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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 100,000
Max Cl/Cd: 60.95 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802b-il-100000-n5.txt
Download as CSV file: xf-goe802b-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 B 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2547   0.11359   0.10881  -0.0327   1.0000   0.0381
  -9.250  -0.2622   0.11245   0.10775  -0.0307   1.0000   0.0386
  -9.000  -0.2721   0.11157   0.10695  -0.0285   1.0000   0.0390
  -8.750  -0.2580   0.10880   0.10418  -0.0345   0.9934   0.0395
  -8.500  -0.2437   0.10484   0.10023  -0.0379   0.9876   0.0400
  -8.250  -0.2264   0.10076   0.09614  -0.0403   0.9831   0.0411
  -8.000  -0.2101   0.09736   0.09275  -0.0441   0.9767   0.0424
  -7.750  -0.1916   0.09384   0.08922  -0.0490   0.9692   0.0438
  -7.500  -0.1686   0.09025   0.08560  -0.0560   0.9619   0.0451
  -7.250  -0.1426   0.08695   0.08225  -0.0649   0.9531   0.0457
  -7.000  -0.1193   0.08259   0.07786  -0.0692   0.9488   0.0462
  -6.750  -0.1058   0.07937   0.07464  -0.0704   0.9403   0.0472
  -6.500  -0.0825   0.07605   0.07128  -0.0748   0.9337   0.0494
  -6.250  -0.0489   0.07283   0.06795  -0.0833   0.9273   0.0517
  -5.750  -0.0063   0.06613   0.06116  -0.0895   0.9123   0.0529
  -5.500   0.0166   0.06311   0.05808  -0.0923   0.9057   0.0542
  -5.250   0.0399   0.06038   0.05527  -0.0952   0.8970   0.0559
  -5.000   0.0768   0.05758   0.05227  -0.1009   0.8913   0.0578
  -4.750   0.1005   0.05483   0.04942  -0.1032   0.8829   0.0586
  -4.500   0.1219   0.05201   0.04656  -0.1044   0.8755   0.0604
  -4.250   0.1545   0.04940   0.04377  -0.1076   0.8704   0.0629
  -4.000   0.1827   0.04766   0.04181  -0.1095   0.8604   0.0641
  -3.750   0.2141   0.04536   0.03930  -0.1117   0.8538   0.0645
  -3.500   0.2374   0.04266   0.03655  -0.1127   0.8462   0.0654
  -3.250   0.2632   0.04061   0.03437  -0.1136   0.8375   0.0667
  -3.000   0.2952   0.03860   0.03213  -0.1152   0.8315   0.0685
  -2.750   0.3229   0.03747   0.03075  -0.1156   0.8206   0.0699
  -2.500   0.3518   0.03531   0.02844  -0.1166   0.8133   0.0711
  -2.250   0.3774   0.03374   0.02672  -0.1168   0.8026   0.0727
  -2.000   0.4075   0.03226   0.02500  -0.1174   0.7940   0.0738
  -1.750   0.4347   0.03110   0.02362  -0.1174   0.7825   0.0744
  -1.500   0.4648   0.02983   0.02209  -0.1177   0.7734   0.0747
  -1.250   0.4913   0.02876   0.02083  -0.1176   0.7610   0.0746
  -1.000   0.5206   0.02750   0.01934  -0.1178   0.7517   0.0740
  -0.750   0.5487   0.02616   0.01769  -0.1176   0.7394   0.0596
  -0.500   0.5774   0.02542   0.01665  -0.1174   0.7285   0.0578
  -0.250   0.6045   0.02450   0.01562  -0.1173   0.7169   0.0605
   0.000   0.6317   0.02382   0.01475  -0.1171   0.7046   0.0603
   0.250   0.6605   0.02327   0.01388  -0.1168   0.6939   0.0580
   0.500   0.6870   0.02261   0.01309  -0.1165   0.6808   0.0576
   0.750   0.7140   0.02205   0.01237  -0.1163   0.6686   0.0574
   1.000   0.7414   0.02157   0.01169  -0.1160   0.6568   0.0575
   1.250   0.7676   0.02122   0.01121  -0.1156   0.6436   0.0580
   1.500   0.7942   0.02085   0.01077  -0.1154   0.6320   0.0600
   1.750   0.8206   0.02072   0.01052  -0.1150   0.6200   0.0639
   2.000   0.8465   0.02047   0.01022  -0.1146   0.6075   0.0661
   2.250   0.8728   0.02027   0.00989  -0.1142   0.5962   0.0680
   2.500   0.8982   0.02019   0.00975  -0.1138   0.5837   0.0707
   3.250   0.9752   0.02004   0.00932  -0.1126   0.5512   0.1010
   3.750   1.0225   0.01716   0.00811  -0.1118   0.5306   1.0000
   4.000   1.0477   0.01747   0.00827  -0.1114   0.5207   1.0000
   4.250   1.0723   0.01780   0.00856  -0.1110   0.5105   1.0000
   4.500   1.0972   0.01814   0.00881  -0.1106   0.5014   1.0000
   4.750   1.1213   0.01849   0.00914  -0.1101   0.4910   1.0000
   5.000   1.1455   0.01884   0.00938  -0.1096   0.4807   1.0000
   5.250   1.1683   0.01919   0.00974  -0.1089   0.4682   1.0000
   5.500   1.1913   0.01955   0.01004  -0.1082   0.4565   1.0000
   5.750   1.2135   0.01991   0.01037  -0.1074   0.4439   1.0000
   6.000   1.2358   0.02030   0.01076  -0.1066   0.4324   1.0000
   6.250   1.2584   0.02070   0.01111  -0.1059   0.4229   1.0000
   6.500   1.2805   0.02111   0.01160  -0.1052   0.4130   1.0000
   6.750   1.3025   0.02154   0.01199  -0.1044   0.4040   1.0000
   7.000   1.3242   0.02199   0.01251  -0.1036   0.3948   1.0000
   7.250   1.3454   0.02244   0.01297  -0.1028   0.3860   1.0000
   7.500   1.3662   0.02292   0.01352  -0.1019   0.3768   1.0000
   7.750   1.3860   0.02341   0.01404  -0.1008   0.3672   1.0000
   8.000   1.4055   0.02393   0.01462  -0.0997   0.3576   1.0000
   8.250   1.4237   0.02447   0.01517  -0.0984   0.3474   1.0000
   8.500   1.4410   0.02504   0.01585  -0.0970   0.3364   1.0000
   8.750   1.4566   0.02565   0.01642  -0.0954   0.3253   1.0000
   9.000   1.4709   0.02629   0.01718  -0.0936   0.3124   1.0000
   9.250   1.4836   0.02699   0.01791  -0.0916   0.2996   1.0000
   9.500   1.4928   0.02774   0.01865  -0.0890   0.2873   1.0000
   9.750   1.5023   0.02855   0.01959  -0.0866   0.2738   1.0000
  10.000   1.5112   0.02946   0.02056  -0.0843   0.2612   1.0000
  10.250   1.5184   0.03050   0.02162  -0.0819   0.2491   1.0000
  10.500   1.5262   0.03160   0.02280  -0.0798   0.2367   1.0000
  10.750   1.5331   0.03283   0.02407  -0.0777   0.2254   1.0000
  11.000   1.5368   0.03428   0.02553  -0.0754   0.2142   1.0000
  11.250   1.5406   0.03585   0.02716  -0.0734   0.2021   1.0000
  11.500   1.5426   0.03761   0.02894  -0.0714   0.1914   1.0000
  11.750   1.5420   0.03967   0.03096  -0.0694   0.1817   1.0000
  12.000   1.5439   0.04165   0.03303  -0.0678   0.1723   1.0000
  12.250   1.5419   0.04402   0.03540  -0.0662   0.1646   1.0000
  12.500   1.5438   0.04619   0.03768  -0.0649   0.1577   1.0000
  12.750   1.5435   0.04861   0.04018  -0.0637   0.1514   1.0000
  13.000   1.5400   0.05140   0.04300  -0.0626   0.1462   1.0000
  13.250   1.5416   0.05384   0.04564  -0.0618   0.1402   1.0000
  13.500   1.5391   0.05675   0.04867  -0.0611   0.1343   1.0000
  13.750   1.5334   0.06009   0.05205  -0.0606   0.1295   1.0000
  14.000   1.5325   0.06307   0.05521  -0.0603   0.1243   1.0000
  14.250   1.5293   0.06643   0.05871  -0.0602   0.1192   1.0000
  14.500   1.5237   0.07017   0.06255  -0.0603   0.1149   1.0000
  14.750   1.5178   0.07405   0.06652  -0.0606   0.1110   1.0000
  15.000   1.5145   0.07775   0.07042  -0.0610   0.1063   1.0000
  15.250   1.5081   0.08196   0.07479  -0.0617   0.1018   1.0000
  15.500   1.4995   0.08658   0.07949  -0.0626   0.0980   1.0000
  15.750   1.4933   0.09091   0.08397  -0.0635   0.0943   1.0000
  16.000   1.4874   0.09529   0.08854  -0.0645   0.0903   1.0000
  16.250   1.4793   0.10011   0.09348  -0.0658   0.0867   1.0000
  16.500   1.4685   0.10544   0.09889  -0.0676   0.0832   1.0000
  16.750   1.4608   0.11038   0.10399  -0.0692   0.0791   1.0000
  17.000   1.4520   0.11556   0.10931  -0.0710   0.0754   1.0000
  17.250   1.4421   0.12101   0.11485  -0.0731   0.0721   1.0000
  17.500   1.4330   0.12641   0.12035  -0.0754   0.0690   1.0000
  17.750   1.4252   0.13170   0.12579  -0.0777   0.0653   1.0000
  18.000   1.4160   0.13731   0.13150  -0.0803   0.0620   1.0000
  18.250   1.4054   0.14328   0.13752  -0.0833   0.0587   1.0000
  18.500   1.3965   0.14911   0.14350  -0.0863   0.0545   1.0000
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