Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 459 AIRFOIL (goe459-il)
Reynolds number: 500,000
Max Cl/Cd: 60.18 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe459-il-500000-n5.txt
Download as CSV file: xf-goe459-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 459 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -1.0255   0.10451   0.10074  -0.0225   1.0000   0.0088
 -17.750  -1.0552   0.09535   0.09145  -0.0272   1.0000   0.0087
 -17.500  -1.0810   0.08707   0.08301  -0.0313   1.0000   0.0088
 -17.250  -1.1034   0.07947   0.07527  -0.0352   1.0000   0.0088
 -17.000  -1.1246   0.07230   0.06795  -0.0389   1.0000   0.0088
 -16.750  -1.1422   0.06599   0.06149  -0.0420   1.0000   0.0089
 -16.500  -1.1598   0.06001   0.05536  -0.0448   1.0000   0.0088
 -16.250  -1.1701   0.05535   0.05056  -0.0468   1.0000   0.0088
 -16.000  -1.1797   0.05099   0.04607  -0.0484   1.0000   0.0091
 -15.750  -1.1871   0.04715   0.04210  -0.0496   1.0000   0.0091
 -15.500  -1.1940   0.04358   0.03840  -0.0504   1.0000   0.0092
 -15.250  -1.2022   0.04014   0.03484  -0.0507   1.0000   0.0095
 -15.000  -1.2042   0.03753   0.03213  -0.0505   1.0000   0.0096
 -14.750  -1.2045   0.03526   0.02977  -0.0500   1.0000   0.0100
 -14.500  -1.2043   0.03318   0.02757  -0.0491   1.0000   0.0101
 -14.250  -1.2010   0.03150   0.02580  -0.0480   1.0000   0.0105
 -14.000  -1.1980   0.02989   0.02409  -0.0465   1.0000   0.0108
 -13.750  -1.1926   0.02857   0.02267  -0.0450   1.0000   0.0111
 -13.500  -1.1871   0.02733   0.02133  -0.0432   1.0000   0.0114
 -13.250  -1.1801   0.02627   0.02016  -0.0412   1.0000   0.0118
 -13.000  -1.1750   0.02513   0.01895  -0.0389   1.0000   0.0122
 -12.750  -1.1697   0.02409   0.01783  -0.0364   1.0000   0.0128
 -12.500  -1.1630   0.02319   0.01686  -0.0337   1.0000   0.0133
 -12.250  -1.1558   0.02239   0.01599  -0.0310   1.0000   0.0140
 -12.000  -1.1477   0.02170   0.01523  -0.0281   1.0000   0.0146
 -11.750  -1.1409   0.02100   0.01447  -0.0249   1.0000   0.0160
 -11.500  -1.1352   0.02033   0.01377  -0.0214   1.0000   0.0175
 -11.000  -1.1237   0.01916   0.01266  -0.0140   1.0000   0.0259
 -10.750  -1.1108   0.01876   0.01228  -0.0114   1.0000   0.0307
 -10.500  -1.0955   0.01844   0.01195  -0.0092   1.0000   0.0343
 -10.250  -1.0802   0.01813   0.01158  -0.0070   1.0000   0.0363
 -10.000  -1.0653   0.01778   0.01124  -0.0048   1.0000   0.0382
  -9.750  -1.0489   0.01751   0.01095  -0.0028   1.0000   0.0402
  -9.500  -1.0324   0.01726   0.01065  -0.0007   1.0000   0.0418
  -9.250  -1.0156   0.01701   0.01035   0.0013   1.0000   0.0430
  -9.000  -0.9986   0.01679   0.01008   0.0033   1.0000   0.0438
  -8.750  -0.9852   0.01637   0.00963   0.0059   1.0000   0.0452
  -8.500  -0.9582   0.01594   0.00919   0.0056   0.9986   0.0472
  -8.250  -0.9272   0.01560   0.00883   0.0046   0.9965   0.0492
  -8.000  -0.8961   0.01527   0.00846   0.0035   0.9943   0.0506
  -7.750  -0.8668   0.01492   0.00807   0.0029   0.9918   0.0518
  -7.500  -0.8366   0.01463   0.00774   0.0022   0.9890   0.0531
  -7.250  -0.8051   0.01438   0.00745   0.0012   0.9864   0.0541
  -7.000  -0.7739   0.01391   0.00695   0.0001   0.9841   0.0559
  -6.750  -0.7468   0.01350   0.00651   0.0000   0.9790   0.0573
  -6.500  -0.7149   0.01311   0.00610  -0.0010   0.9749   0.0587
  -6.250  -0.6849   0.01276   0.00574  -0.0016   0.9695   0.0603
  -6.000  -0.6555   0.01243   0.00539  -0.0021   0.9635   0.0620
  -5.750  -0.6241   0.01213   0.00507  -0.0029   0.9595   0.0638
  -5.500  -0.5987   0.01187   0.00479  -0.0024   0.9521   0.0659
  -5.250  -0.5673   0.01154   0.00448  -0.0033   0.9477   0.0709
  -5.000  -0.5385   0.01122   0.00420  -0.0036   0.9412   0.0782
  -4.750  -0.5076   0.01072   0.00386  -0.0045   0.9354   0.1084
  -4.500  -0.4717   0.01030   0.00359  -0.0065   0.9313   0.1396
  -4.250  -0.4389   0.01001   0.00336  -0.0077   0.9238   0.1581
  -4.000  -0.4017   0.00969   0.00311  -0.0099   0.9174   0.1792
  -3.750  -0.3685   0.00933   0.00289  -0.0113   0.9080   0.2097
  -3.500  -0.3344   0.00901   0.00268  -0.0128   0.8989   0.2429
  -3.250  -0.3044   0.00877   0.00252  -0.0133   0.8875   0.2707
  -3.000  -0.2763   0.00853   0.00236  -0.0134   0.8749   0.3010
  -2.750  -0.2499   0.00830   0.00221  -0.0132   0.8603   0.3307
  -2.500  -0.2250   0.00808   0.00208  -0.0125   0.8434   0.3635
  -2.250  -0.2019   0.00787   0.00196  -0.0115   0.8251   0.4042
  -2.000  -0.1790   0.00771   0.00188  -0.0104   0.8070   0.4439
  -1.750  -0.1558   0.00761   0.00181  -0.0093   0.7888   0.4742
  -1.500  -0.1327   0.00752   0.00174  -0.0082   0.7708   0.4995
  -1.250  -0.1106   0.00742   0.00169  -0.0068   0.7529   0.5288
  -1.000  -0.0887   0.00734   0.00165  -0.0054   0.7342   0.5573
  -0.500  -0.0449   0.00726   0.00160  -0.0026   0.6938   0.6072
   0.000   0.0000   0.00722   0.00159   0.0000   0.6539   0.6536
   0.250   0.0223   0.00724   0.00159   0.0013   0.6313   0.6741
   0.500   0.0448   0.00726   0.00160   0.0026   0.6068   0.6939
   1.000   0.0889   0.00733   0.00165   0.0054   0.5590   0.7343
   1.250   0.1106   0.00742   0.00169   0.0068   0.5285   0.7528
   1.500   0.1328   0.00752   0.00174   0.0082   0.4999   0.7706
   1.750   0.1558   0.00761   0.00181   0.0093   0.4736   0.7886
   2.000   0.1789   0.00771   0.00188   0.0104   0.4425   0.8071
   2.250   0.2019   0.00787   0.00196   0.0115   0.4040   0.8254
   2.500   0.2250   0.00808   0.00208   0.0126   0.3630   0.8435
   2.750   0.2499   0.00830   0.00221   0.0132   0.3307   0.8602
   3.000   0.2764   0.00853   0.00236   0.0134   0.3011   0.8750
   3.250   0.3043   0.00878   0.00252   0.0133   0.2699   0.8875
   3.500   0.3343   0.00902   0.00269   0.0128   0.2417   0.8990
   3.750   0.3685   0.00934   0.00289   0.0113   0.2095   0.9081
   4.000   0.4014   0.00968   0.00311   0.0100   0.1793   0.9173
   4.250   0.4389   0.01001   0.00335   0.0077   0.1588   0.9238
   4.500   0.4718   0.01030   0.00359   0.0065   0.1401   0.9313
   4.750   0.5077   0.01071   0.00386   0.0045   0.1095   0.9354
   5.000   0.5385   0.01122   0.00420   0.0036   0.0784   0.9413
   5.250   0.5674   0.01155   0.00448   0.0033   0.0708   0.9479
   5.500   0.5987   0.01187   0.00479   0.0024   0.0659   0.9521
   5.750   0.6237   0.01212   0.00507   0.0030   0.0640   0.9599
   6.000   0.6556   0.01243   0.00539   0.0020   0.0621   0.9636
   6.250   0.6850   0.01275   0.00573   0.0016   0.0604   0.9694
   6.500   0.7150   0.01310   0.00610   0.0010   0.0590   0.9749
   6.750   0.7469   0.01349   0.00651  -0.0001   0.0573   0.9790
   7.000   0.7741   0.01391   0.00695  -0.0001   0.0560   0.9841
   7.250   0.8053   0.01437   0.00744  -0.0012   0.0541   0.9865
   7.500   0.8368   0.01462   0.00773  -0.0022   0.0532   0.9890
   7.750   0.8668   0.01493   0.00809  -0.0029   0.0519   0.9919
   8.000   0.8963   0.01526   0.00846  -0.0036   0.0506   0.9944
   8.250   0.9275   0.01558   0.00882  -0.0046   0.0491   0.9965
   8.500   0.9583   0.01593   0.00918  -0.0056   0.0473   0.9986
   8.750   0.9852   0.01637   0.00962  -0.0059   0.0451   1.0000
   9.000   0.9987   0.01678   0.01007  -0.0033   0.0438   1.0000
   9.250   1.0156   0.01701   0.01035  -0.0013   0.0431   1.0000
   9.500   1.0324   0.01725   0.01064   0.0007   0.0418   1.0000
   9.750   1.0492   0.01750   0.01093   0.0027   0.0401   1.0000
  10.000   1.0654   0.01778   0.01123   0.0048   0.0381   1.0000
  10.250   1.0803   0.01813   0.01157   0.0070   0.0363   1.0000
  10.500   1.0957   0.01844   0.01194   0.0092   0.0343   1.0000
  10.750   1.1108   0.01876   0.01228   0.0114   0.0309   1.0000
  11.000   1.1239   0.01915   0.01265   0.0139   0.0257   1.0000
  11.250   1.1310   0.01968   0.01312   0.0174   0.0204   1.0000
  11.500   1.1355   0.02032   0.01377   0.0213   0.0175   1.0000
  11.750   1.1410   0.02101   0.01448   0.0249   0.0158   1.0000
  12.000   1.1483   0.02168   0.01521   0.0280   0.0148   1.0000
  12.250   1.1561   0.02239   0.01599   0.0309   0.0140   1.0000
  12.500   1.1637   0.02317   0.01684   0.0336   0.0134   1.0000
  12.750   1.1701   0.02409   0.01783   0.0363   0.0128   1.0000
  13.000   1.1760   0.02510   0.01892   0.0388   0.0122   1.0000
  13.250   1.1813   0.02622   0.02011   0.0411   0.0117   1.0000
  13.500   1.1875   0.02734   0.02135   0.0431   0.0114   1.0000
  13.750   1.1935   0.02855   0.02265   0.0448   0.0111   1.0000
  14.000   1.1981   0.02994   0.02414   0.0465   0.0107   1.0000
  14.250   1.2022   0.03146   0.02576   0.0478   0.0104   1.0000
  14.500   1.2053   0.03317   0.02756   0.0489   0.0102   1.0000
  14.750   1.2056   0.03525   0.02974   0.0498   0.0098   1.0000
  15.000   1.2043   0.03763   0.03223   0.0503   0.0096   1.0000
  15.250   1.2036   0.04011   0.03481   0.0505   0.0095   1.0000
  15.500   1.1978   0.04329   0.03811   0.0502   0.0093   1.0000
  15.750   1.1890   0.04707   0.04202   0.0494   0.0091   1.0000
  16.000   1.1811   0.05099   0.04607   0.0482   0.0090   1.0000
  16.250   1.1710   0.05543   0.05064   0.0465   0.0089   1.0000
  16.500   1.1577   0.06055   0.05591   0.0443   0.0088   1.0000
  16.750   1.1459   0.06568   0.06118   0.0419   0.0088   1.0000
  17.000   1.1274   0.07217   0.06781   0.0386   0.0088   1.0000
  17.250   1.1083   0.07899   0.07480   0.0352   0.0087   1.0000
  17.500   1.0855   0.08664   0.08258   0.0312   0.0087   1.0000
  17.750   1.0560   0.09558   0.09167   0.0267   0.0089   1.0000
  18.000   1.0281   0.10446   0.10069   0.0222   0.0088   1.0000
<< Back to GOE 459 AIRFOIL (goe459-il)

Polar data table (+)

Polar graphs


<< Back to GOE 459 AIRFOIL (goe459-il)