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GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 584 AIRFOIL (goe584-il)
Reynolds number: 200,000
Max Cl/Cd: 78.07 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe584-il-200000.txt
Download as CSV file: xf-goe584-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 584 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2722   0.11160   0.10789  -0.0431   1.0000   0.0635
 -10.500  -0.2827   0.10884   0.10519  -0.0457   1.0000   0.0669
 -10.250  -0.3125   0.10600   0.10247  -0.0508   1.0000   0.0677
 -10.000  -0.2980   0.10201   0.09851  -0.0476   1.0000   0.0686
  -9.750  -0.2899   0.10023   0.09678  -0.0447   1.0000   0.0695
  -9.500  -0.3023   0.09976   0.09643  -0.0407   0.9993   0.0700
  -9.250  -0.2779   0.09599   0.09264  -0.0449   0.9943   0.0724
  -9.000  -0.2802   0.08901   0.08566  -0.0635   0.9796   0.0780
  -8.750  -0.2613   0.08372   0.08037  -0.0652   0.9741   0.0794
  -8.500  -0.2294   0.08142   0.07804  -0.0649   0.9710   0.0812
  -8.250  -0.2065   0.07804   0.07463  -0.0689   0.9629   0.0843
  -8.000  -0.2113   0.06637   0.06283  -0.0947   0.9424   0.0911
  -7.750  -0.1777   0.06518   0.06168  -0.0919   0.9395   0.0926
  -7.500  -0.1538   0.06336   0.05983  -0.0922   0.9288   0.0955
  -7.250  -0.1634   0.05467   0.05075  -0.1061   0.9082   0.1046
  -7.000  -0.1420   0.05300   0.04912  -0.1047   0.8983   0.1059
  -6.750  -0.1206   0.05146   0.04755  -0.1042   0.8897   0.1083
  -6.250  -0.1063   0.04521   0.04090  -0.1060   0.8648   0.1208
  -6.000  -0.0870   0.04373   0.03938  -0.1052   0.8565   0.1236
  -5.750  -0.0807   0.04065   0.03586  -0.1058   0.8452   0.1348
  -5.500  -0.0815   0.02859   0.02221  -0.1045   0.8375   0.0898
  -5.250  -0.0632   0.02642   0.01979  -0.1033   0.8281   0.0893
  -5.000  -0.0401   0.02497   0.01797  -0.1025   0.8214   0.0898
  -4.750  -0.0188   0.02352   0.01628  -0.1014   0.8128   0.0898
  -4.500   0.0057   0.02231   0.01478  -0.1007   0.8060   0.0900
  -4.250   0.0289   0.02092   0.01316  -0.0999   0.7986   0.0910
  -4.000   0.0536   0.01975   0.01188  -0.0994   0.7912   0.0924
  -3.750   0.0804   0.01897   0.01096  -0.0990   0.7855   0.0935
  -3.500   0.1050   0.01834   0.01027  -0.0983   0.7774   0.0945
  -3.250   0.1322   0.01776   0.00957  -0.0979   0.7713   0.0960
  -3.000   0.1580   0.01734   0.00908  -0.0973   0.7644   0.0981
  -2.750   0.1843   0.01692   0.00858  -0.0968   0.7576   0.1003
  -2.500   0.2123   0.01651   0.00805  -0.0965   0.7524   0.1021
  -2.250   0.2372   0.01619   0.00771  -0.0957   0.7448   0.1037
  -2.000   0.2632   0.01558   0.00713  -0.0952   0.7387   0.1066
  -1.750   0.2898   0.01530   0.00685  -0.0948   0.7332   0.1106
  -1.500   0.3146   0.01510   0.00667  -0.0941   0.7259   0.1152
  -1.250   0.3412   0.01477   0.00633  -0.0936   0.7203   0.1207
  -1.000   0.3664   0.01457   0.00618  -0.0929   0.7141   0.1287
  -0.750   0.3914   0.01432   0.00601  -0.0922   0.7073   0.1435
  -0.500   0.4169   0.01382   0.00579  -0.0916   0.7022   0.2171
  -0.250   0.4356   0.01312   0.00584  -0.0902   0.6951   0.4078
   0.000   0.5112   0.01167   0.00588  -0.0988   0.6886   0.9635
   0.250   0.5740   0.01168   0.00570  -0.1058   0.6823   1.0000
   0.500   0.5961   0.01178   0.00573  -0.1046   0.6750   1.0000
   0.750   0.6212   0.01186   0.00565  -0.1039   0.6694   1.0000
   1.000   0.6435   0.01200   0.00575  -0.1028   0.6624   1.0000
   1.250   0.6674   0.01209   0.00576  -0.1019   0.6559   1.0000
   1.500   0.6930   0.01220   0.00574  -0.1012   0.6503   1.0000
   1.750   0.7148   0.01235   0.00589  -0.1000   0.6428   1.0000
   2.000   0.7402   0.01244   0.00588  -0.0993   0.6368   1.0000
   2.250   0.7634   0.01260   0.00601  -0.0983   0.6300   1.0000
   2.500   0.7873   0.01272   0.00608  -0.0974   0.6229   1.0000
   2.750   0.8132   0.01284   0.00611  -0.0968   0.6170   1.0000
   3.000   0.8351   0.01300   0.00629  -0.0956   0.6090   1.0000
   3.250   0.8612   0.01310   0.00630  -0.0951   0.6027   1.0000
   3.500   0.8833   0.01328   0.00650  -0.0939   0.5949   1.0000
   3.750   0.9082   0.01338   0.00655  -0.0932   0.5877   1.0000
   4.000   0.9314   0.01355   0.00672  -0.0922   0.5801   1.0000
   4.250   0.9555   0.01367   0.00681  -0.0913   0.5722   1.0000
   4.500   0.9791   0.01383   0.00695  -0.0904   0.5643   1.0000
   4.750   1.0026   0.01395   0.00707  -0.0894   0.5558   1.0000
   5.000   1.0258   0.01411   0.00723  -0.0884   0.5472   1.0000
   5.250   1.0494   0.01421   0.00729  -0.0875   0.5378   1.0000
   5.500   1.0704   0.01432   0.00742  -0.0860   0.5263   1.0000
   5.750   1.0925   0.01442   0.00749  -0.0848   0.5148   1.0000
   6.000   1.1150   0.01453   0.00755  -0.0836   0.5037   1.0000
   6.250   1.1351   0.01471   0.00779  -0.0821   0.4921   1.0000
   6.500   1.1564   0.01490   0.00798  -0.0809   0.4809   1.0000
   6.750   1.1782   0.01511   0.00813  -0.0797   0.4700   1.0000
   7.000   1.1976   0.01534   0.00840  -0.0781   0.4576   1.0000
   7.250   1.2170   0.01559   0.00869  -0.0766   0.4451   1.0000
   7.500   1.2361   0.01587   0.00896  -0.0750   0.4325   1.0000
   7.750   1.2544   0.01618   0.00923  -0.0733   0.4196   1.0000
   8.000   1.2720   0.01653   0.00953  -0.0715   0.4067   1.0000
   8.250   1.2882   0.01689   0.00993  -0.0695   0.3932   1.0000
   8.500   1.3038   0.01730   0.01035  -0.0675   0.3799   1.0000
   8.750   1.3182   0.01775   0.01079  -0.0653   0.3667   1.0000
   9.000   1.3306   0.01824   0.01126  -0.0627   0.3531   1.0000
   9.250   1.3393   0.01876   0.01175  -0.0596   0.3392   1.0000
   9.500   1.3463   0.01935   0.01229  -0.0563   0.3254   1.0000
   9.750   1.3527   0.02003   0.01292  -0.0530   0.3114   1.0000
  10.000   1.3587   0.02076   0.01364  -0.0500   0.2973   1.0000
  10.250   1.3650   0.02156   0.01445  -0.0471   0.2835   1.0000
  10.500   1.3706   0.02246   0.01536  -0.0444   0.2699   1.0000
  10.750   1.3757   0.02347   0.01637  -0.0418   0.2566   1.0000
  11.000   1.3801   0.02460   0.01748  -0.0394   0.2438   1.0000
  11.250   1.3836   0.02587   0.01873  -0.0371   0.2314   1.0000
  11.750   1.3911   0.02864   0.02150  -0.0331   0.2082   1.0000
  12.000   1.3958   0.03010   0.02298  -0.0314   0.1984   1.0000
  12.250   1.3978   0.03180   0.02462  -0.0297   0.1896   1.0000
  12.500   1.4033   0.03332   0.02622  -0.0284   0.1804   1.0000
  12.750   1.4063   0.03507   0.02799  -0.0270   0.1720   1.0000
  13.000   1.4093   0.03689   0.02983  -0.0258   0.1642   1.0000
  13.250   1.4132   0.03869   0.03169  -0.0248   0.1571   1.0000
  13.500   1.4152   0.04070   0.03373  -0.0238   0.1501   1.0000
  13.750   1.4184   0.04269   0.03579  -0.0229   0.1433   1.0000
  14.000   1.4185   0.04503   0.03816  -0.0222   0.1360   1.0000
  14.250   1.4201   0.04732   0.04055  -0.0216   0.1280   1.0000
  14.500   1.4163   0.05024   0.04346  -0.0212   0.1202   1.0000
  14.750   1.4137   0.05319   0.04649  -0.0209   0.1099   1.0000
  15.000   1.4087   0.05654   0.04988  -0.0209   0.0985   1.0000
  15.250   1.3991   0.06055   0.05388  -0.0210   0.0857   1.0000
  15.500   1.3888   0.06477   0.05808  -0.0213   0.0733   1.0000
  15.750   1.3774   0.06926   0.06254  -0.0218   0.0641   1.0000
  16.000   1.3687   0.07352   0.06683  -0.0223   0.0586   1.0000
  16.250   1.3597   0.07790   0.07124  -0.0230   0.0549   1.0000
  16.500   1.3526   0.08214   0.07554  -0.0238   0.0518   1.0000
  16.750   1.3419   0.08696   0.08037  -0.0249   0.0494   1.0000
  17.000   1.3371   0.09098   0.08448  -0.0258   0.0475   1.0000
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