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GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 547 AIRFOIL (goe547-il)
Reynolds number: 100,000
Max Cl/Cd: 59.54 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe547-il-100000-n5.txt
Download as CSV file: xf-goe547-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 547 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3878   0.09959   0.09466  -0.0419   1.0000   0.0464
  -9.000  -0.4036   0.09588   0.09105  -0.0415   1.0000   0.0450
  -8.500  -0.4557   0.08603   0.08140  -0.0440   0.9982   0.0428
  -8.250  -0.4249   0.08743   0.08277  -0.0413   0.9964   0.0462
  -8.000  -0.4186   0.08255   0.07790  -0.0469   0.9895   0.0471
  -7.750  -0.4127   0.07582   0.07116  -0.0553   0.9808   0.0468
  -7.500  -0.4070   0.06552   0.06076  -0.0680   0.9707   0.0460
  -7.250  -0.4053   0.05314   0.04795  -0.0802   0.9607   0.0453
  -7.000  -0.3899   0.04817   0.04264  -0.0842   0.9538   0.0464
  -6.750  -0.3733   0.04385   0.03792  -0.0869   0.9472   0.0481
  -6.500  -0.3544   0.03956   0.03309  -0.0891   0.9410   0.0491
  -6.250  -0.3277   0.03567   0.02858  -0.0916   0.9374   0.0499
  -6.000  -0.3104   0.03319   0.02563  -0.0910   0.9300   0.0504
  -5.750  -0.2823   0.03094   0.02279  -0.0922   0.9257   0.0522
  -5.500  -0.2503   0.02902   0.02040  -0.0937   0.9229   0.0537
  -5.250  -0.2298   0.02766   0.01886  -0.0928   0.9160   0.0545
  -5.000  -0.2000   0.02633   0.01732  -0.0936   0.9119   0.0555
  -4.750  -0.1667   0.02512   0.01592  -0.0949   0.9091   0.0566
  -4.500  -0.1407   0.02421   0.01485  -0.0948   0.9037   0.0579
  -4.250  -0.1129   0.02335   0.01385  -0.0949   0.8986   0.0594
  -4.000  -0.0796   0.02251   0.01285  -0.0959   0.8953   0.0618
  -3.750  -0.0440   0.02175   0.01195  -0.0975   0.8930   0.0654
  -3.500  -0.0240   0.02123   0.01146  -0.0962   0.8852   0.0679
  -3.250   0.0078   0.02056   0.01074  -0.0970   0.8814   0.0714
  -3.000   0.0432   0.01995   0.01002  -0.0984   0.8787   0.0761
  -2.750   0.0647   0.01947   0.00954  -0.0973   0.8713   0.0818
  -2.500   0.0957   0.01891   0.00894  -0.0980   0.8669   0.0934
  -2.250   0.1299   0.01825   0.00840  -0.0994   0.8639   0.1177
  -2.000   0.1520   0.01780   0.00831  -0.0986   0.8568   0.1960
  -1.750   0.1818   0.01729   0.00816  -0.0992   0.8520   0.2945
  -1.500   0.2155   0.01676   0.00807  -0.1004   0.8489   0.4106
  -1.250   0.2367   0.01664   0.00816  -0.0991   0.8413   0.4875
  -1.000   0.2670   0.01638   0.00805  -0.0994   0.8366   0.5544
  -0.750   0.3009   0.01603   0.00787  -0.1003   0.8334   0.6262
  -0.500   0.3204   0.01588   0.00795  -0.0984   0.8254   0.7011
  -0.250   0.3960   0.01531   0.00781  -0.1077   0.8248   1.0000
   0.000   0.4285   0.01529   0.00764  -0.1086   0.8202   1.0000
   0.250   0.4529   0.01542   0.00766  -0.1079   0.8133   1.0000
   0.500   0.4805   0.01549   0.00763  -0.1079   0.8071   1.0000
   0.750   0.5150   0.01546   0.00750  -0.1090   0.8033   1.0000
   1.000   0.5332   0.01571   0.00770  -0.1072   0.7944   1.0000
   1.250   0.5652   0.01572   0.00763  -0.1080   0.7897   1.0000
   1.500   0.5871   0.01592   0.00781  -0.1068   0.7821   1.0000
   1.750   0.6158   0.01599   0.00784  -0.1069   0.7763   1.0000
   2.000   0.6431   0.01610   0.00792  -0.1067   0.7703   1.0000
   2.250   0.6674   0.01624   0.00806  -0.1060   0.7626   1.0000
   2.500   0.6946   0.01623   0.00803  -0.1056   0.7537   1.0000
   2.750   0.7271   0.01599   0.00776  -0.1059   0.7430   1.0000
   3.000   0.7512   0.01595   0.00770  -0.1047   0.7297   1.0000
   3.250   0.7734   0.01603   0.00780  -0.1034   0.7180   1.0000
   3.500   0.7988   0.01612   0.00791  -0.1027   0.7087   1.0000
   3.750   0.8275   0.01613   0.00794  -0.1026   0.6997   1.0000
   4.000   0.8497   0.01626   0.00811  -0.1013   0.6877   1.0000
   4.250   0.8736   0.01636   0.00826  -0.1003   0.6758   1.0000
   4.500   0.8988   0.01644   0.00838  -0.0995   0.6639   1.0000
   4.750   0.9244   0.01653   0.00850  -0.0988   0.6516   1.0000
   5.000   0.9488   0.01664   0.00865  -0.0979   0.6379   1.0000
   5.250   0.9711   0.01679   0.00886  -0.0966   0.6220   1.0000
   5.500   0.9927   0.01697   0.00910  -0.0952   0.6056   1.0000
   5.750   1.0139   0.01718   0.00939  -0.0937   0.5894   1.0000
   6.000   1.0332   0.01740   0.00966  -0.0918   0.5684   1.0000
   6.250   1.0497   0.01763   0.00992  -0.0894   0.5400   1.0000
   6.500   1.0651   0.01792   0.01015  -0.0868   0.5047   1.0000
   6.750   1.0784   0.01832   0.01041  -0.0839   0.4606   1.0000
   7.000   1.0893   0.01890   0.01077  -0.0806   0.4146   1.0000
   7.250   1.0982   0.01959   0.01128  -0.0772   0.3753   1.0000
   7.750   1.1115   0.02132   0.01268  -0.0700   0.3044   1.0000
   8.000   1.1164   0.02236   0.01352  -0.0665   0.2679   1.0000
   8.250   1.1218   0.02343   0.01441  -0.0632   0.2312   1.0000
   8.500   1.1282   0.02452   0.01535  -0.0602   0.1936   1.0000
   8.750   1.1349   0.02567   0.01634  -0.0575   0.1555   1.0000
   9.000   1.1384   0.02712   0.01751  -0.0545   0.1254   1.0000
   9.250   1.1438   0.02854   0.01883  -0.0519   0.1053   1.0000
   9.500   1.1539   0.02971   0.02005  -0.0498   0.0824   1.0000
   9.750   1.1597   0.03123   0.02142  -0.0475   0.0615   1.0000
  10.000   1.1636   0.03294   0.02307  -0.0450   0.0492   1.0000
  10.250   1.1662   0.03479   0.02493  -0.0425   0.0422   1.0000
  10.500   1.1711   0.03648   0.02675  -0.0403   0.0373   1.0000
  10.750   1.1741   0.03837   0.02867  -0.0382   0.0339   1.0000
  11.000   1.1795   0.04010   0.03054  -0.0364   0.0308   1.0000
  11.250   1.1839   0.04194   0.03251  -0.0347   0.0288   1.0000
  11.500   1.1854   0.04411   0.03475  -0.0330   0.0276   1.0000
  11.750   1.1886   0.04622   0.03701  -0.0314   0.0266   1.0000
  12.000   1.1920   0.04842   0.03937  -0.0298   0.0255   1.0000
  12.250   1.1961   0.05061   0.04171  -0.0285   0.0246   1.0000
  12.500   1.1999   0.05288   0.04410  -0.0274   0.0236   1.0000
  12.750   1.2034   0.05521   0.04654  -0.0264   0.0227   1.0000
  13.000   1.2047   0.05779   0.04919  -0.0256   0.0217   1.0000
  13.250   1.2074   0.06047   0.05196  -0.0247   0.0210   1.0000
  13.500   1.2119   0.06309   0.05480  -0.0239   0.0205   1.0000
  13.750   1.2155   0.06593   0.05786  -0.0231   0.0201   1.0000
  14.000   1.2174   0.06903   0.06122  -0.0225   0.0197   1.0000
  14.250   1.2168   0.07250   0.06493  -0.0222   0.0194   1.0000
  14.500   1.2136   0.07629   0.06897  -0.0221   0.0192   1.0000
  14.750   1.2077   0.08050   0.07344  -0.0224   0.0190   1.0000
  15.000   1.1991   0.08520   0.07838  -0.0232   0.0188   1.0000
  15.250   1.1884   0.09030   0.08374  -0.0244   0.0187   1.0000
  15.500   1.1750   0.09601   0.08970  -0.0263   0.0186   1.0000
  15.750   1.1599   0.10231   0.09624  -0.0289   0.0186   1.0000
  16.000   1.1427   0.10932   0.10350  -0.0323   0.0186   1.0000
  16.250   1.1232   0.11730   0.11171  -0.0367   0.0187   1.0000
  16.500   1.1011   0.12652   0.12115  -0.0423   0.0189   1.0000
  16.750   1.0766   0.13719   0.13203  -0.0491   0.0192   1.0000
  17.000   1.0470   0.15050   0.14546  -0.0577   0.0196   1.0000
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