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GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 612 AIRFOIL (goe612-il)
Reynolds number: 100,000
Max Cl/Cd: 49.26 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe612-il-100000-n5.txt
Download as CSV file: xf-goe612-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 612 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  -0.3513   0.05384   0.04806  -0.1118   0.9375   0.0552
  -9.250  -0.3749   0.04688   0.04058  -0.1164   0.9233   0.0552
  -9.000  -0.3819   0.04258   0.03578  -0.1171   0.9116   0.0555
  -8.750  -0.3727   0.04049   0.03352  -0.1163   0.9019   0.0559
  -8.500  -0.3533   0.03861   0.03149  -0.1168   0.8954   0.0566
  -8.250  -0.3377   0.03710   0.02982  -0.1162   0.8873   0.0575
  -8.000  -0.3203   0.03549   0.02801  -0.1158   0.8797   0.0586
  -7.750  -0.2968   0.03359   0.02580  -0.1165   0.8754   0.0599
  -7.500  -0.2865   0.03220   0.02414  -0.1143   0.8649   0.0608
  -7.250  -0.2626   0.03044   0.02202  -0.1144   0.8600   0.0620
  -7.000  -0.2449   0.02917   0.02046  -0.1130   0.8521   0.0629
  -6.750  -0.2214   0.02817   0.01943  -0.1126   0.8458   0.0639
  -6.500  -0.1929   0.02721   0.01840  -0.1129   0.8419   0.0653
  -6.250  -0.1740   0.02658   0.01768  -0.1116   0.8341   0.0671
  -6.000  -0.1492   0.02576   0.01670  -0.1111   0.8283   0.0694
  -5.750  -0.1201   0.02485   0.01565  -0.1113   0.8245   0.0718
  -5.500  -0.1004   0.02438   0.01519  -0.1100   0.8169   0.0738
  -5.250  -0.0754   0.02378   0.01453  -0.1095   0.8114   0.0764
  -5.000  -0.0464   0.02308   0.01368  -0.1096   0.8077   0.0799
  -4.750  -0.0243   0.02268   0.01332  -0.1086   0.8016   0.0835
  -4.500  -0.0006   0.02228   0.01285  -0.1078   0.7955   0.0890
  -4.250   0.0277   0.02175   0.01230  -0.1078   0.7914   0.0955
  -4.000   0.0552   0.02127   0.01177  -0.1076   0.7873   0.1042
  -3.750   0.0748   0.02105   0.01155  -0.1062   0.7804   0.1140
  -3.500   0.1015   0.02062   0.01113  -0.1060   0.7759   0.1275
  -3.250   0.1319   0.02017   0.01068  -0.1063   0.7725   0.1450
  -3.000   0.1527   0.02004   0.01059  -0.1051   0.7663   0.1614
  -2.750   0.1768   0.01984   0.01046  -0.1044   0.7610   0.1810
  -2.500   0.2056   0.01956   0.01024  -0.1045   0.7571   0.2057
  -2.250   0.2373   0.01926   0.01001  -0.1050   0.7540   0.2365
  -2.000   0.2544   0.01939   0.01023  -0.1032   0.7469   0.2655
  -1.750   0.2810   0.01927   0.01018  -0.1027   0.7416   0.2979
  -1.500   0.3138   0.01900   0.00990  -0.1032   0.7373   0.3269
  -1.250   0.3337   0.01905   0.00998  -0.1016   0.7290   0.3477
  -1.000   0.3630   0.01885   0.00976  -0.1015   0.7223   0.3717
  -0.750   0.3913   0.01870   0.00957  -0.1012   0.7152   0.3948
  -0.500   0.4151   0.01863   0.00950  -0.1001   0.7064   0.4156
  -0.250   0.4493   0.01833   0.00917  -0.1008   0.7006   0.4392
   0.000   0.4678   0.01843   0.00934  -0.0990   0.6917   0.4603
   0.250   0.4969   0.01830   0.00924  -0.0989   0.6858   0.4917
   0.500   0.5246   0.01814   0.00918  -0.0986   0.6801   0.5294
   0.750   0.5452   0.01808   0.00931  -0.0971   0.6723   0.5707
   1.000   0.5737   0.01772   0.00920  -0.0968   0.6665   0.6384
   1.250   0.6619   0.01714   0.00927  -0.1083   0.6582   1.0000
   1.500   0.6852   0.01725   0.00925  -0.1073   0.6506   1.0000
   1.750   0.7096   0.01734   0.00921  -0.1064   0.6435   1.0000
   2.000   0.7288   0.01753   0.00933  -0.1047   0.6345   1.0000
   2.250   0.7550   0.01756   0.00924  -0.1041   0.6270   1.0000
   2.500   0.7722   0.01778   0.00942  -0.1021   0.6169   1.0000
   2.750   0.7966   0.01785   0.00939  -0.1012   0.6084   1.0000
   3.000   0.8149   0.01803   0.00953  -0.0993   0.5977   1.0000
   3.250   0.8351   0.01818   0.00962  -0.0977   0.5870   1.0000
   3.500   0.8581   0.01824   0.00959  -0.0965   0.5762   1.0000
   3.750   0.8741   0.01847   0.00981  -0.0943   0.5631   1.0000
   4.000   0.8923   0.01865   0.00994  -0.0924   0.5499   1.0000
   4.250   0.9107   0.01882   0.01004  -0.0905   0.5358   1.0000
   4.500   0.9282   0.01901   0.01016  -0.0884   0.5205   1.0000
   4.750   0.9447   0.01924   0.01030  -0.0863   0.5039   1.0000
   5.000   0.9606   0.01950   0.01047  -0.0840   0.4865   1.0000
   5.250   0.9752   0.01980   0.01065  -0.0815   0.4692   1.0000
   5.500   0.9892   0.02015   0.01087  -0.0790   0.4521   1.0000
   5.750   1.0033   0.02055   0.01115  -0.0766   0.4359   1.0000
   6.000   1.0179   0.02100   0.01147  -0.0744   0.4213   1.0000
   6.250   1.0323   0.02150   0.01185  -0.0722   0.4077   1.0000
   6.500   1.0470   0.02204   0.01230  -0.0702   0.3950   1.0000
   6.750   1.0626   0.02258   0.01276  -0.0683   0.3840   1.0000
   7.000   1.0780   0.02316   0.01323  -0.0665   0.3733   1.0000
   7.250   1.0933   0.02376   0.01378  -0.0648   0.3634   1.0000
   7.750   1.1244   0.02500   0.01492  -0.0615   0.3454   1.0000
   8.000   1.1412   0.02562   0.01544  -0.0600   0.3376   1.0000
   8.250   1.1561   0.02629   0.01614  -0.0584   0.3297   1.0000
   8.500   1.1719   0.02695   0.01677  -0.0570   0.3224   1.0000
   8.750   1.1879   0.02764   0.01744  -0.0556   0.3155   1.0000
   9.000   1.2024   0.02836   0.01820  -0.0540   0.3085   1.0000
   9.250   1.2195   0.02904   0.01881  -0.0528   0.3025   1.0000
   9.500   1.2332   0.02983   0.01969  -0.0513   0.2961   1.0000
   9.750   1.2472   0.03062   0.02052  -0.0499   0.2899   1.0000
  10.000   1.2641   0.03134   0.02118  -0.0488   0.2845   1.0000
  10.250   1.2750   0.03228   0.02224  -0.0471   0.2781   1.0000
  10.500   1.2869   0.03319   0.02321  -0.0456   0.2721   1.0000
  10.750   1.3011   0.03403   0.02400  -0.0444   0.2666   1.0000
  11.000   1.3100   0.03514   0.02526  -0.0427   0.2603   1.0000
  11.250   1.3204   0.03618   0.02635  -0.0413   0.2546   1.0000
  11.500   1.3330   0.03715   0.02731  -0.0401   0.2496   1.0000
  11.750   1.3411   0.03842   0.02874  -0.0386   0.2437   1.0000
  12.000   1.3505   0.03962   0.02999  -0.0373   0.2386   1.0000
  12.250   1.3625   0.04066   0.03098  -0.0362   0.2341   1.0000
  12.500   1.3689   0.04217   0.03268  -0.0349   0.2287   1.0000
  12.750   1.3763   0.04359   0.03419  -0.0336   0.2236   1.0000
  13.000   1.3859   0.04483   0.03542  -0.0326   0.2194   1.0000
  13.250   1.3917   0.04649   0.03720  -0.0314   0.2146   1.0000
  13.500   1.3967   0.04822   0.03905  -0.0304   0.2098   1.0000
  13.750   1.4039   0.04975   0.04063  -0.0294   0.2058   1.0000
  14.000   1.4131   0.05119   0.04208  -0.0286   0.2022   1.0000
  14.250   1.4156   0.05333   0.04440  -0.0277   0.1982   1.0000
  14.500   1.4204   0.05528   0.04646  -0.0269   0.1945   1.0000
  14.750   1.4270   0.05705   0.04829  -0.0262   0.1914   1.0000
  15.000   1.4388   0.05833   0.04957  -0.0256   0.1886   1.0000
  15.250   1.4384   0.06094   0.05236  -0.0250   0.1855   1.0000
  15.500   1.4367   0.06372   0.05532  -0.0246   0.1823   1.0000
  15.750   1.4382   0.06619   0.05791  -0.0242   0.1793   1.0000
  16.000   1.4433   0.06823   0.06001  -0.0238   0.1765   1.0000
  16.250   1.4562   0.06939   0.06114  -0.0234   0.1738   1.0000
  16.500   1.4428   0.07378   0.06580  -0.0235   0.1712   1.0000
  16.750   1.4312   0.07809   0.07032  -0.0239   0.1684   1.0000
  17.000   1.4236   0.08197   0.07436  -0.0243   0.1656   1.0000
  17.250   1.4256   0.08453   0.07696  -0.0245   0.1625   1.0000
  17.500   1.4366   0.08586   0.07826  -0.0243   0.1595   1.0000
  17.750   1.4035   0.09369   0.08641  -0.0265   0.1571   1.0000
  18.000   1.3620   0.10338   0.09640  -0.0298   0.1550   1.0000
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