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FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 63-120 AIRFOIL (fx63120-il)
Reynolds number: 200,000
Max Cl/Cd: 89.96 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63120-il-200000-n5.txt
Download as CSV file: xf-fx63120-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-120 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2526   0.08725   0.08365  -0.0660   0.9797   0.0231
  -9.000  -0.2478   0.08116   0.07757  -0.0713   0.9717   0.0232
  -8.750  -0.2500   0.07363   0.07006  -0.0777   0.9601   0.0233
  -8.500  -0.2588   0.06456   0.06101  -0.0856   0.9453   0.0234
  -8.250  -0.2787   0.03563   0.03103  -0.1298   0.9204   0.0238
  -8.000  -0.2466   0.03415   0.02949  -0.1335   0.9154   0.0245
  -7.750  -0.2092   0.03177   0.02687  -0.1391   0.9119   0.0258
  -7.500  -0.1725   0.02736   0.02181  -0.1461   0.9065   0.0271
  -7.250  -0.1336   0.02408   0.01778  -0.1513   0.9012   0.0288
  -7.000  -0.0965   0.02265   0.01627  -0.1544   0.8970   0.0300
  -6.750  -0.0587   0.02136   0.01478  -0.1574   0.8926   0.0314
  -6.500  -0.0254   0.02005   0.01321  -0.1592   0.8858   0.0325
  -6.250   0.0117   0.01896   0.01181  -0.1616   0.8805   0.0343
  -6.000   0.0460   0.01784   0.01056  -0.1634   0.8747   0.0356
  -5.750   0.0773   0.01705   0.00972  -0.1644   0.8675   0.0367
  -5.500   0.1116   0.01634   0.00891  -0.1659   0.8619   0.0379
  -5.250   0.1416   0.01582   0.00830  -0.1666   0.8546   0.0398
  -5.000   0.1734   0.01529   0.00766  -0.1675   0.8478   0.0413
  -4.750   0.2055   0.01469   0.00700  -0.1686   0.8416   0.0426
  -4.500   0.2358   0.01421   0.00650  -0.1693   0.8343   0.0442
  -4.250   0.2684   0.01384   0.00607  -0.1704   0.8282   0.0464
  -4.000   0.2983   0.01355   0.00572  -0.1710   0.8209   0.0493
  -3.750   0.3301   0.01321   0.00532  -0.1719   0.8141   0.0522
  -3.500   0.3614   0.01293   0.00499  -0.1727   0.8070   0.0566
  -3.250   0.3921   0.01268   0.00467  -0.1733   0.7984   0.0634
  -3.000   0.4234   0.01239   0.00439  -0.1741   0.7902   0.0815
  -2.750   0.4559   0.01193   0.00413  -0.1754   0.7820   0.1461
  -2.500   0.4898   0.01135   0.00399  -0.1773   0.7752   0.2864
  -2.250   0.5196   0.01126   0.00405  -0.1778   0.7676   0.3709
  -2.000   0.5496   0.01126   0.00402  -0.1781   0.7614   0.4103
  -1.750   0.5781   0.01124   0.00405  -0.1782   0.7537   0.4409
  -1.500   0.6074   0.01123   0.00408  -0.1783   0.7471   0.4704
  -1.250   0.6357   0.01126   0.00416  -0.1783   0.7398   0.4959
  -1.000   0.6643   0.01130   0.00418  -0.1782   0.7328   0.5129
  -0.750   0.6928   0.01134   0.00421  -0.1782   0.7259   0.5274
  -0.500   0.7210   0.01139   0.00425  -0.1782   0.7184   0.5405
  -0.250   0.7495   0.01145   0.00428  -0.1781   0.7118   0.5516
   0.000   0.7773   0.01150   0.00434  -0.1780   0.7038   0.5630
   0.500   0.8332   0.01164   0.00447  -0.1778   0.6887   0.5887
   0.750   0.8613   0.01172   0.00453  -0.1777   0.6814   0.6021
   1.000   0.8886   0.01180   0.00465  -0.1774   0.6728   0.6153
   1.250   0.9164   0.01190   0.00472  -0.1773   0.6650   0.6285
   1.500   0.9436   0.01200   0.00485  -0.1770   0.6558   0.6419
   1.750   0.9709   0.01210   0.00495  -0.1768   0.6473   0.6543
   2.000   0.9975   0.01221   0.00509  -0.1764   0.6370   0.6670
   2.250   1.0239   0.01232   0.00521  -0.1760   0.6251   0.6800
   2.500   1.0499   0.01246   0.00532  -0.1755   0.6115   0.6930
   2.750   1.0757   0.01260   0.00545  -0.1749   0.5979   0.7052
   3.000   1.1015   0.01274   0.00562  -0.1744   0.5853   0.7169
   3.250   1.1274   0.01290   0.00579  -0.1739   0.5727   0.7289
   3.500   1.1530   0.01307   0.00598  -0.1734   0.5598   0.7413
   3.750   1.1782   0.01325   0.00618  -0.1728   0.5465   0.7537
   4.000   1.2029   0.01345   0.00639  -0.1721   0.5327   0.7667
   4.250   1.2270   0.01367   0.00661  -0.1713   0.5185   0.7808
   4.500   1.2504   0.01390   0.00685  -0.1703   0.5029   0.7959
   4.750   1.2728   0.01416   0.00710  -0.1692   0.4853   0.8127
   5.000   1.2938   0.01444   0.00737  -0.1678   0.4662   0.8324
   5.250   1.3125   0.01472   0.00766  -0.1659   0.4475   0.8595
   5.500   1.3253   0.01486   0.00783  -0.1628   0.4305   0.9983
   5.750   1.3484   0.01534   0.00823  -0.1621   0.4106   1.0000
   6.000   1.3708   0.01582   0.00864  -0.1612   0.3925   1.0000
   6.250   1.3930   0.01630   0.00909  -0.1604   0.3750   1.0000
   6.500   1.4148   0.01678   0.00955  -0.1594   0.3571   1.0000
   6.750   1.4348   0.01735   0.01005  -0.1582   0.3340   1.0000
   7.000   1.4521   0.01804   0.01063  -0.1566   0.3066   1.0000
   7.250   1.4674   0.01885   0.01130  -0.1547   0.2780   1.0000
   7.500   1.4820   0.01968   0.01201  -0.1527   0.2525   1.0000
   7.750   1.4953   0.02051   0.01275  -0.1505   0.2320   1.0000
   8.000   1.5084   0.02132   0.01352  -0.1483   0.2147   1.0000
   8.250   1.5210   0.02218   0.01435  -0.1460   0.1987   1.0000
   8.500   1.5328   0.02310   0.01524  -0.1438   0.1827   1.0000
   8.750   1.5437   0.02410   0.01621  -0.1414   0.1664   1.0000
   9.000   1.5535   0.02519   0.01726  -0.1391   0.1502   1.0000
   9.250   1.5625   0.02638   0.01841  -0.1368   0.1349   1.0000
   9.500   1.5710   0.02765   0.01967  -0.1345   0.1217   1.0000
   9.750   1.5793   0.02899   0.02100  -0.1323   0.1110   1.0000
  10.000   1.5867   0.03044   0.02246  -0.1302   0.1025   1.0000
  10.250   1.5944   0.03192   0.02398  -0.1283   0.0953   1.0000
  10.500   1.6011   0.03355   0.02565  -0.1264   0.0896   1.0000
  10.750   1.6084   0.03518   0.02737  -0.1246   0.0842   1.0000
  11.000   1.6122   0.03719   0.02940  -0.1228   0.0795   1.0000
  11.250   1.6199   0.03890   0.03123  -0.1214   0.0754   1.0000
  11.500   1.6253   0.04089   0.03330  -0.1199   0.0716   1.0000
  11.750   1.6275   0.04325   0.03571  -0.1185   0.0683   1.0000
  12.000   1.6331   0.04535   0.03793  -0.1173   0.0650   1.0000
  12.250   1.6387   0.04751   0.04020  -0.1163   0.0614   1.0000
  12.500   1.6410   0.05007   0.04282  -0.1153   0.0582   1.0000
  12.750   1.6435   0.05269   0.04553  -0.1144   0.0555   1.0000
  13.000   1.6485   0.05509   0.04806  -0.1137   0.0527   1.0000
  13.250   1.6513   0.05782   0.05089  -0.1132   0.0501   1.0000
  13.500   1.6515   0.06095   0.05409  -0.1127   0.0481   1.0000
  13.750   1.6525   0.06406   0.05731  -0.1124   0.0462   1.0000
  14.000   1.6551   0.06705   0.06046  -0.1122   0.0443   1.0000
  14.250   1.6563   0.07029   0.06383  -0.1122   0.0422   1.0000
  14.500   1.6553   0.07393   0.06756  -0.1123   0.0406   1.0000
  14.750   1.6516   0.07806   0.07177  -0.1127   0.0392   1.0000
  15.000   1.6524   0.08160   0.07547  -0.1131   0.0376   1.0000
  15.250   1.6518   0.08544   0.07946  -0.1136   0.0360   1.0000
  15.500   1.6498   0.08959   0.08373  -0.1144   0.0345   1.0000
  15.750   1.6453   0.09421   0.08845  -0.1155   0.0332   1.0000
  16.000   1.6398   0.09908   0.09342  -0.1169   0.0320   1.0000
  16.250   1.6385   0.10333   0.09786  -0.1180   0.0306   1.0000
  16.500   1.6354   0.10794   0.10263  -0.1195   0.0292   1.0000
  16.750   1.6310   0.11287   0.10770  -0.1213   0.0280   1.0000
  17.000   1.6240   0.11832   0.11323  -0.1235   0.0269   1.0000
  17.250   1.6192   0.12340   0.11846  -0.1256   0.0259   1.0000
  17.500   1.6158   0.12830   0.12354  -0.1278   0.0246   1.0000
  17.750   1.6111   0.13352   0.12890  -0.1303   0.0235   1.0000
  18.000   1.6056   0.13891   0.13442  -0.1330   0.0227   1.0000
  18.250   1.5988   0.14467   0.14027  -0.1362   0.0220   1.0000
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