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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 100,000
Max Cl/Cd: 52.84 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe613-il-100000-n5.txt
Download as CSV file: xf-goe613-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3529   0.09821   0.09369  -0.0329   1.0000   0.0560
  -8.000  -0.3737   0.09708   0.09267  -0.0315   1.0000   0.0564
  -7.750  -0.3931   0.09566   0.09135  -0.0298   1.0000   0.0566
  -7.500  -0.3869   0.09079   0.08645  -0.0393   0.9942   0.0570
  -7.250  -0.3700   0.08515   0.08068  -0.0475   0.9871   0.0572
  -7.000  -0.3582   0.08003   0.07565  -0.0465   0.9843   0.0582
  -6.750  -0.3433   0.07728   0.07293  -0.0448   0.9804   0.0602
  -6.500  -0.3229   0.07372   0.06930  -0.0486   0.9755   0.0646
  -6.000  -0.2880   0.06348   0.05874  -0.0612   0.9594   0.0723
  -5.750  -0.2644   0.05702   0.05201  -0.0650   0.9533   0.0544
  -5.500  -0.2429   0.05253   0.04724  -0.0680   0.9461   0.0549
  -5.250  -0.2181   0.04824   0.04267  -0.0707   0.9396   0.0544
  -5.000  -0.1930   0.04429   0.03842  -0.0727   0.9329   0.0528
  -4.500  -0.1314   0.03722   0.03048  -0.0769   0.9213   0.0541
  -4.250  -0.1104   0.03475   0.02763  -0.0763   0.9121   0.0541
  -4.000  -0.0781   0.03211   0.02457  -0.0777   0.9082   0.0538
  -3.750  -0.0530   0.03018   0.02228  -0.0775   0.9016   0.0537
  -3.500  -0.0237   0.02839   0.02012  -0.0779   0.8960   0.0539
  -3.250   0.0121   0.02692   0.01820  -0.0793   0.8926   0.0558
  -3.000   0.0371   0.02597   0.01693  -0.0785   0.8850   0.0569
  -2.750   0.0703   0.02469   0.01537  -0.0794   0.8801   0.0570
  -2.250   0.1308   0.02242   0.01278  -0.0800   0.8676   0.0579
  -2.000   0.1668   0.02128   0.01156  -0.0813   0.8630   0.0588
  -1.750   0.1927   0.02052   0.01077  -0.0807   0.8532   0.0599
  -1.500   0.2289   0.01961   0.00983  -0.0819   0.8461   0.0616
  -1.250   0.2562   0.01903   0.00924  -0.0814   0.8347   0.0652
  -1.000   0.2828   0.01850   0.00867  -0.0808   0.8231   0.0685
  -0.750   0.3112   0.01797   0.00808  -0.0805   0.8126   0.0701
  -0.500   0.3425   0.01735   0.00744  -0.0808   0.8032   0.0730
  -0.250   0.3685   0.01699   0.00704  -0.0801   0.7905   0.0768
   0.000   0.3963   0.01668   0.00665  -0.0797   0.7778   0.0827
   0.250   0.4256   0.01631   0.00629  -0.0796   0.7646   0.0962
   0.750   0.5387   0.01365   0.00585  -0.0907   0.7356   1.0000
   1.000   0.5650   0.01366   0.00568  -0.0901   0.7183   1.0000
   1.250   0.5908   0.01370   0.00554  -0.0893   0.6999   1.0000
   1.500   0.6144   0.01379   0.00548  -0.0882   0.6798   1.0000
   1.750   0.6373   0.01390   0.00545  -0.0870   0.6579   1.0000
   2.000   0.6605   0.01403   0.00543  -0.0859   0.6351   1.0000
   2.250   0.6833   0.01418   0.00543  -0.0846   0.6104   1.0000
   2.500   0.7062   0.01436   0.00543  -0.0835   0.5861   1.0000
   2.750   0.7292   0.01458   0.00546  -0.0823   0.5634   1.0000
   3.000   0.7514   0.01485   0.00557  -0.0811   0.5417   1.0000
   3.250   0.7737   0.01516   0.00571  -0.0799   0.5221   1.0000
   3.500   0.7959   0.01549   0.00590  -0.0788   0.5042   1.0000
   3.750   0.8178   0.01582   0.00614  -0.0776   0.4869   1.0000
   4.000   0.8395   0.01616   0.00640  -0.0765   0.4700   1.0000
   4.250   0.8610   0.01650   0.00667  -0.0753   0.4539   1.0000
   4.500   0.8826   0.01685   0.00696  -0.0741   0.4388   1.0000
   4.750   0.9043   0.01721   0.00728  -0.0730   0.4252   1.0000
   5.250   0.9474   0.01796   0.00796  -0.0708   0.3997   1.0000
   5.500   0.9690   0.01834   0.00835  -0.0697   0.3880   1.0000
   5.750   0.9908   0.01875   0.00874  -0.0687   0.3780   1.0000
   6.000   1.0125   0.01919   0.00915  -0.0677   0.3688   1.0000
   6.250   1.0342   0.01961   0.00962  -0.0667   0.3593   1.0000
   6.500   1.0559   0.02008   0.01008  -0.0657   0.3511   1.0000
   6.750   1.0773   0.02053   0.01060  -0.0647   0.3421   1.0000
   7.000   1.0983   0.02100   0.01111  -0.0636   0.3336   1.0000
   7.250   1.1177   0.02148   0.01159  -0.0623   0.3236   1.0000
   7.500   1.1337   0.02191   0.01207  -0.0604   0.3094   1.0000
   7.750   1.1475   0.02236   0.01250  -0.0581   0.2936   1.0000
   8.000   1.1633   0.02281   0.01303  -0.0563   0.2806   1.0000
   8.250   1.1790   0.02328   0.01358  -0.0544   0.2683   1.0000
   8.500   1.1938   0.02377   0.01414  -0.0524   0.2565   1.0000
   8.750   1.2065   0.02428   0.01474  -0.0500   0.2442   1.0000
   9.000   1.2164   0.02483   0.01533  -0.0473   0.2262   1.0000
   9.250   1.2275   0.02546   0.01600  -0.0449   0.2094   1.0000
   9.500   1.2392   0.02615   0.01674  -0.0426   0.1933   1.0000
   9.750   1.2476   0.02704   0.01759  -0.0401   0.1660   1.0000
  10.000   1.2504   0.02835   0.01869  -0.0371   0.1304   1.0000
  10.250   1.2473   0.03027   0.02030  -0.0338   0.0871   1.0000
  10.500   1.2296   0.03346   0.02297  -0.0296   0.0344   1.0000
  10.750   1.2274   0.03554   0.02510  -0.0270   0.0285   1.0000
  11.000   1.2276   0.03749   0.02717  -0.0248   0.0264   1.0000
  11.250   1.2284   0.03946   0.02929  -0.0229   0.0253   1.0000
  11.500   1.2280   0.04163   0.03165  -0.0212   0.0244   1.0000
  11.750   1.2248   0.04416   0.03437  -0.0198   0.0235   1.0000
  12.000   1.2200   0.04699   0.03738  -0.0186   0.0228   1.0000
  12.250   1.2125   0.05028   0.04086  -0.0179   0.0221   1.0000
  12.500   1.2034   0.05397   0.04474  -0.0176   0.0216   1.0000
  12.750   1.1923   0.05819   0.04914  -0.0178   0.0213   1.0000
  13.000   1.1768   0.06331   0.05444  -0.0188   0.0207   1.0000
  13.250   1.1647   0.06836   0.05969  -0.0201   0.0206   1.0000
  13.500   1.1484   0.07437   0.06588  -0.0221   0.0204   1.0000
  13.750   1.1354   0.08010   0.07178  -0.0242   0.0203   1.0000
  14.000   1.1221   0.08605   0.07788  -0.0264   0.0202   1.0000
  14.250   1.1114   0.09168   0.08365  -0.0285   0.0199   1.0000
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