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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.09 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe574-il-1000000-n5.txt
Download as CSV file: xf-goe574-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 574 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2201   0.09079   0.08913  -0.0660   0.9733   0.0037
  -9.000  -0.2196   0.08712   0.08548  -0.0670   0.9682   0.0035
  -8.750  -0.2370   0.08525   0.08365  -0.0625   0.9553   0.0034
  -8.500  -0.2267   0.08092   0.07931  -0.0665   0.9215   0.0039
  -8.000  -0.2883   0.01813   0.01446  -0.1164   0.8433   0.0045
  -7.750  -0.2714   0.01583   0.01162  -0.1152   0.8126   0.0046
  -7.500  -0.2564   0.01450   0.00993  -0.1131   0.7922   0.0048
  -7.250  -0.2386   0.01367   0.00886  -0.1112   0.7745   0.0051
  -7.000  -0.2194   0.01302   0.00799  -0.1096   0.7581   0.0054
  -6.750  -0.1989   0.01256   0.00738  -0.1082   0.7423   0.0058
  -6.500  -0.1785   0.01206   0.00669  -0.1067   0.7268   0.0061
  -6.250  -0.1575   0.01161   0.00608  -0.1053   0.7119   0.0066
  -6.000  -0.1360   0.01123   0.00553  -0.1040   0.6969   0.0069
  -5.750  -0.1141   0.01088   0.00505  -0.1028   0.6818   0.0078
  -5.500  -0.0915   0.01062   0.00470  -0.1018   0.6664   0.0088
  -5.250  -0.0688   0.01036   0.00430  -0.1007   0.6516   0.0098
  -5.000  -0.0455   0.01014   0.00398  -0.0998   0.6368   0.0114
  -4.750  -0.0198   0.01022   0.00403  -0.0993   0.6219   0.0132
  -4.500   0.0051   0.01020   0.00393  -0.0987   0.6073   0.0149
  -4.250   0.0297   0.01014   0.00377  -0.0981   0.5917   0.0160
  -4.000   0.0564   0.01036   0.00396  -0.0979   0.5759   0.0172
  -3.750   0.0820   0.01044   0.00396  -0.0975   0.5609   0.0186
  -3.500   0.1068   0.01040   0.00382  -0.0969   0.5452   0.0201
  -3.250   0.1321   0.01042   0.00375  -0.0964   0.5314   0.0216
  -3.000   0.1573   0.01042   0.00367  -0.0959   0.5184   0.0227
  -2.750   0.1824   0.01041   0.00357  -0.0953   0.5064   0.0232
  -2.500   0.2080   0.01049   0.00359  -0.0949   0.4952   0.0237
  -2.250   0.2310   0.01017   0.00316  -0.0940   0.4852   0.0246
  -2.000   0.2534   0.00981   0.00274  -0.0929   0.4771   0.0258
  -1.500   0.3010   0.00952   0.00233  -0.0912   0.4629   0.0269
  -1.250   0.3249   0.00942   0.00217  -0.0904   0.4564   0.0271
  -1.000   0.3489   0.00933   0.00203  -0.0896   0.4511   0.0273
  -0.750   0.3731   0.00925   0.00191  -0.0889   0.4458   0.0275
  -0.250   0.4213   0.00914   0.00172  -0.0873   0.4371   0.0281
   0.000   0.4455   0.00908   0.00164  -0.0866   0.4335   0.0280
   0.250   0.4697   0.00905   0.00158  -0.0858   0.4300   0.0279
   0.500   0.4938   0.00903   0.00154  -0.0851   0.4267   0.0278
   0.750   0.5180   0.00901   0.00150  -0.0844   0.4240   0.0279
   1.000   0.5425   0.00900   0.00147  -0.0837   0.4214   0.0280
   1.250   0.5668   0.00898   0.00145  -0.0830   0.4190   0.0284
   1.500   0.5911   0.00899   0.00145  -0.0823   0.4164   0.0292
   1.750   0.6153   0.00901   0.00146  -0.0816   0.4140   0.0299
   2.000   0.6392   0.00903   0.00148  -0.0808   0.4115   0.0331
   2.250   0.6625   0.00897   0.00154  -0.0799   0.4094   0.0857
   2.500   0.6782   0.00844   0.00170  -0.0776   0.4073   0.3884
   3.000   0.8633   0.00811   0.00276  -0.1084   0.3947   0.9925
   3.250   0.9247   0.00827   0.00289  -0.1163   0.3873   0.9977
   3.500   0.9697   0.00838   0.00296  -0.1206   0.3777   1.0000
   3.750   0.9916   0.00847   0.00305  -0.1194   0.3714   1.0000
   4.000   1.0129   0.00859   0.00315  -0.1181   0.3608   1.0000
   4.250   1.0333   0.00875   0.00325  -0.1167   0.3455   1.0000
   4.500   1.0411   0.00964   0.00364  -0.1129   0.2536   1.0000
   4.750   1.0454   0.01068   0.00425  -0.1084   0.1722   1.0000
   5.000   1.0397   0.01215   0.00515  -0.1019   0.0436   1.0000
   5.250   1.0533   0.01257   0.00548  -0.0990   0.0161   1.0000
   5.500   1.0696   0.01283   0.00574  -0.0968   0.0125   1.0000
   5.750   1.0856   0.01309   0.00605  -0.0944   0.0100   1.0000
   6.000   1.1005   0.01332   0.00631  -0.0919   0.0094   1.0000
   6.250   1.1140   0.01353   0.00656  -0.0890   0.0085   1.0000
   6.500   1.1267   0.01378   0.00684  -0.0860   0.0078   1.0000
   6.750   1.1387   0.01408   0.00715  -0.0829   0.0068   1.0000
   7.000   1.1500   0.01443   0.00755  -0.0796   0.0061   1.0000
   7.250   1.1634   0.01473   0.00788  -0.0769   0.0057   1.0000
   7.500   1.1763   0.01508   0.00827  -0.0741   0.0053   1.0000
   7.750   1.1884   0.01547   0.00872  -0.0712   0.0050   1.0000
   8.000   1.2012   0.01586   0.00914  -0.0685   0.0046   1.0000
   8.250   1.2125   0.01634   0.00965  -0.0656   0.0044   1.0000
   8.500   1.2228   0.01686   0.01022  -0.0625   0.0039   1.0000
   8.750   1.2334   0.01741   0.01083  -0.0596   0.0038   1.0000
   9.000   1.2429   0.01802   0.01151  -0.0566   0.0036   1.0000
   9.250   1.2509   0.01874   0.01230  -0.0534   0.0035   1.0000
   9.500   1.2625   0.01930   0.01290  -0.0510   0.0032   1.0000
   9.750   1.2668   0.02025   0.01395  -0.0475   0.0031   1.0000
  10.000   1.2824   0.02067   0.01439  -0.0460   0.0028   1.0000
  10.250   1.2788   0.02214   0.01600  -0.0416   0.0030   1.0000
  10.500   1.2940   0.02264   0.01650  -0.0403   0.0027   1.0000
  10.750   1.2973   0.02388   0.01782  -0.0375   0.0026   1.0000
  11.000   1.2877   0.02613   0.02020  -0.0337   0.0024   1.0000
  11.250   1.2910   0.02768   0.02183  -0.0316   0.0024   1.0000
  11.500   1.2935   0.02943   0.02368  -0.0298   0.0024   1.0000
  11.750   1.2930   0.03156   0.02592  -0.0281   0.0023   1.0000
  12.000   1.2897   0.03408   0.02855  -0.0264   0.0023   1.0000
  12.250   1.2847   0.03688   0.03146  -0.0250   0.0023   1.0000
  12.500   1.2846   0.03931   0.03399  -0.0240   0.0022   1.0000
  12.750   1.2832   0.04195   0.03673  -0.0231   0.0022   1.0000
  13.000   1.2907   0.04375   0.03860  -0.0227   0.0020   1.0000
  13.250   1.2822   0.04718   0.04215  -0.0216   0.0021   1.0000
  13.500   1.2773   0.05026   0.04535  -0.0207   0.0020   1.0000
  13.750   1.2798   0.05269   0.04786  -0.0204   0.0019   1.0000
  14.000   1.2785   0.05550   0.05079  -0.0198   0.0019   1.0000
  14.250   1.2728   0.05865   0.05409  -0.0185   0.0019   1.0000
  14.500   1.2785   0.06100   0.05650  -0.0190   0.0018   1.0000
  14.750   1.2781   0.06387   0.05946  -0.0187   0.0017   1.0000
  15.000   1.2805   0.06659   0.06227  -0.0190   0.0017   1.0000
  15.250   1.2770   0.06982   0.06562  -0.0185   0.0016   1.0000
  15.500   1.2774   0.07281   0.06870  -0.0187   0.0016   1.0000
  15.750   1.2671   0.07671   0.07284  -0.0172   0.0016   1.0000
  16.000   1.2731   0.07948   0.07561  -0.0190   0.0016   1.0000
  16.250   1.2668   0.08334   0.07962  -0.0190   0.0016   1.0000
  16.500   1.2685   0.08656   0.08289  -0.0203   0.0015   1.0000
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