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GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 546 AIRFOIL (goe546-il)
Reynolds number: 100,000
Max Cl/Cd: 58.58 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe546-il-100000-n5.txt
Download as CSV file: xf-goe546-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4737   0.07369   0.06902  -0.0465   1.0000   0.0369
  -8.000  -0.4907   0.06865   0.06400  -0.0482   1.0000   0.0368
  -7.500  -0.4694   0.06124   0.05648  -0.0551   0.9918   0.0390
  -7.250  -0.4523   0.05458   0.04954  -0.0626   0.9849   0.0401
  -7.000  -0.4368   0.04765   0.04215  -0.0684   0.9773   0.0405
  -6.750  -0.4176   0.04252   0.03652  -0.0719   0.9708   0.0418
  -6.500  -0.3931   0.03800   0.03133  -0.0750   0.9653   0.0444
  -6.250  -0.3697   0.03436   0.02694  -0.0763   0.9592   0.0458
  -6.000  -0.3429   0.03158   0.02372  -0.0777   0.9543   0.0472
  -5.750  -0.3109   0.03015   0.02218  -0.0796   0.9511   0.0497
  -5.500  -0.2866   0.02865   0.02041  -0.0796   0.9445   0.0516
  -5.250  -0.2554   0.02689   0.01825  -0.0807   0.9402   0.0532
  -5.000  -0.2206   0.02551   0.01648  -0.0823   0.9372   0.0558
  -4.750  -0.1950   0.02444   0.01513  -0.0820   0.9305   0.0578
  -4.500  -0.1635   0.02311   0.01374  -0.0830   0.9262   0.0596
  -4.250  -0.1284   0.02209   0.01264  -0.0845   0.9231   0.0616
  -4.000  -0.1004   0.02136   0.01183  -0.0846   0.9172   0.0643
  -3.750  -0.0687   0.02071   0.01107  -0.0854   0.9120   0.0683
  -3.500  -0.0335   0.01990   0.01020  -0.0868   0.9086   0.0713
  -3.250  -0.0036   0.01923   0.00956  -0.0873   0.9032   0.0748
  -3.000   0.0260   0.01872   0.00900  -0.0877   0.8969   0.0797
  -2.750   0.0610   0.01814   0.00839  -0.0891   0.8928   0.0880
  -2.500   0.0886   0.01772   0.00797  -0.0891   0.8856   0.1010
  -2.250   0.1202   0.01710   0.00747  -0.0898   0.8797   0.1298
  -2.000   0.1541   0.01597   0.00715  -0.0915   0.8757   0.3114
  -1.750   0.1768   0.01561   0.00718  -0.0905   0.8660   0.4295
  -1.500   0.2104   0.01520   0.00702  -0.0912   0.8609   0.5253
  -1.250   0.2323   0.01487   0.00704  -0.0896   0.8509   0.6202
  -1.000   0.2615   0.01425   0.00692  -0.0887   0.8454   0.7541
  -0.750   0.3071   0.01389   0.00681  -0.0914   0.8378   0.9135
  -0.500   0.3590   0.01374   0.00651  -0.0963   0.8319   1.0000
  -0.250   0.3845   0.01379   0.00641  -0.0957   0.8220   1.0000
   0.000   0.4160   0.01375   0.00623  -0.0963   0.8146   1.0000
   0.250   0.4395   0.01384   0.00623  -0.0954   0.8037   1.0000
   0.500   0.4677   0.01387   0.00615  -0.0953   0.7950   1.0000
   0.750   0.4950   0.01391   0.00611  -0.0950   0.7854   1.0000
   1.000   0.5201   0.01400   0.00614  -0.0944   0.7751   1.0000
   1.250   0.5493   0.01401   0.00608  -0.0944   0.7665   1.0000
   1.500   0.5745   0.01411   0.00613  -0.0937   0.7558   1.0000
   1.750   0.6003   0.01421   0.00620  -0.0932   0.7453   1.0000
   2.000   0.6289   0.01425   0.00619  -0.0931   0.7362   1.0000
   2.250   0.6546   0.01434   0.00627  -0.0925   0.7247   1.0000
   2.500   0.6803   0.01442   0.00633  -0.0918   0.7119   1.0000
   2.750   0.7065   0.01448   0.00635  -0.0912   0.6977   1.0000
   3.000   0.7327   0.01453   0.00635  -0.0905   0.6819   1.0000
   3.250   0.7588   0.01462   0.00641  -0.0899   0.6665   1.0000
   3.500   0.7847   0.01477   0.00654  -0.0893   0.6532   1.0000
   3.750   0.8109   0.01494   0.00671  -0.0888   0.6409   1.0000
   4.000   0.8373   0.01513   0.00690  -0.0883   0.6287   1.0000
   4.250   0.8627   0.01533   0.00710  -0.0876   0.6147   1.0000
   4.500   0.8861   0.01555   0.00733  -0.0866   0.5969   1.0000
   4.750   0.9086   0.01579   0.00759  -0.0854   0.5768   1.0000
   5.000   0.9306   0.01602   0.00779  -0.0840   0.5541   1.0000
   5.250   0.9507   0.01627   0.00804  -0.0823   0.5271   1.0000
   5.500   0.9701   0.01656   0.00828  -0.0805   0.4959   1.0000
   5.750   0.9887   0.01693   0.00852  -0.0787   0.4617   1.0000
   6.000   1.0064   0.01738   0.00884  -0.0767   0.4257   1.0000
   6.250   1.0215   0.01798   0.00924  -0.0744   0.3812   1.0000
   6.500   1.0358   0.01867   0.00973  -0.0721   0.3329   1.0000
   6.750   1.0490   0.01947   0.01032  -0.0698   0.2863   1.0000
   7.000   1.0611   0.02038   0.01101  -0.0673   0.2459   1.0000
   7.250   1.0730   0.02135   0.01180  -0.0649   0.2062   1.0000
   7.500   1.0833   0.02246   0.01268  -0.0624   0.1536   1.0000
   7.750   1.0891   0.02384   0.01372  -0.0594   0.1110   1.0000
   8.000   1.0960   0.02511   0.01486  -0.0564   0.0916   1.0000
   8.250   1.1048   0.02625   0.01598  -0.0537   0.0800   1.0000
   8.500   1.1145   0.02734   0.01711  -0.0512   0.0727   1.0000
   8.750   1.1237   0.02846   0.01828  -0.0488   0.0678   1.0000
   9.000   1.1309   0.02973   0.01958  -0.0463   0.0648   1.0000
   9.250   1.1404   0.03089   0.02087  -0.0441   0.0623   1.0000
   9.500   1.1492   0.03214   0.02225  -0.0419   0.0599   1.0000
   9.750   1.1577   0.03345   0.02364  -0.0399   0.0576   1.0000
  10.000   1.1647   0.03493   0.02515  -0.0380   0.0554   1.0000
  10.250   1.1733   0.03642   0.02671  -0.0362   0.0535   1.0000
  10.500   1.1839   0.03787   0.02830  -0.0346   0.0520   1.0000
  10.750   1.1947   0.03936   0.02991  -0.0331   0.0501   1.0000
  11.000   1.2049   0.04091   0.03156  -0.0318   0.0481   1.0000
  11.250   1.2150   0.04255   0.03324  -0.0305   0.0464   1.0000
  11.500   1.2286   0.04442   0.03509  -0.0294   0.0448   1.0000
  11.750   1.2408   0.04616   0.03707  -0.0282   0.0433   1.0000
  12.000   1.2512   0.04805   0.03918  -0.0271   0.0415   1.0000
  12.250   1.2600   0.05005   0.04134  -0.0260   0.0398   1.0000
  12.500   1.2689   0.05214   0.04359  -0.0249   0.0385   1.0000
  12.750   1.2773   0.05437   0.04587  -0.0241   0.0371   1.0000
  13.000   1.2862   0.05718   0.04880  -0.0233   0.0356   1.0000
  13.250   1.2838   0.06005   0.05200  -0.0222   0.0348   1.0000
  13.500   1.2804   0.06328   0.05555  -0.0213   0.0339   1.0000
  13.750   1.2748   0.06685   0.05941  -0.0207   0.0331   1.0000
  14.000   1.2668   0.07068   0.06351  -0.0205   0.0324   1.0000
  14.250   1.2574   0.07473   0.06780  -0.0207   0.0317   1.0000
  14.500   1.2465   0.07911   0.07241  -0.0213   0.0311   1.0000
  14.750   1.2335   0.08390   0.07743  -0.0225   0.0307   1.0000
  15.000   1.2198   0.08902   0.08275  -0.0241   0.0302   1.0000
  15.250   1.2040   0.09476   0.08871  -0.0264   0.0299   1.0000
  15.500   1.1866   0.10112   0.09527  -0.0294   0.0296   1.0000
  15.750   1.1644   0.10888   0.10326  -0.0336   0.0296   1.0000
  16.000   1.1310   0.11980   0.11448  -0.0404   0.0301   1.0000
  16.250   1.0461   0.14686   0.14190  -0.0588   0.0328   1.0000
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