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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 200,000
Max Cl/Cd: 75.3 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe408-il-200000-n5.txt
Download as CSV file: xf-goe408-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3873   0.09126   0.08788  -0.0205   1.0000   0.0166
  -7.500  -0.3948   0.08866   0.08535  -0.0198   1.0000   0.0165
  -7.250  -0.4027   0.08606   0.08280  -0.0189   1.0000   0.0165
  -7.000  -0.4051   0.08280   0.07959  -0.0193   1.0000   0.0164
  -6.750  -0.4062   0.07949   0.07631  -0.0199   1.0000   0.0164
  -6.500  -0.4029   0.07573   0.07257  -0.0215   0.9994   0.0164
  -6.250  -0.3764   0.06977   0.06654  -0.0296   0.9945   0.0165
  -6.000  -0.3488   0.06227   0.05890  -0.0386   0.9884   0.0177
  -5.750  -0.3230   0.05543   0.05189  -0.0450   0.9817   0.0184
  -5.500  -0.2963   0.05224   0.04860  -0.0482   0.9763   0.0190
  -5.000  -0.2477   0.04514   0.04121  -0.0524   0.9605   0.0214
  -4.750  -0.2284   0.03800   0.03362  -0.0533   0.9487   0.0240
  -4.500  -0.2065   0.03574   0.03119  -0.0532   0.9381   0.0253
  -4.000  -0.1590   0.02880   0.02352  -0.0524   0.9186   0.0317
  -3.750  -0.1317   0.02803   0.02266  -0.0527   0.9076   0.0338
  -3.500  -0.1058   0.02422   0.01819  -0.0518   0.8986   0.0392
  -3.250  -0.0724   0.02361   0.01754  -0.0533   0.8894   0.0411
  -3.000  -0.0408   0.02224   0.01585  -0.0540   0.8791   0.0449
  -2.750  -0.0054   0.02036   0.01344  -0.0549   0.8700   0.0471
  -2.500   0.0306   0.01862   0.01140  -0.0568   0.8592   0.0491
  -2.250   0.0703   0.01759   0.01019  -0.0594   0.8470   0.0507
  -2.000   0.1142   0.01643   0.00875  -0.0627   0.8337   0.0516
  -1.750   0.1606   0.01548   0.00755  -0.0667   0.8193   0.0527
  -1.500   0.2064   0.01473   0.00657  -0.0706   0.8038   0.0538
  -1.250   0.2468   0.01418   0.00582  -0.0732   0.7871   0.0550
  -1.000   0.2828   0.01385   0.00532  -0.0749   0.7702   0.0571
  -0.750   0.3151   0.01353   0.00486  -0.0758   0.7547   0.0583
  -0.500   0.3448   0.01323   0.00445  -0.0761   0.7401   0.0588
  -0.250   0.3727   0.01298   0.00412  -0.0760   0.7259   0.0593
   0.000   0.3988   0.01262   0.00372  -0.0756   0.7126   0.0606
   0.250   0.4238   0.01241   0.00347  -0.0749   0.6995   0.0621
   0.500   0.4485   0.01228   0.00331  -0.0742   0.6870   0.0636
   0.750   0.4730   0.01221   0.00319  -0.0733   0.6749   0.0655
   1.000   0.4968   0.01216   0.00310  -0.0724   0.6621   0.0674
   1.250   0.5204   0.01214   0.00304  -0.0714   0.6492   0.0713
   1.500   0.5439   0.01211   0.00301  -0.0703   0.6366   0.0763
   1.750   0.5674   0.01212   0.00300  -0.0693   0.6237   0.0803
   2.000   0.5909   0.01213   0.00301  -0.0682   0.6109   0.0905
   2.250   0.6142   0.01214   0.00304  -0.0672   0.5977   0.1152
   2.750   0.8175   0.01133   0.00379  -0.1019   0.5274   1.0000
   3.000   0.8387   0.01155   0.00391  -0.1004   0.5055   1.0000
   3.250   0.8600   0.01177   0.00403  -0.0990   0.4861   1.0000
   3.500   0.8822   0.01198   0.00419  -0.0977   0.4714   1.0000
   3.750   0.9044   0.01219   0.00438  -0.0965   0.4572   1.0000
   4.000   0.9264   0.01242   0.00457  -0.0953   0.4433   1.0000
   4.250   0.9484   0.01266   0.00478  -0.0940   0.4302   1.0000
   4.500   0.9704   0.01290   0.00501  -0.0928   0.4173   1.0000
   4.750   0.9917   0.01317   0.00527  -0.0914   0.4021   1.0000
   5.000   1.0118   0.01347   0.00552  -0.0899   0.3809   1.0000
   5.250   1.0316   0.01380   0.00579  -0.0882   0.3603   1.0000
   5.500   1.0516   0.01412   0.00608  -0.0866   0.3379   1.0000
   5.750   1.0714   0.01446   0.00642  -0.0850   0.3185   1.0000
   6.000   1.0908   0.01482   0.00676  -0.0834   0.2971   1.0000
   6.250   1.1095   0.01523   0.00714  -0.0816   0.2748   1.0000
   6.500   1.1271   0.01571   0.00755  -0.0797   0.2496   1.0000
   6.750   1.1440   0.01624   0.00802  -0.0777   0.2259   1.0000
   7.250   1.1753   0.01748   0.00911  -0.0733   0.1782   1.0000
   7.500   1.1891   0.01821   0.00972  -0.0709   0.1533   1.0000
   7.750   1.2044   0.01884   0.01032  -0.0687   0.1344   1.0000
   8.000   1.2189   0.01952   0.01094  -0.0663   0.1145   1.0000
   8.250   1.2300   0.02041   0.01166  -0.0635   0.0730   1.0000
   8.500   1.2361   0.02155   0.01265  -0.0599   0.0537   1.0000
   8.750   1.2453   0.02239   0.01354  -0.0566   0.0429   1.0000
   9.000   1.2534   0.02329   0.01448  -0.0531   0.0329   1.0000
   9.250   1.2616   0.02419   0.01541  -0.0499   0.0258   1.0000
   9.500   1.2680   0.02524   0.01648  -0.0463   0.0212   1.0000
   9.750   1.2758   0.02619   0.01755  -0.0431   0.0193   1.0000
  10.000   1.2821   0.02724   0.01871  -0.0399   0.0174   1.0000
  10.250   1.2840   0.02861   0.02016  -0.0362   0.0152   1.0000
  10.500   1.2851   0.03005   0.02174  -0.0326   0.0145   1.0000
  10.750   1.2885   0.03139   0.02324  -0.0295   0.0140   1.0000
  11.000   1.2901   0.03294   0.02498  -0.0265   0.0133   1.0000
  11.250   1.2904   0.03468   0.02687  -0.0237   0.0130   1.0000
  11.500   1.2904   0.03657   0.02890  -0.0213   0.0127   1.0000
  11.750   1.2892   0.03871   0.03118  -0.0191   0.0122   1.0000
  12.000   1.2882   0.04098   0.03357  -0.0173   0.0117   1.0000
  12.250   1.2875   0.04333   0.03605  -0.0160   0.0113   1.0000
  12.500   1.2838   0.04613   0.03895  -0.0148   0.0107   1.0000
  12.750   1.2752   0.04962   0.04254  -0.0139   0.0100   1.0000
  13.000   1.2721   0.05269   0.04574  -0.0130   0.0100   1.0000
  13.250   1.2713   0.05553   0.04875  -0.0125   0.0099   1.0000
  13.500   1.2697   0.05856   0.05194  -0.0122   0.0097   1.0000
  13.750   1.2661   0.06195   0.05551  -0.0119   0.0095   1.0000
  14.000   1.2612   0.06559   0.05934  -0.0120   0.0091   1.0000
  14.250   1.2564   0.06932   0.06324  -0.0122   0.0091   1.0000
  14.500   1.2502   0.07333   0.06741  -0.0126   0.0090   1.0000
  14.750   1.2432   0.07759   0.07185  -0.0134   0.0088   1.0000
  15.000   1.2354   0.08211   0.07657  -0.0145   0.0087   1.0000
  15.250   1.2253   0.08718   0.08183  -0.0159   0.0086   1.0000
  15.500   1.2157   0.09231   0.08713  -0.0176   0.0085   1.0000
  15.750   1.2046   0.09788   0.09288  -0.0195   0.0087   1.0000
  16.000   1.1931   0.10374   0.09891  -0.0220   0.0086   1.0000
  16.250   1.1786   0.11042   0.10577  -0.0250   0.0084   1.0000
  16.500   1.1654   0.11703   0.11255  -0.0281   0.0084   1.0000
  16.750   1.1494   0.12454   0.12024  -0.0319   0.0084   1.0000
  17.000   1.1350   0.13201   0.12787  -0.0358   0.0085   1.0000
  17.250   1.1174   0.14060   0.13663  -0.0405   0.0085   1.0000
  17.500   1.0995   0.14974   0.14589  -0.0456   0.0086   1.0000
  17.750   1.0818   0.15932   0.15561  -0.0510   0.0088   1.0000
  18.000   1.0582   0.17159   0.16802  -0.0579   0.0089   1.0000
  18.250   1.0324   0.18567   0.18217  -0.0654   0.0093   1.0000
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