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FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 63-147 AIRFOIL (fx63147-il)
Reynolds number: 50,000
Max Cl/Cd: 18.56 at α=13°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63147-il-50000.txt
Download as CSV file: xf-fx63147-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3562   0.13806   0.13110  -0.0348   1.0001   0.2049
 -11.000  -0.3337   0.13284   0.12587  -0.0334   1.0001   0.2123
 -10.750  -0.3572   0.13257   0.12575  -0.0348   1.0001   0.2204
 -10.500  -0.3309   0.12738   0.12055  -0.0330   1.0001   0.2315
 -10.250  -0.3291   0.12434   0.11759  -0.0326   1.0001   0.2404
 -10.000  -0.3497   0.12372   0.11710  -0.0330   1.0001   0.2509
  -9.750  -0.3320   0.11963   0.11304  -0.0314   1.0001   0.2649
  -9.500  -0.3214   0.11619   0.10964  -0.0302   1.0001   0.2773
  -9.250  -0.3176   0.11333   0.10686  -0.0291   1.0001   0.2901
  -9.000  -0.3158   0.11067   0.10427  -0.0279   1.0001   0.3041
  -8.750  -0.3147   0.10813   0.10182  -0.0265   1.0001   0.3188
  -8.500  -0.3131   0.10560   0.09938  -0.0249   1.0001   0.3342
  -6.250  -0.3926   0.08578   0.08070  -0.0061   1.0001   0.3850
  -6.000  -0.4479   0.08438   0.07954  -0.0029   1.0001   0.3632
  -5.750  -0.4950   0.08312   0.07850   0.0004   1.0001   0.3613
  -5.500  -0.5759   0.05998   0.05352  -0.0303   1.0001   0.1297
  -5.250  -0.5622   0.05573   0.04882  -0.0305   1.0001   0.1146
  -5.000  -0.5438   0.05229   0.04453  -0.0311   1.0001   0.1022
  -4.750  -0.5275   0.04926   0.04139  -0.0310   1.0001   0.0999
  -4.500  -0.5084   0.04660   0.03839  -0.0312   1.0001   0.0971
  -4.250  -0.4868   0.04420   0.03553  -0.0314   1.0001   0.0942
  -4.000  -0.4638   0.04219   0.03300  -0.0314   1.0001   0.0919
  -3.750  -0.4306   0.04059   0.03081  -0.0328   0.9970   0.0903
  -3.500  -0.3817   0.03892   0.02880  -0.0363   0.9872   0.0908
  -3.250  -0.3411   0.03767   0.02748  -0.0381   0.9775   0.0940
  -3.000  -0.3039   0.03696   0.02665  -0.0388   0.9676   0.1001
  -2.750  -0.2680   0.03622   0.02591  -0.0393   0.9584   0.1129
  -2.500  -0.0385   0.03815   0.03060  -0.0454   0.9725   0.9999
  -2.250  -0.0038   0.03791   0.03001  -0.0498   0.9585   0.9999
  -2.000   0.0292   0.03777   0.02956  -0.0536   0.9453   0.9999
  -1.750   0.0626   0.03771   0.02920  -0.0572   0.9331   0.9999
  -1.500   0.0874   0.03772   0.02898  -0.0590   0.9201   0.9999
  -1.250   0.1089   0.03782   0.02890  -0.0600   0.9073   0.9999
  -1.000   0.1293   0.03801   0.02890  -0.0608   0.8950   0.9999
  -0.750   0.1529   0.03821   0.02892  -0.0619   0.8837   0.9999
  -0.500   0.1863   0.03835   0.02887  -0.0644   0.8737   0.9999
  -0.250   0.1933   0.03880   0.02921  -0.0626   0.8614   0.9999
   0.000   0.2026   0.03930   0.02961  -0.0611   0.8504   0.9999
   0.250   0.2305   0.03962   0.02978  -0.0624   0.8412   0.9999
   0.500   0.2372   0.04021   0.03029  -0.0604   0.8303   0.9999
   0.750   0.2382   0.04094   0.03096  -0.0576   0.8202   0.9999
   1.000   0.2751   0.04125   0.03113  -0.0600   0.8121   0.9999
   1.250   0.2571   0.04226   0.03212  -0.0544   0.8014   0.9999
   1.500   0.2659   0.04300   0.03279  -0.0527   0.7928   0.9999
   1.750   0.2772   0.04367   0.03340  -0.0513   0.7837   0.9999
   2.000   0.2703   0.04461   0.03430  -0.0474   0.7745   0.9999
   2.250   0.2963   0.04520   0.03482  -0.0479   0.7666   0.9999
   2.500   0.2757   0.04633   0.03594  -0.0424   0.7580   0.9999
   2.750   0.3083   0.04694   0.03648  -0.0437   0.7504   0.9999
   3.000   0.2803   0.04821   0.03775  -0.0376   0.7428   0.9999
   3.250   0.3081   0.04900   0.03849  -0.0383   0.7354   0.9999
   3.500   0.2928   0.05041   0.03990  -0.0345   0.7292   0.9999
   3.750   0.3108   0.05152   0.04098  -0.0345   0.7219   0.9999
   4.000   0.3178   0.05294   0.04240  -0.0337   0.7153   0.9999
   4.250   0.3278   0.05442   0.04389  -0.0335   0.7089   0.9999
   4.500   0.3516   0.05581   0.04527  -0.0345   0.7016   0.9999
   4.750   0.3558   0.05752   0.04701  -0.0340   0.6950   0.9999
   5.000   0.3857   0.05891   0.04841  -0.0355   0.6866   0.9999
   5.250   0.3860   0.06100   0.05054  -0.0352   0.6822   0.9999
   5.500   0.4016   0.06292   0.05251  -0.0362   0.6772   0.9999
   5.750   0.4229   0.06478   0.05441  -0.0373   0.6704   0.9999
   6.000   0.4271   0.06721   0.05689  -0.0379   0.6688   0.9999
   6.250   0.4377   0.06988   0.05963  -0.0392   0.6703   0.9999
   6.500   0.4542   0.07276   0.06259  -0.0412   0.6732   0.9999
   6.750   0.3744   0.07841   0.06837  -0.0408   0.7690   0.9999
   7.000   0.3883   0.08035   0.07037  -0.0415   0.7576   0.9999
   7.250   0.4091   0.08275   0.07282  -0.0430   0.7457   0.9999
   7.500   0.4409   0.08595   0.07611  -0.0459   0.7340   0.9999
   7.750   0.4594   0.08807   0.07831  -0.0470   0.7202   0.9999
   8.000   0.4635   0.08959   0.07990  -0.0465   0.7084   0.9999
   8.250   0.4771   0.09193   0.08232  -0.0473   0.6970   0.9999
   8.500   0.5014   0.09501   0.08550  -0.0493   0.6862   0.9999
   8.750   0.5292   0.09818   0.08882  -0.0515   0.6734   0.9999
   9.000   0.5328   0.09982   0.09054  -0.0512   0.6601   0.9999
   9.250   0.5448   0.10214   0.09295  -0.0517   0.6460   0.9999
   9.500   0.5568   0.10463   0.09554  -0.0523   0.6326   0.9999
   9.750   0.5702   0.10736   0.09839  -0.0532   0.6201   0.9999
  10.000   0.5917   0.11074   0.10191  -0.0548   0.6087   0.9999
  10.250   0.6155   0.11416   0.10547  -0.0564   0.5947   0.9999
  10.500   0.6270   0.11669   0.10814  -0.0570   0.5809   0.9999
  10.750   0.6251   0.11877   0.11031  -0.0569   0.5688   0.9999
  11.000   0.6356   0.12154   0.11319  -0.0575   0.5543   0.9999
  11.250   0.6510   0.12445   0.11624  -0.0584   0.5377   0.9999
  11.500   0.6600   0.12736   0.11927  -0.0591   0.5237   0.9999
  13.000   1.1807   0.06360   0.05801  -0.0208   0.2591   0.9999
  13.250   1.1159   0.07722   0.07178  -0.0246   0.2614   0.9999
  13.500   1.1854   0.06585   0.05981  -0.0177   0.1990   0.9999
  13.750   1.1786   0.06934   0.06321  -0.0173   0.1792   0.9999
  14.000   1.1896   0.07114   0.06472  -0.0158   0.1566   0.9999
  14.250   1.1960   0.07414   0.06770  -0.0150   0.1426   0.9999
  14.500   1.2157   0.07640   0.06988  -0.0137   0.1299   0.9999
  14.750   1.1969   0.08224   0.07613  -0.0150   0.1275   0.9999
  15.000   1.1762   0.08858   0.08279  -0.0168   0.1257   0.9999
  15.250   1.1483   0.09632   0.09082  -0.0199   0.1256   0.9999
  15.500   1.1103   0.10617   0.10091  -0.0246   0.1274   0.9999
  15.750   1.0695   0.11780   0.11265  -0.0309   0.1296   0.9999
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