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GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 546 AIRFOIL (goe546-il)
Reynolds number: 500,000
Max Cl/Cd: 106.71 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe546-il-500000.txt
Download as CSV file: xf-goe546-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 546 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3900   0.10902   0.10657  -0.0357   1.0000   0.0261
 -10.500  -0.3885   0.10570   0.10328  -0.0365   1.0000   0.0268
 -10.250  -0.3911   0.10152   0.09911  -0.0384   1.0000   0.0283
 -10.000  -0.3329   0.08465   0.08250  -0.0437   1.0000   0.0297
  -9.750  -0.3350   0.08246   0.08034  -0.0421   1.0000   0.0300
  -9.500  -0.3396   0.08127   0.07919  -0.0395   0.9998   0.0303
  -9.250  -0.3275   0.07759   0.07550  -0.0419   0.9984   0.0310
  -9.000  -0.3193   0.07298   0.07090  -0.0452   0.9965   0.0317
  -8.750  -0.3130   0.06782   0.06574  -0.0493   0.9943   0.0332
  -8.500  -0.3972   0.03694   0.03466  -0.0811   0.9808   0.0300
  -8.250  -0.3882   0.03163   0.02919  -0.0864   0.9751   0.0303
  -8.000  -0.4319   0.03595   0.03282  -0.0913   0.9732   0.0264
  -7.750  -0.4233   0.02772   0.02380  -0.0937   0.9652   0.0267
  -7.500  -0.3984   0.02372   0.01923  -0.0954   0.9619   0.0279
  -7.250  -0.3657   0.02227   0.01735  -0.0970   0.9600   0.0292
  -7.000  -0.3404   0.01951   0.01436  -0.0980   0.9564   0.0307
  -6.750  -0.3113   0.01879   0.01359  -0.0987   0.9522   0.0318
  -6.500  -0.2797   0.01775   0.01240  -0.0998   0.9493   0.0330
  -6.250  -0.2466   0.01682   0.01129  -0.1011   0.9468   0.0345
  -6.000  -0.2131   0.01643   0.01072  -0.1022   0.9439   0.0357
  -5.750  -0.1882   0.01451   0.00865  -0.1021   0.9380   0.0370
  -5.500  -0.1572   0.01378   0.00789  -0.1029   0.9340   0.0383
  -5.250  -0.1238   0.01327   0.00733  -0.1042   0.9309   0.0400
  -5.000  -0.0973   0.01276   0.00677  -0.1039   0.9246   0.0413
  -4.750  -0.0680   0.01224   0.00617  -0.1041   0.9193   0.0424
  -4.500  -0.0370   0.01188   0.00572  -0.1047   0.9147   0.0435
  -4.250  -0.0132   0.01111   0.00492  -0.1039   0.9078   0.0452
  -4.000   0.0146   0.01063   0.00441  -0.1039   0.9021   0.0469
  -3.750   0.0408   0.01033   0.00408  -0.1035   0.8953   0.0487
  -3.500   0.0676   0.01006   0.00376  -0.1031   0.8878   0.0507
  -3.250   0.0942   0.00986   0.00352  -0.1027   0.8800   0.0529
  -3.000   0.1199   0.00949   0.00310  -0.1021   0.8723   0.0563
  -2.750   0.1465   0.00926   0.00285  -0.1018   0.8657   0.0608
  -2.500   0.1726   0.00905   0.00261  -0.1012   0.8582   0.0670
  -2.250   0.1994   0.00875   0.00236  -0.1009   0.8517   0.0859
  -2.000   0.2217   0.00797   0.00215  -0.1001   0.8435   0.2453
  -1.750   0.2469   0.00756   0.00208  -0.0997   0.8365   0.3619
  -1.500   0.2717   0.00734   0.00206  -0.0990   0.8277   0.4303
  -1.250   0.2981   0.00721   0.00202  -0.0986   0.8199   0.4803
  -1.000   0.3235   0.00707   0.00199  -0.0979   0.8106   0.5235
  -0.750   0.3493   0.00695   0.00196  -0.0973   0.8016   0.5648
  -0.500   0.3741   0.00677   0.00194  -0.0966   0.7921   0.6265
  -0.250   0.3956   0.00643   0.00196  -0.0950   0.7804   0.7274
   0.000   0.4165   0.00603   0.00201  -0.0928   0.7684   0.8887
   0.250   0.4809   0.00596   0.00195  -0.1005   0.7562   0.9765
   0.500   0.5264   0.00601   0.00191  -0.1043   0.7421   1.0000
   0.750   0.5495   0.00607   0.00189  -0.1032   0.7270   1.0000
   1.000   0.5728   0.00616   0.00188  -0.1021   0.7124   1.0000
   1.250   0.5962   0.00626   0.00189  -0.1011   0.6975   1.0000
   1.500   0.6196   0.00638   0.00192  -0.1000   0.6827   1.0000
   1.750   0.6429   0.00651   0.00196  -0.0989   0.6673   1.0000
   2.000   0.6659   0.00666   0.00202  -0.0978   0.6494   1.0000
   2.250   0.6887   0.00682   0.00209  -0.0966   0.6304   1.0000
   2.500   0.7123   0.00698   0.00218  -0.0956   0.6151   1.0000
   2.750   0.7361   0.00713   0.00227  -0.0947   0.6006   1.0000
   3.000   0.7602   0.00727   0.00237  -0.0939   0.5864   1.0000
   3.250   0.7843   0.00742   0.00248  -0.0930   0.5721   1.0000
   3.500   0.8078   0.00758   0.00258  -0.0920   0.5529   1.0000
   3.750   0.8302   0.00778   0.00269  -0.0908   0.5274   1.0000
   4.000   0.8525   0.00800   0.00282  -0.0897   0.5009   1.0000
   4.250   0.8745   0.00827   0.00298  -0.0885   0.4722   1.0000
   4.500   0.8951   0.00862   0.00317  -0.0870   0.4393   1.0000
   4.750   0.9154   0.00901   0.00341  -0.0856   0.4013   1.0000
   5.000   0.9346   0.00950   0.00369  -0.0840   0.3549   1.0000
   5.250   0.9520   0.01013   0.00402  -0.0821   0.2953   1.0000
   5.500   0.9678   0.01091   0.00447  -0.0801   0.2356   1.0000
   5.750   0.9841   0.01168   0.00495  -0.0781   0.1809   1.0000
   6.000   0.9939   0.01293   0.00567  -0.0752   0.0905   1.0000
   6.250   1.0102   0.01370   0.00624  -0.0733   0.0565   1.0000
   6.500   1.0301   0.01419   0.00668  -0.0719   0.0492   1.0000
   6.750   1.0499   0.01468   0.00715  -0.0704   0.0457   1.0000
   7.000   1.0684   0.01523   0.00774  -0.0688   0.0429   1.0000
   7.250   1.0879   0.01568   0.00824  -0.0673   0.0418   1.0000
   7.500   1.1064   0.01618   0.00879  -0.0657   0.0406   1.0000
   7.750   1.1233   0.01671   0.00937  -0.0639   0.0394   1.0000
   8.000   1.1377   0.01730   0.01001  -0.0616   0.0380   1.0000
   8.250   1.1499   0.01799   0.01073  -0.0589   0.0368   1.0000
   8.500   1.1585   0.01891   0.01169  -0.0558   0.0357   1.0000
   8.750   1.1660   0.01995   0.01281  -0.0526   0.0347   1.0000
   9.000   1.1812   0.02053   0.01345  -0.0507   0.0341   1.0000
   9.250   1.1950   0.02122   0.01421  -0.0486   0.0332   1.0000
   9.500   1.2073   0.02205   0.01510  -0.0465   0.0324   1.0000
   9.750   1.2192   0.02292   0.01603  -0.0444   0.0315   1.0000
  10.000   1.2310   0.02382   0.01697  -0.0423   0.0305   1.0000
  10.250   1.2414   0.02488   0.01805  -0.0403   0.0295   1.0000
  10.500   1.2482   0.02669   0.01990  -0.0380   0.0283   1.0000
  10.750   1.2607   0.02800   0.02129  -0.0363   0.0276   1.0000
  11.000   1.2737   0.02885   0.02224  -0.0347   0.0270   1.0000
  11.250   1.2859   0.02984   0.02332  -0.0331   0.0261   1.0000
  11.500   1.2978   0.03094   0.02449  -0.0316   0.0253   1.0000
  11.750   1.3085   0.03205   0.02567  -0.0301   0.0244   1.0000
  12.000   1.3186   0.03324   0.02690  -0.0287   0.0237   1.0000
  12.250   1.3295   0.03476   0.02843  -0.0274   0.0229   1.0000
  12.500   1.3430   0.03700   0.03076  -0.0263   0.0221   1.0000
  12.750   1.3490   0.03834   0.03226  -0.0247   0.0216   1.0000
  13.000   1.3549   0.03981   0.03387  -0.0232   0.0210   1.0000
  13.250   1.3602   0.04135   0.03552  -0.0219   0.0203   1.0000
  13.500   1.3660   0.04306   0.03735  -0.0208   0.0198   1.0000
  13.750   1.3700   0.04481   0.03919  -0.0198   0.0193   1.0000
  14.000   1.3738   0.04674   0.04120  -0.0189   0.0189   1.0000
  14.250   1.3777   0.04869   0.04321  -0.0182   0.0185   1.0000
  14.500   1.3817   0.05098   0.04554  -0.0175   0.0180   1.0000
  14.750   1.3797   0.05442   0.04916  -0.0167   0.0176   1.0000
  15.000   1.3756   0.05740   0.05233  -0.0164   0.0174   1.0000
  15.250   1.3705   0.06067   0.05580  -0.0164   0.0171   1.0000
  15.500   1.3641   0.06438   0.05970  -0.0166   0.0168   1.0000
  15.750   1.3567   0.06834   0.06384  -0.0172   0.0165   1.0000
  16.000   1.3480   0.07271   0.06840  -0.0182   0.0162   1.0000
  16.250   1.3390   0.07730   0.07316  -0.0195   0.0160   1.0000
  16.500   1.3288   0.08224   0.07826  -0.0212   0.0158   1.0000
  16.750   1.3204   0.08709   0.08324  -0.0232   0.0155   1.0000
  17.000   1.3099   0.09251   0.08881  -0.0256   0.0154   1.0000
  17.250   1.3008   0.09788   0.09431  -0.0283   0.0152   1.0000
  17.500   1.2847   0.10480   0.10140  -0.0319   0.0151   1.0000
  17.750   1.2706   0.11164   0.10839  -0.0357   0.0150   1.0000
  18.000   1.2438   0.12153   0.11850  -0.0415   0.0150   1.0000
  18.250   1.2317   0.12853   0.12563  -0.0459   0.0149   1.0000
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