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FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-120 AIRFOIL (fx63120-il)
Reynolds number: 50,000
Max Cl/Cd: 40 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63120-il-50000-n5.txt
Download as CSV file: xf-fx63120-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3091   0.11397   0.10743  -0.0356   1.0000   0.1316
  -8.500  -0.3329   0.11376   0.10739  -0.0344   1.0000   0.1338
  -8.250  -0.3627   0.10573   0.09940  -0.0377   1.0000   0.0743
  -8.000  -0.3665   0.10364   0.09738  -0.0354   1.0000   0.0738
  -7.750  -0.3690   0.10128   0.09508  -0.0340   0.9991   0.0731
  -7.500  -0.3555   0.09720   0.09099  -0.0375   0.9927   0.0719
  -7.250  -0.3444   0.09298   0.08678  -0.0415   0.9855   0.0701
  -7.000  -0.3350   0.08812   0.08192  -0.0468   0.9771   0.0682
  -6.750  -0.3256   0.08218   0.07599  -0.0541   0.9677   0.0663
  -6.500  -0.3134   0.07477   0.06854  -0.0644   0.9580   0.0653
  -6.250  -0.2952   0.06628   0.05987  -0.0776   0.9492   0.0654
  -6.000  -0.2687   0.05885   0.05209  -0.0896   0.9419   0.0662
  -5.750  -0.2359   0.05197   0.04468  -0.1004   0.9354   0.0663
  -5.500  -0.1953   0.04653   0.03862  -0.1093   0.9302   0.0671
  -5.250  -0.1490   0.04249   0.03389  -0.1169   0.9268   0.0706
  -5.000  -0.1092   0.03939   0.03012  -0.1218   0.9217   0.0728
  -4.750  -0.0694   0.03701   0.02711  -0.1255   0.9166   0.0744
  -4.500  -0.0322   0.03522   0.02522  -0.1283   0.9126   0.0783
  -4.250   0.0027   0.03393   0.02371  -0.1303   0.9077   0.0825
  -4.000   0.0337   0.03282   0.02234  -0.1311   0.9014   0.0855
  -3.750   0.0699   0.03179   0.02106  -0.1326   0.8969   0.0895
  -3.500   0.1031   0.03095   0.02024  -0.1340   0.8920   0.0968
  -3.250   0.1316   0.03040   0.01951  -0.1343   0.8848   0.1035
  -3.000   0.1707   0.02955   0.01869  -0.1368   0.8803   0.1140
  -2.750   0.2159   0.02860   0.01780  -0.1408   0.8765   0.1400
  -2.500   0.2572   0.02736   0.01727  -0.1451   0.8699   0.2475
  -2.250   0.2945   0.02726   0.01779  -0.1467   0.8644   0.4576
  -2.000   0.3230   0.02764   0.01827  -0.1459   0.8581   0.5262
  -1.750   0.3414   0.02822   0.01894  -0.1430   0.8492   0.5784
  -1.500   0.3715   0.02839   0.01907  -0.1420   0.8443   0.6177
  -1.250   0.3916   0.02867   0.01925  -0.1406   0.8341   0.6362
  -1.000   0.4289   0.02855   0.01896  -0.1419   0.8290   0.6554
  -0.750   0.4526   0.02873   0.01905  -0.1412   0.8198   0.6709
  -0.500   0.4871   0.02864   0.01885  -0.1422   0.8137   0.6871
  -0.250   0.5157   0.02871   0.01883  -0.1423   0.8059   0.7016
   0.000   0.5459   0.02872   0.01876  -0.1427   0.7984   0.7170
   0.250   0.5806   0.02857   0.01854  -0.1436   0.7927   0.7334
   0.500   0.6031   0.02881   0.01876  -0.1429   0.7829   0.7497
   1.000   0.6581   0.02890   0.01881  -0.1426   0.7671   0.7878
   1.500   0.7062   0.02891   0.01887  -0.1408   0.7508   0.8319
   2.000   0.7480   0.02878   0.01885  -0.1377   0.7339   0.9013
   2.250   0.7787   0.02877   0.01885  -0.1383   0.7255   1.0000
   2.500   0.8155   0.02903   0.01904  -0.1404   0.7169   1.0000
   2.750   0.8484   0.02940   0.01938  -0.1417   0.7077   1.0000
   3.000   0.8855   0.02950   0.01944  -0.1433   0.6998   1.0000
   3.250   0.9128   0.03002   0.01996  -0.1437   0.6891   1.0000
   3.500   0.9523   0.02988   0.01981  -0.1453   0.6822   1.0000
   3.750   0.9757   0.03049   0.02044  -0.1450   0.6702   1.0000
   4.000   1.0099   0.03053   0.02051  -0.1457   0.6615   1.0000
   4.500   1.0637   0.03116   0.02121  -0.1453   0.6384   1.0000
   4.750   1.0947   0.03118   0.02129  -0.1454   0.6276   1.0000
   5.000   1.1281   0.03104   0.02118  -0.1457   0.6169   1.0000
   5.250   1.1499   0.03152   0.02174  -0.1447   0.6034   1.0000
   5.500   1.1739   0.03188   0.02220  -0.1440   0.5905   1.0000
   5.750   1.2013   0.03206   0.02245  -0.1436   0.5784   1.0000
   6.000   1.2336   0.03193   0.02238  -0.1436   0.5668   1.0000
   6.250   1.2555   0.03238   0.02295  -0.1426   0.5529   1.0000
   6.500   1.2766   0.03286   0.02353  -0.1414   0.5385   1.0000
   6.750   1.2984   0.03328   0.02406  -0.1403   0.5239   1.0000
   7.000   1.3203   0.03368   0.02458  -0.1391   0.5088   1.0000
   7.250   1.3419   0.03407   0.02505  -0.1378   0.4930   1.0000
   7.500   1.3630   0.03440   0.02544  -0.1364   0.4756   1.0000
   7.750   1.3844   0.03461   0.02564  -0.1349   0.4561   1.0000
   8.000   1.3949   0.03539   0.02648  -0.1322   0.4354   1.0000
   8.250   1.4053   0.03621   0.02734  -0.1296   0.4145   1.0000
   8.500   1.4167   0.03706   0.02821  -0.1273   0.3942   1.0000
   8.750   1.4277   0.03803   0.02917  -0.1250   0.3747   1.0000
   9.000   1.4330   0.03943   0.03066  -0.1224   0.3552   1.0000
   9.250   1.4386   0.04089   0.03222  -0.1200   0.3358   1.0000
   9.500   1.4437   0.04245   0.03381  -0.1177   0.3163   1.0000
   9.750   1.4481   0.04413   0.03547  -0.1155   0.2973   1.0000
  10.000   1.4510   0.04607   0.03742  -0.1134   0.2787   1.0000
  10.250   1.4526   0.04825   0.03963  -0.1115   0.2602   1.0000
  10.500   1.4534   0.05062   0.04200  -0.1097   0.2424   1.0000
  10.750   1.4535   0.05318   0.04457  -0.1082   0.2256   1.0000
  11.000   1.4535   0.05589   0.04728  -0.1068   0.2100   1.0000
  11.250   1.4531   0.05876   0.05016  -0.1056   0.1955   1.0000
  11.500   1.4528   0.06172   0.05315  -0.1046   0.1824   1.0000
  11.750   1.4531   0.06473   0.05616  -0.1037   0.1710   1.0000
  12.000   1.4535   0.06779   0.05927  -0.1030   0.1606   1.0000
  12.250   1.4547   0.07097   0.06260  -0.1024   0.1509   1.0000
  12.500   1.4567   0.07400   0.06565  -0.1019   0.1429   1.0000
  12.750   1.4583   0.07726   0.06908  -0.1015   0.1351   1.0000
  13.000   1.4625   0.08019   0.07205  -0.1011   0.1288   1.0000
  13.250   1.4644   0.08359   0.07567  -0.1009   0.1225   1.0000
  13.500   1.4705   0.08623   0.07826  -0.1005   0.1170   1.0000
  13.750   1.4685   0.09042   0.08279  -0.1009   0.1118   1.0000
  14.000   1.4719   0.09364   0.08612  -0.1009   0.1071   1.0000
  14.250   1.4789   0.09649   0.08907  -0.1007   0.1030   1.0000
  14.500   1.4720   0.10164   0.09457  -0.1018   0.0995   1.0000
  14.750   1.4681   0.10625   0.09940  -0.1030   0.0961   1.0000
  15.000   1.4834   0.10750   0.10053  -0.1022   0.0917   1.0000
  15.250   1.4671   0.11445   0.10786  -0.1050   0.0898   1.0000
  15.500   1.4478   0.12231   0.11608  -0.1087   0.0881   1.0000
  15.750   1.4253   0.13125   0.12533  -0.1135   0.0868   1.0000
  16.000   1.3941   0.14286   0.13723  -0.1207   0.0862   1.0000
  16.250   1.3292   0.16540   0.15998  -0.1361   0.0870   1.0000
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