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GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 432 AIRFOIL (goe432-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.58 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe432-il-1000000-n5.txt
Download as CSV file: xf-goe432-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 432 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3659   0.11322   0.11154  -0.0203   1.0000   0.0044
 -10.000  -0.3655   0.10965   0.10799  -0.0207   1.0000   0.0042
  -8.500  -0.4276   0.02109   0.01817  -0.0997   0.9770   0.0049
  -8.250  -0.4064   0.01810   0.01481  -0.1002   0.9739   0.0051
  -8.000  -0.3820   0.01644   0.01291  -0.1004   0.9708   0.0052
  -7.750  -0.3543   0.01522   0.01147  -0.1009   0.9683   0.0054
  -7.500  -0.3255   0.01428   0.01036  -0.1014   0.9663   0.0055
  -7.250  -0.2984   0.01305   0.00891  -0.1017   0.9638   0.0058
  -7.000  -0.2747   0.01222   0.00794  -0.1010   0.9591   0.0061
  -6.750  -0.2474   0.01159   0.00720  -0.1009   0.9553   0.0063
  -6.500  -0.2180   0.01105   0.00655  -0.1012   0.9522   0.0066
  -6.250  -0.1925   0.01059   0.00600  -0.1007   0.9469   0.0069
  -6.000  -0.1653   0.01012   0.00545  -0.1004   0.9399   0.0073
  -5.750  -0.1383   0.00971   0.00494  -0.1001   0.9307   0.0076
  -5.500  -0.1108   0.00936   0.00449  -0.0998   0.9184   0.0080
  -5.250  -0.0839   0.00892   0.00393  -0.0994   0.9028   0.0086
  -5.000  -0.0568   0.00862   0.00353  -0.0991   0.8803   0.0095
  -4.750  -0.0312   0.00846   0.00318  -0.0983   0.8435   0.0103
  -4.250   0.0181   0.00823   0.00259  -0.0965   0.7816   0.0124
  -4.000   0.0430   0.00813   0.00237  -0.0957   0.7543   0.0142
  -3.750   0.0677   0.00808   0.00217  -0.0949   0.7225   0.0164
  -3.500   0.0922   0.00808   0.00206  -0.0940   0.6860   0.0205
  -3.250   0.1169   0.00813   0.00196  -0.0932   0.6446   0.0240
  -3.000   0.1410   0.00828   0.00191  -0.0923   0.5918   0.0272
  -2.750   0.1659   0.00844   0.00187  -0.0916   0.5491   0.0292
  -2.500   0.1918   0.00845   0.00178  -0.0910   0.5252   0.0315
  -2.250   0.2182   0.00846   0.00172  -0.0906   0.5081   0.0338
  -2.000   0.2449   0.00847   0.00168  -0.0903   0.4939   0.0359
  -1.750   0.2718   0.00848   0.00163  -0.0899   0.4816   0.0376
  -1.500   0.2987   0.00849   0.00158  -0.0896   0.4703   0.0385
  -1.250   0.3253   0.00843   0.00145  -0.0892   0.4589   0.0401
  -1.000   0.3520   0.00838   0.00135  -0.0888   0.4475   0.0427
  -0.750   0.3788   0.00837   0.00130  -0.0885   0.4354   0.0449
  -0.500   0.4054   0.00840   0.00126  -0.0881   0.4198   0.0474
  -0.250   0.4320   0.00844   0.00123  -0.0877   0.4049   0.0494
   0.000   0.4586   0.00849   0.00122  -0.0874   0.3909   0.0508
   0.250   0.4852   0.00851   0.00120  -0.0870   0.3786   0.0567
   0.500   0.5118   0.00855   0.00120  -0.0866   0.3666   0.0623
   0.750   0.5380   0.00856   0.00123  -0.0862   0.3537   0.0876
   1.000   0.5639   0.00853   0.00126  -0.0858   0.3409   0.1400
   1.250   0.5896   0.00843   0.00134  -0.0854   0.3292   0.2317
   1.500   0.6156   0.00839   0.00142  -0.0850   0.3195   0.2969
   1.750   0.6411   0.00833   0.00150  -0.0846   0.3084   0.3778
   2.000   0.6593   0.00761   0.00167  -0.0829   0.2927   0.7596
   2.500   0.7359   0.00785   0.00199  -0.0877   0.2147   1.0000
   2.750   0.7588   0.00824   0.00219  -0.0868   0.1797   1.0000
   3.000   0.7836   0.00846   0.00232  -0.0861   0.1694   1.0000
   3.250   0.8092   0.00860   0.00244  -0.0856   0.1657   1.0000
   3.500   0.8347   0.00875   0.00256  -0.0850   0.1625   1.0000
   3.750   0.8601   0.00890   0.00269  -0.0845   0.1597   1.0000
   4.000   0.8856   0.00906   0.00283  -0.0840   0.1569   1.0000
   4.250   0.9111   0.00921   0.00298  -0.0835   0.1545   1.0000
   4.500   0.9368   0.00934   0.00311  -0.0830   0.1535   1.0000
   4.750   0.9624   0.00947   0.00325  -0.0825   0.1523   1.0000
   5.000   0.9880   0.00962   0.00341  -0.0820   0.1508   1.0000
   5.250   1.0134   0.00978   0.00358  -0.0815   0.1489   1.0000
   5.500   1.0386   0.00995   0.00375  -0.0810   0.1465   1.0000
   5.750   1.0637   0.01013   0.00394  -0.0805   0.1444   1.0000
   6.000   1.0886   0.01033   0.00415  -0.0799   0.1419   1.0000
   6.250   1.1135   0.01052   0.00436  -0.0794   0.1399   1.0000
   6.500   1.1388   0.01067   0.00454  -0.0789   0.1388   1.0000
   6.750   1.1640   0.01082   0.00473  -0.0784   0.1344   1.0000
   7.000   1.1882   0.01107   0.00494  -0.0778   0.1273   1.0000
   7.250   1.2124   0.01131   0.00514  -0.0772   0.1162   1.0000
   7.500   1.2334   0.01185   0.00549  -0.0761   0.0892   1.0000
   7.750   1.2553   0.01229   0.00588  -0.0752   0.0787   1.0000
   8.000   1.2785   0.01260   0.00621  -0.0744   0.0726   1.0000
   8.250   1.3001   0.01304   0.00662  -0.0734   0.0631   1.0000
   8.500   1.3162   0.01398   0.00735  -0.0716   0.0341   1.0000
   8.750   1.3327   0.01486   0.00813  -0.0699   0.0158   1.0000
   9.000   1.3526   0.01540   0.00867  -0.0686   0.0111   1.0000
   9.250   1.3725   0.01592   0.00922  -0.0674   0.0090   1.0000
   9.500   1.3928   0.01638   0.00972  -0.0662   0.0079   1.0000
   9.750   1.4118   0.01693   0.01030  -0.0649   0.0068   1.0000
  10.000   1.4309   0.01744   0.01086  -0.0635   0.0061   1.0000
  10.250   1.4496   0.01794   0.01141  -0.0622   0.0056   1.0000
  10.500   1.4670   0.01851   0.01202  -0.0606   0.0050   1.0000
  10.750   1.4829   0.01916   0.01274  -0.0588   0.0046   1.0000
  11.000   1.4978   0.01974   0.01338  -0.0568   0.0043   1.0000
  11.250   1.5110   0.02034   0.01404  -0.0546   0.0041   1.0000
  11.500   1.5232   0.02098   0.01475  -0.0522   0.0039   1.0000
  11.750   1.5349   0.02165   0.01549  -0.0498   0.0037   1.0000
  12.000   1.5454   0.02241   0.01632  -0.0474   0.0035   1.0000
  12.250   1.5552   0.02323   0.01720  -0.0450   0.0034   1.0000
  12.500   1.5618   0.02426   0.01830  -0.0423   0.0031   1.0000
  12.750   1.5665   0.02545   0.01960  -0.0396   0.0030   1.0000
  13.000   1.5750   0.02642   0.02066  -0.0375   0.0029   1.0000
  13.250   1.5819   0.02755   0.02188  -0.0354   0.0028   1.0000
  13.500   1.5871   0.02884   0.02326  -0.0333   0.0027   1.0000
  13.750   1.5905   0.03034   0.02486  -0.0313   0.0026   1.0000
  14.000   1.5916   0.03213   0.02676  -0.0294   0.0025   1.0000
  14.250   1.5938   0.03396   0.02868  -0.0280   0.0025   1.0000
  14.500   1.5952   0.03599   0.03080  -0.0268   0.0024   1.0000
  14.750   1.5944   0.03839   0.03331  -0.0259   0.0023   1.0000
  15.000   1.5924   0.04109   0.03611  -0.0254   0.0022   1.0000
  15.250   1.5838   0.04480   0.03996  -0.0254   0.0022   1.0000
  15.500   1.5792   0.04830   0.04357  -0.0258   0.0021   1.0000
  15.750   1.5721   0.05237   0.04777  -0.0267   0.0021   1.0000
  16.000   1.5596   0.05754   0.05308  -0.0283   0.0021   1.0000
  16.250   1.5480   0.06280   0.05847  -0.0303   0.0021   1.0000
  16.500   1.5356   0.06832   0.06412  -0.0324   0.0021   1.0000
  16.750   1.5166   0.07504   0.07100  -0.0352   0.0020   1.0000
  17.000   1.4945   0.08249   0.07859  -0.0384   0.0020   1.0000
  17.250   1.4754   0.08965   0.08588  -0.0416   0.0020   1.0000
  17.500   1.4564   0.09699   0.09335  -0.0449   0.0020   1.0000
  17.750   1.4338   0.10526   0.10177  -0.0489   0.0020   1.0000
  18.000   1.4128   0.11350   0.11013  -0.0530   0.0021   1.0000
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