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GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 546 AIRFOIL (goe546-il)
Reynolds number: 50,000
Max Cl/Cd: 38.44 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe546-il-50000.txt
Download as CSV file: xf-goe546-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 546 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3800   0.11905   0.11173  -0.0294   1.0000   0.2292
  -9.500  -0.3570   0.11350   0.10616  -0.0279   1.0000   0.2385
  -9.250  -0.3848   0.11453   0.10737  -0.0288   1.0000   0.2451
  -9.000  -0.3560   0.10857   0.10136  -0.0270   1.0000   0.2569
  -8.750  -0.3533   0.10562   0.09847  -0.0263   1.0000   0.2658
  -8.500  -0.3729   0.10558   0.09860  -0.0258   1.0000   0.2757
  -8.250  -0.3590   0.10173   0.09476  -0.0242   1.0000   0.2901
  -8.000  -0.3491   0.09827   0.09134  -0.0227   1.0000   0.3023
  -7.750  -0.3514   0.09589   0.08905  -0.0212   1.0000   0.3128
  -7.500  -0.3796   0.09641   0.08979  -0.0186   1.0000   0.3232
  -7.250  -0.3641   0.09250   0.08588  -0.0169   1.0000   0.3372
  -7.000  -0.3576   0.08945   0.08288  -0.0148   1.0000   0.3492
  -6.750  -0.3629   0.08745   0.08098  -0.0120   1.0000   0.3617
  -6.500  -0.4052   0.08869   0.08245  -0.0065   1.0000   0.3705
  -6.250  -0.4049   0.08628   0.08011  -0.0034   1.0000   0.3858
  -6.000  -0.4117   0.08443   0.07836   0.0001   1.0000   0.4017
  -5.750  -0.4244   0.08304   0.07707   0.0036   1.0000   0.4182
  -5.250  -0.4094   0.07709   0.07119   0.0098   1.0000   0.4546
  -4.250  -0.3730   0.04229   0.03411  -0.0449   1.0000   0.1647
  -4.000  -0.3494   0.03898   0.03032  -0.0458   1.0000   0.1603
  -3.750  -0.3258   0.03651   0.02737  -0.0462   1.0000   0.1607
  -3.500  -0.3019   0.03438   0.02478  -0.0463   1.0000   0.1612
  -3.250  -0.2779   0.03257   0.02255  -0.0461   1.0000   0.1613
  -3.000  -0.2547   0.03116   0.02074  -0.0457   1.0000   0.1639
  -2.750  -0.2319   0.03005   0.01926  -0.0451   1.0000   0.1694
  -2.500  -0.2108   0.02904   0.01825  -0.0444   1.0000   0.1760
  -2.250  -0.1879   0.02825   0.01720  -0.0437   1.0000   0.1827
  -2.000  -0.1674   0.02753   0.01652  -0.0427   1.0000   0.1934
  -1.750  -0.1456   0.02702   0.01600  -0.0420   1.0000   0.2107
  -1.500  -0.1220   0.02647   0.01557  -0.0417   1.0000   0.2368
  -1.250  -0.0960   0.02544   0.01532  -0.0417   1.0000   0.3409
  -1.000  -0.0811   0.02287   0.01515  -0.0369   1.0000   1.0000
  -0.750  -0.0594   0.02338   0.01511  -0.0370   1.0000   1.0000
  -0.500  -0.0391   0.02394   0.01528  -0.0370   1.0000   1.0000
  -0.250  -0.0193   0.02454   0.01556  -0.0369   1.0000   1.0000
   0.000  -0.0001   0.02518   0.01591  -0.0368   1.0000   1.0000
   0.250   0.0188   0.02586   0.01636  -0.0367   1.0000   1.0000
   0.500   0.0561   0.02704   0.01728  -0.0400   0.9920   1.0000
   0.750   0.0992   0.02833   0.01832  -0.0444   0.9798   1.0000
   1.000   0.1396   0.02952   0.01932  -0.0481   0.9674   1.0000
   1.250   0.1786   0.03066   0.02030  -0.0516   0.9550   1.0000
   1.500   0.2173   0.03180   0.02131  -0.0548   0.9427   1.0000
   1.750   0.2569   0.03294   0.02235  -0.0581   0.9307   1.0000
   2.000   0.2883   0.03389   0.02323  -0.0600   0.9174   1.0000
   2.250   0.3181   0.03487   0.02416  -0.0615   0.9044   1.0000
   2.500   0.3491   0.03588   0.02514  -0.0632   0.8912   1.0000
   2.750   0.3806   0.03692   0.02617  -0.0649   0.8780   1.0000
   3.000   0.4135   0.03796   0.02721  -0.0667   0.8646   1.0000
   3.250   0.4476   0.03895   0.02822  -0.0685   0.8506   1.0000
   3.500   0.4819   0.03987   0.02918  -0.0702   0.8361   1.0000
   3.750   0.5126   0.04068   0.03004  -0.0712   0.8197   1.0000
   4.000   0.5423   0.04141   0.03083  -0.0718   0.8023   1.0000
   4.250   0.5734   0.04208   0.03160  -0.0725   0.7851   1.0000
   4.500   0.6050   0.04272   0.03234  -0.0731   0.7682   1.0000
   4.750   0.6363   0.04335   0.03308  -0.0736   0.7519   1.0000
   5.000   0.6680   0.04392   0.03380  -0.0741   0.7357   1.0000
   5.250   0.7010   0.04436   0.03439  -0.0745   0.7193   1.0000
   5.500   0.7355   0.04468   0.03488  -0.0748   0.7030   1.0000
   5.750   0.7744   0.04464   0.03507  -0.0753   0.6865   1.0000
   6.000   0.8173   0.04420   0.03489  -0.0758   0.6703   1.0000
   6.250   0.8408   0.04470   0.03557  -0.0745   0.6509   1.0000
   6.500   0.8717   0.04460   0.03573  -0.0735   0.6312   1.0000
   6.750   1.0212   0.03269   0.02438  -0.0756   0.5900   1.0000
   7.000   1.0628   0.02954   0.02125  -0.0725   0.5455   1.0000
   7.250   1.0762   0.02888   0.02067  -0.0681   0.5046   1.0000
   7.500   1.0886   0.02832   0.02007  -0.0635   0.4570   1.0000
   7.750   1.0888   0.02850   0.01996  -0.0574   0.3895   1.0000
   8.000   1.0741   0.03008   0.02074  -0.0502   0.2964   1.0000
   8.250   1.0651   0.03290   0.02254  -0.0448   0.2263   1.0000
   8.500   1.0788   0.03535   0.02460  -0.0427   0.1864   1.0000
   8.750   1.1125   0.03766   0.02678  -0.0431   0.1633   1.0000
   9.000   1.1504   0.04004   0.02912  -0.0440   0.1493   1.0000
   9.250   1.1845   0.04255   0.03160  -0.0448   0.1387   1.0000
   9.500   1.2131   0.04538   0.03475  -0.0447   0.1328   1.0000
   9.750   1.2460   0.04880   0.03815  -0.0456   0.1272   1.0000
  10.000   1.2532   0.05166   0.04160  -0.0429   0.1241   1.0000
  10.250   1.2605   0.05491   0.04530  -0.0406   0.1215   1.0000
  10.500   1.2645   0.05858   0.04940  -0.0382   0.1205   1.0000
  10.750   1.2619   0.06232   0.05353  -0.0355   0.1199   1.0000
  11.000   1.2532   0.06607   0.05765  -0.0324   0.1194   1.0000
  11.250   1.2365   0.06984   0.06175  -0.0289   0.1194   1.0000
  11.500   1.2120   0.07378   0.06597  -0.0255   0.1201   1.0000
  11.750   1.1825   0.07834   0.07079  -0.0231   0.1213   1.0000
  12.000   1.1504   0.08373   0.07639  -0.0223   0.1229   1.0000
  12.250   1.1184   0.09001   0.08282  -0.0229   0.1246   1.0000
  12.500   1.0924   0.09686   0.08977  -0.0248   0.1261   1.0000
  12.750   1.0734   0.10401   0.09698  -0.0270   0.1272   1.0000
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