.3258   1.0000
   7.250   1.1071   0.02245   0.01283  -0.0777   0.3133   1.0000
   7.500   1.1231   0.02308   0.01339  -0.0758   0.3022   1.0000
   7.750   1.1390   0.02372   0.01400  -0.0739   0.2913   1.0000
   8.000   1.1553   0.02435   0.01463  -0.0722   0.2812   1.0000
   8.250   1.1706   0.02504   0.01527  -0.0703   0.2720   1.0000
   8.500   1.1870   0.02568   0.01596  -0.0687   0.2629   1.0000
   8.750   1.2018   0.02641   0.01666  -0.0668   0.2548   1.0000
   9.000   1.2177   0.02710   0.01740  -0.0652   0.2464   1.0000
   9.250   1.2321   0.02787   0.01815  -0.0634   0.2389   1.0000
   9.500   1.2473   0.02862   0.01896  -0.0618   0.2315   1.0000
   9.750   1.2614   0.02942   0.01980  -0.0600   0.2244   1.0000
  10.000   1.2757   0.03027   0.02064  -0.0584   0.2183   1.0000
  10.250   1.2897   0.03111   0.02157  -0.0568   0.2114   1.0000
  10.500   1.3019   0.03203   0.02247  -0.0550   0.2054   1.0000
  10.750   1.3146   0.03296   0.02350  -0.0534   0.1988   1.0000
  11.000   1.3254   0.03394   0.02454  -0.0516   0.1925   1.0000
  11.250   1.3355   0.03501   0.02561  -0.0498   0.1866   1.0000
  11.500   1.3458   0.03608   0.02681  -0.0482   0.1802   1.0000
  11.750   1.3546   0.03724   0.02799  -0.0465   0.1751   1.0000
  12.000   1.3647   0.03843   0.02928  -0.0450   0.1701   1.0000
  12.250   1.3739   0.03968   0.03065  -0.0435   0.1650   1.0000
  12.500   1.3817   0.04101   0.03203  -0.0419   0.1608   1.0000
  12.750   1.3894   0.04242   0.03351  -0.0405   0.1564   1.0000
  13.000   1.3956   0.04395   0.03520  -0.0391   0.1511   1.0000
  13.250   1.3998   0.04560   0.03692  -0.0377   0.1466   1.0000
  13.500   1.4041   0.04735   0.03876  -0.0365   0.1422   1.0000
  13.750   1.4077   0.04924   0.04082  -0.0354   0.1372   1.0000
  14.000   1.4089   0.05131   0.04297  -0.0343   0.1328   1.0000
  14.250   1.4105   0.05349   0.04525  -0.0334   0.1286   1.0000
  14.500   1.4116   0.05585   0.04779  -0.0327   0.1240   1.0000
  14.750   1.4100   0.05847   0.05052  -0.0321   0.1198   1.0000
  15.000   1.4078   0.06130   0.05346  -0.0317   0.1156   1.0000
  15.250   1.4049   0.06441   0.05676  -0.0315   0.1107   1.0000
  15.500   1.3990   0.06790   0.06033  -0.0317   0.1065   1.0000
  15.750   1.3932   0.07162   0.06421  -0.0320   0.1021   1.0000
  16.000   1.3850   0.07583   0.06858  -0.0328   0.0973   1.0000
  16.250   1.3741   0.08050   0.07331  -0.0339   0.0935   1.0000
  16.500   1.3637   0.08549   0.07852  -0.0353   0.0886   1.0000
  16.750   1.3497   0.09109   0.08424  -0.0372   0.0845   1.0000
  17.000   1.3351   0.09702   0.09030  -0.0395   0.0807   1.0000
  17.250   1.3188   0.10347   0.09691  -0.0422   0.0767   1.0000
  17.500   1.3020   0.11011   0.10362  -0.0452   0.0737   1.0000
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