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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 100,000
Max Cl/Cd: 58.34 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe408-il-100000.txt
Download as CSV file: xf-goe408-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3827   0.09471   0.08994  -0.0207   1.0000   0.0638
  -7.250  -0.3898   0.09251   0.08781  -0.0202   1.0000   0.0653
  -7.000  -0.3937   0.09021   0.08558  -0.0221   1.0000   0.0671
  -6.750  -0.3946   0.08832   0.08371  -0.0259   1.0000   0.0681
  -6.500  -0.3929   0.08686   0.08215  -0.0304   1.0000   0.0687
  -6.250  -0.3904   0.08090   0.07633  -0.0272   1.0000   0.0697
  -6.000  -0.3863   0.07723   0.07274  -0.0238   1.0000   0.0712
  -5.750  -0.3821   0.07436   0.06991  -0.0222   1.0000   0.0735
  -5.500  -0.3774   0.07168   0.06723  -0.0218   1.0000   0.0770
  -5.250  -0.3643   0.07146   0.06662  -0.0274   1.0000   0.0823
  -5.000  -0.3646   0.06601   0.06137  -0.0243   1.0000   0.0839
  -4.750  -0.3623   0.06313   0.05857  -0.0213   1.0000   0.0863
  -4.500  -0.3575   0.06083   0.05627  -0.0198   1.0000   0.0897
  -4.250  -0.3427   0.06102   0.05590  -0.0218   1.0000   0.0968
  -4.000  -0.3418   0.05627   0.05139  -0.0193   1.0000   0.0983
  -3.750  -0.3389   0.05377   0.04897  -0.0167   1.0000   0.1015
  -3.500  -0.3250   0.05328   0.04801  -0.0168   1.0000   0.1114
  -3.250  -0.3045   0.04907   0.04401  -0.0177   0.9954   0.1185
  -3.000  -0.2659   0.04590   0.04059  -0.0220   0.9866   0.1325
  -2.750  -0.2265   0.04368   0.03793  -0.0259   0.9763   0.1555
  -2.500  -0.1991   0.04046   0.03477  -0.0274   0.9673   0.1759
  -2.250  -0.1676   0.03874   0.03274  -0.0293   0.9569   0.2145
  -2.000  -0.1395   0.03569   0.02977  -0.0304   0.9489   0.2493
  -1.750  -0.1167   0.03350   0.02764  -0.0301   0.9391   0.3090
  -1.500  -0.0937   0.03147   0.02564  -0.0292   0.9285   0.3584
  -1.250  -0.0641   0.02982   0.02381  -0.0294   0.9185   0.3945
  -1.000   0.0696   0.01148   0.00369  -0.0437   0.8906   0.1527
  -0.750   0.0651   0.02648   0.01795  -0.0377   0.9029   0.1419
  -0.500   0.1131   0.02490   0.01609  -0.0407   0.8970   0.1350
  -0.250   0.1491   0.02382   0.01480  -0.0417   0.8862   0.1339
   0.000   0.2021   0.02234   0.01307  -0.0456   0.8816   0.1295
   0.250   0.2403   0.02142   0.01202  -0.0469   0.8707   0.1288
   0.500   0.2990   0.02004   0.01063  -0.0523   0.8664   0.1317
   0.750   0.3407   0.01937   0.00993  -0.0546   0.8548   0.1393
   1.000   0.3932   0.01827   0.00899  -0.0592   0.8453   0.1453
   1.250   0.4659   0.01722   0.00796  -0.0679   0.8374   0.1604
   1.500   0.6532   0.01445   0.00694  -0.1022   0.8283   1.0000
   1.750   0.6986   0.01438   0.00671  -0.1055   0.8091   1.0000
   2.000   0.7357   0.01448   0.00668  -0.1071   0.7890   1.0000
   2.250   0.7659   0.01469   0.00681  -0.1072   0.7681   1.0000
   2.500   0.7970   0.01492   0.00693  -0.1075   0.7486   1.0000
   2.750   0.8236   0.01521   0.00713  -0.1069   0.7290   1.0000
   3.000   0.8465   0.01549   0.00735  -0.1054   0.7070   1.0000
   3.250   0.8712   0.01571   0.00745  -0.1042   0.6850   1.0000
   3.500   0.8908   0.01596   0.00765  -0.1020   0.6628   1.0000
   3.750   0.9135   0.01621   0.00784  -0.1006   0.6437   1.0000
   4.000   0.9367   0.01649   0.00810  -0.0993   0.6266   1.0000
   4.250   0.9578   0.01678   0.00838  -0.0976   0.6091   1.0000
   4.500   0.9785   0.01707   0.00870  -0.0959   0.5917   1.0000
   4.750   0.9992   0.01735   0.00899  -0.0942   0.5739   1.0000
   5.000   1.0203   0.01763   0.00931  -0.0925   0.5563   1.0000
   5.250   1.0416   0.01791   0.00959  -0.0909   0.5387   1.0000
   5.500   1.0627   0.01823   0.00990  -0.0892   0.5207   1.0000
   5.750   1.0805   0.01854   0.01028  -0.0869   0.4999   1.0000
   6.000   1.0997   0.01885   0.01054  -0.0848   0.4783   1.0000
   6.250   1.1161   0.01921   0.01096  -0.0822   0.4544   1.0000
   6.500   1.1325   0.01959   0.01130  -0.0797   0.4295   1.0000
   6.750   1.1478   0.02002   0.01168  -0.0769   0.4033   1.0000
   7.000   1.1614   0.02048   0.01217  -0.0739   0.3763   1.0000
   7.250   1.1755   0.02101   0.01272  -0.0711   0.3504   1.0000
   7.500   1.1892   0.02157   0.01327  -0.0683   0.3258   1.0000
   7.750   1.1996   0.02207   0.01373  -0.0649   0.2989   1.0000
   8.000   1.2085   0.02261   0.01425  -0.0613   0.2700   1.0000
   8.250   1.2168   0.02328   0.01490  -0.0578   0.2397   1.0000
   8.500   1.2226   0.02417   0.01574  -0.0539   0.2038   1.0000
   8.750   1.2216   0.02562   0.01695  -0.0491   0.1587   1.0000
   9.000   1.2145   0.02755   0.01855  -0.0434   0.1155   1.0000
   9.250   1.2127   0.02917   0.02002  -0.0384   0.0912   1.0000
   9.500   1.2122   0.03079   0.02155  -0.0339   0.0789   1.0000
   9.750   1.2135   0.03254   0.02328  -0.0298   0.0713   1.0000
  10.000   1.2149   0.03458   0.02518  -0.0263   0.0653   1.0000
  10.250   1.2253   0.03635   0.02711  -0.0238   0.0608   1.0000
  10.500   1.2395   0.03859   0.02933  -0.0220   0.0564   1.0000
  10.750   1.2716   0.04227   0.03305  -0.0231   0.0527   1.0000
  11.000   1.2790   0.04425   0.03539  -0.0203   0.0500   1.0000
  11.250   1.2910   0.04679   0.03820  -0.0184   0.0482   1.0000
  11.500   1.3003   0.04967   0.04134  -0.0164   0.0467   1.0000
  11.750   1.3048   0.05270   0.04467  -0.0139   0.0462   1.0000
  12.000   1.3030   0.05578   0.04805  -0.0110   0.0459   1.0000
  12.250   1.2946   0.05895   0.05156  -0.0077   0.0459   1.0000
  12.500   1.2823   0.06244   0.05535  -0.0047   0.0457   1.0000
  12.750   1.2649   0.06607   0.05930  -0.0022   0.0459   1.0000
  13.000   1.2429   0.07024   0.06380  -0.0006   0.0466   1.0000
  13.250   1.2192   0.07501   0.06887  -0.0002   0.0471   1.0000
  13.500   1.1935   0.08053   0.07464  -0.0009   0.0472   1.0000
  13.750   1.1670   0.08664   0.08100  -0.0028   0.0479   1.0000
  14.000   1.1377   0.09389   0.08846  -0.0060   0.0485   1.0000
  14.250   1.1074   0.10209   0.09685  -0.0105   0.0493   1.0000
  14.500   1.0763   0.11145   0.10635  -0.0161   0.0502   1.0000
  14.750   1.0435   0.12244   0.11741  -0.0229   0.0513   1.0000
  15.000   1.0175   0.13316   0.12815  -0.0290   0.0525   1.0000
  15.250   1.0023   0.14199   0.13696  -0.0327   0.0534   1.0000
  15.500   0.7184   0.15828   0.15338  -0.0347   0.0828   1.0000
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