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FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-147 AIRFOIL (fx63147-il)
Reynolds number: 50,000
Max Cl/Cd: 27.46 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63147-il-50000-n5.txt
Download as CSV file: xf-fx63147-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-147 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3606   0.10410   0.09727  -0.0491   1.0001   0.0384
  -9.750  -0.3674   0.09944   0.09271  -0.0506   1.0001   0.0373
  -9.500  -0.3969   0.08962   0.08295  -0.0577   1.0001   0.0346
  -9.250  -0.4043   0.08616   0.07956  -0.0578   1.0001   0.0343
  -9.000  -0.4168   0.08270   0.07617  -0.0578   1.0001   0.0340
  -8.750  -0.4334   0.07958   0.07312  -0.0570   1.0001   0.0337
  -8.500  -0.4543   0.07697   0.07056  -0.0551   1.0001   0.0335
  -8.250  -0.4781   0.07492   0.06858  -0.0520   1.0001   0.0333
  -8.000  -0.4993   0.07264   0.06632  -0.0493   1.0001   0.0331
  -7.750  -0.5180   0.07027   0.06394  -0.0465   1.0001   0.0329
  -7.500  -0.5341   0.06791   0.06152  -0.0437   1.0001   0.0326
  -7.250  -0.5478   0.06547   0.05899  -0.0410   1.0001   0.0324
  -7.000  -0.5392   0.06125   0.05446  -0.0432   0.9934   0.0320
  -6.750  -0.5204   0.05669   0.04946  -0.0465   0.9832   0.0315
  -6.500  -0.4983   0.05248   0.04475  -0.0492   0.9734   0.0312
  -6.250  -0.4751   0.04884   0.04062  -0.0511   0.9631   0.0313
  -6.000  -0.4489   0.04566   0.03692  -0.0527   0.9532   0.0319
  -5.750  -0.4182   0.04275   0.03347  -0.0544   0.9446   0.0330
  -5.500  -0.3868   0.04025   0.03042  -0.0555   0.9354   0.0341
  -5.250  -0.3570   0.03812   0.02801  -0.0563   0.9260   0.0355
  -5.000  -0.3209   0.03624   0.02593  -0.0578   0.9191   0.0369
  -4.750  -0.2917   0.03477   0.02426  -0.0576   0.9090   0.0384
  -4.500  -0.2548   0.03338   0.02266  -0.0583   0.9026   0.0407
  -4.250  -0.2258   0.03233   0.02137  -0.0577   0.8924   0.0433
  -4.000  -0.1974   0.03117   0.02017  -0.0580   0.8829   0.0477
  -3.750  -0.1651   0.02998   0.01887  -0.0590   0.8747   0.0581
  -3.500  -0.1408   0.02876   0.01777  -0.0591   0.8638   0.0877
  -3.250  -0.1253   0.02521   0.01633  -0.0594   0.8555   0.3719
  -3.000  -0.1210   0.02651   0.01901  -0.0481   0.8459   0.6958
  -2.750  -0.1032   0.02884   0.02111  -0.0406   0.8359   0.7862
  -2.500  -0.0621   0.03009   0.02194  -0.0387   0.8300   0.8337
  -2.250  -0.0316   0.03008   0.02158  -0.0386   0.8203   0.8523
  -2.000   0.0155   0.02974   0.02084  -0.0418   0.8139   0.8635
  -1.750   0.0469   0.02950   0.02031  -0.0426   0.8037   0.8744
  -1.500   0.0888   0.02909   0.01958  -0.0451   0.7972   0.8848
  -1.250   0.1173   0.02891   0.01917  -0.0456   0.7863   0.8950
  -1.000   0.1611   0.02851   0.01849  -0.0487   0.7790   0.9024
  -0.750   0.1882   0.02833   0.01812  -0.0489   0.7690   0.9118
  -0.500   0.2292   0.02803   0.01762  -0.0518   0.7600   0.9188
  -0.250   0.2665   0.02774   0.01712  -0.0538   0.7519   0.9265
   0.000   0.3023   0.02756   0.01681  -0.0559   0.7417   0.9331
   0.250   0.3413   0.02726   0.01631  -0.0582   0.7343   0.9393
   0.750   0.4065   0.02707   0.01592  -0.0612   0.7145   0.9519
   1.000   0.4495   0.02684   0.01557  -0.0645   0.7060   0.9564
   1.250   0.4761   0.02690   0.01557  -0.0650   0.6964   0.9625
   1.500   0.5170   0.02668   0.01527  -0.0679   0.6890   0.9663
   1.750   0.5424   0.02684   0.01542  -0.0683   0.6788   0.9716
   2.000   0.5776   0.02677   0.01527  -0.0701   0.6716   0.9758
   2.250   0.6062   0.02692   0.01543  -0.0711   0.6618   0.9804
   2.500   0.6368   0.02701   0.01552  -0.0723   0.6538   0.9850
   2.750   0.6690   0.02709   0.01561  -0.0738   0.6450   0.9893
   3.000   0.6960   0.02732   0.01586  -0.0745   0.6362   0.9940
   3.250   0.7306   0.02735   0.01593  -0.0762   0.6283   0.9973
   3.500   0.7467   0.02777   0.01641  -0.0750   0.6193   0.9999
   3.750   0.7674   0.02795   0.01659  -0.0740   0.6124   0.9999
   4.000   0.7688   0.02860   0.01732  -0.0700   0.6038   0.9999
   4.250   0.7880   0.02882   0.01755  -0.0688   0.5971   0.9999
   4.500   0.7864   0.02952   0.01834  -0.0644   0.5888   0.9999
   4.750   0.8027   0.02981   0.01870  -0.0627   0.5822   0.9999
   5.000   0.7994   0.03053   0.01950  -0.0580   0.5742   0.9999
   5.250   0.8117   0.03088   0.01991  -0.0556   0.5673   0.9999
   5.500   0.8079   0.03159   0.02069  -0.0509   0.5595   0.9999
   5.750   0.8155   0.03201   0.02119  -0.0479   0.5523   0.9999
   6.000   0.8137   0.03268   0.02194  -0.0436   0.5447   0.9999
   6.250   0.8206   0.03323   0.02256  -0.0407   0.5371   0.9999
   6.500   0.8285   0.03390   0.02333  -0.0382   0.5298   0.9999
   6.750   0.8361   0.03467   0.02423  -0.0358   0.5219   0.9999
   7.000   0.8516   0.03536   0.02502  -0.0347   0.5149   0.9999
   7.250   0.8598   0.03642   0.02622  -0.0330   0.5066   0.9999
   7.500   0.8781   0.03721   0.02715  -0.0324   0.4995   0.9999
   7.750   0.8890   0.03840   0.02851  -0.0314   0.4910   0.9999
   8.000   0.8980   0.03975   0.03001  -0.0303   0.4819   0.9999
   8.250   0.9265   0.03993   0.03035  -0.0305   0.4744   0.9999
   8.500   0.9235   0.04220   0.03279  -0.0290   0.4635   0.9999
   8.750   0.9641   0.04159   0.03238  -0.0299   0.4579   0.9999
   9.000   0.9513   0.04478   0.03574  -0.0283   0.4461   0.9999
   9.250   1.0038   0.04313   0.03430  -0.0294   0.4414   0.9999
   9.500   0.9884   0.04655   0.03788  -0.0279   0.4288   0.9999
   9.750   0.9813   0.04966   0.04115  -0.0272   0.4166   0.9999
  10.000   1.0463   0.04606   0.03782  -0.0276   0.4110   0.9999
  10.250   1.0312   0.04967   0.04159  -0.0266   0.3978   0.9999
  10.500   1.0223   0.05311   0.04520  -0.0263   0.3848   0.9999
  10.750   1.0255   0.05534   0.04760  -0.0261   0.3724   0.9999
  11.000   1.0491   0.05499   0.04745  -0.0254   0.3607   0.9999
  11.250   1.0794   0.05370   0.04639  -0.0245   0.3480   0.9999
  11.500   1.0953   0.05412   0.04698  -0.0239   0.3338   0.9999
  11.750   1.1003   0.05585   0.04887  -0.0236   0.3190   0.9999
  12.000   1.0986   0.05852   0.05170  -0.0236   0.3034   0.9999
  12.250   1.0955   0.06141   0.05473  -0.0239   0.2865   0.9999
  12.500   1.0920   0.06445   0.05790  -0.0243   0.2682   0.9999
  12.750   1.0968   0.06625   0.05978  -0.0244   0.2477   0.9999
  13.000   1.0982   0.06870   0.06228  -0.0246   0.2281   0.9999
  13.250   1.0945   0.07215   0.06579  -0.0254   0.2087   0.9999
  13.500   1.0954   0.07465   0.06819  -0.0256   0.1874   0.9999
  13.750   1.0902   0.07846   0.07197  -0.0266   0.1684   0.9999
  14.000   1.0843   0.08250   0.07599  -0.0277   0.1506   0.9999
  14.250   1.0787   0.08649   0.07989  -0.0288   0.1353   0.9999
  14.500   1.0734   0.09057   0.08393  -0.0300   0.1224   0.9999
  14.750   1.0699   0.09462   0.08797  -0.0312   0.1114   0.9999
  15.000   1.0664   0.09862   0.09192  -0.0325   0.1019   0.9999
  15.250   1.0638   0.10266   0.09597  -0.0339   0.0934   0.9999
  15.500   1.0627   0.10646   0.09983  -0.0350   0.0863   0.9999
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