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FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 63-120 AIRFOIL (fx63120-il)
Reynolds number: 100,000
Max Cl/Cd: 67.12 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63120-il-100000-n5.txt
Download as CSV file: xf-fx63120-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3014   0.12008   0.11511  -0.0442   1.0000   0.0609
 -10.000  -0.3097   0.11797   0.11308  -0.0442   1.0000   0.0612
  -9.750  -0.3187   0.11588   0.11109  -0.0434   1.0000   0.0613
  -9.250  -0.3090   0.10433   0.09953  -0.0453   0.9967   0.0414
  -9.000  -0.2926   0.10027   0.09546  -0.0485   0.9924   0.0406
  -8.750  -0.2817   0.09505   0.09024  -0.0542   0.9865   0.0410
  -8.500  -0.2719   0.09013   0.08533  -0.0591   0.9793   0.0410
  -8.250  -0.2621   0.08545   0.08066  -0.0636   0.9716   0.0408
  -8.000  -0.2519   0.08077   0.07599  -0.0683   0.9639   0.0403
  -7.750  -0.2467   0.07573   0.07096  -0.0730   0.9538   0.0399
  -7.250  -0.2359   0.05882   0.05398  -0.0942   0.9298   0.0388
  -7.000  -0.2177   0.04641   0.04098  -0.1154   0.9182   0.0394
  -6.750  -0.1803   0.03861   0.03230  -0.1282   0.9131   0.0410
  -6.500  -0.1358   0.03345   0.02623  -0.1366   0.9107   0.0419
  -6.250  -0.1082   0.03158   0.02428  -0.1384   0.9038   0.0436
  -6.000  -0.0719   0.02985   0.02234  -0.1414   0.8997   0.0459
  -5.750  -0.0303   0.02754   0.01957  -0.1454   0.8970   0.0474
  -5.500   0.0119   0.02566   0.01726  -0.1489   0.8946   0.0495
  -5.250   0.0424   0.02441   0.01579  -0.1500   0.8881   0.0518
  -5.000   0.0769   0.02326   0.01457  -0.1516   0.8833   0.0536
  -4.750   0.1143   0.02219   0.01338  -0.1536   0.8799   0.0557
  -4.500   0.1515   0.02131   0.01238  -0.1555   0.8763   0.0589
  -4.250   0.1799   0.02076   0.01173  -0.1557   0.8688   0.0619
  -4.000   0.2158   0.01991   0.01092  -0.1575   0.8644   0.0652
  -3.750   0.2552   0.01922   0.01018  -0.1598   0.8610   0.0697
  -3.500   0.2847   0.01882   0.00972  -0.1604   0.8532   0.0761
  -3.250   0.3221   0.01824   0.00909  -0.1625   0.8480   0.0878
  -3.000   0.3646   0.01742   0.00837  -0.1658   0.8441   0.1185
  -2.750   0.3992   0.01645   0.00817  -0.1684   0.8363   0.2849
  -2.500   0.4347   0.01627   0.00813  -0.1698   0.8301   0.4015
  -2.250   0.4656   0.01624   0.00819  -0.1702   0.8226   0.4603
  -2.000   0.4947   0.01631   0.00835  -0.1700   0.8148   0.5062
  -1.750   0.5249   0.01640   0.00842  -0.1699   0.8081   0.5384
  -1.500   0.5526   0.01649   0.00847  -0.1697   0.7999   0.5579
  -1.250   0.5851   0.01644   0.00834  -0.1702   0.7943   0.5714
  -1.000   0.6103   0.01655   0.00843  -0.1696   0.7855   0.5840
  -0.750   0.6418   0.01652   0.00833  -0.1700   0.7793   0.5971
  -0.500   0.6692   0.01660   0.00837  -0.1698   0.7710   0.6095
  -0.250   0.6987   0.01659   0.00833  -0.1699   0.7642   0.6205
   0.000   0.7263   0.01666   0.00838  -0.1697   0.7564   0.6321
   0.250   0.7552   0.01669   0.00839  -0.1697   0.7490   0.6454
   0.500   0.7835   0.01676   0.00844  -0.1696   0.7414   0.6594
   0.750   0.8108   0.01682   0.00850  -0.1693   0.7334   0.6723
   1.000   0.8384   0.01689   0.00857  -0.1690   0.7258   0.6859
   1.250   0.8651   0.01697   0.00867  -0.1686   0.7173   0.7004
   1.500   0.8923   0.01704   0.00875  -0.1682   0.7093   0.7155
   1.750   0.9188   0.01713   0.00886  -0.1678   0.7006   0.7306
   2.000   0.9450   0.01722   0.00898  -0.1673   0.6918   0.7456
   2.250   0.9718   0.01728   0.00905  -0.1668   0.6831   0.7610
   2.500   0.9962   0.01739   0.00923  -0.1659   0.6732   0.7770
   2.750   1.0231   0.01740   0.00923  -0.1654   0.6646   0.7941
   3.000   1.0453   0.01751   0.00944  -0.1641   0.6531   0.8123
   3.250   1.0683   0.01756   0.00954  -0.1629   0.6415   0.8326
   3.500   1.0902   0.01753   0.00955  -0.1613   0.6297   0.8566
   3.750   1.1092   0.01750   0.00957  -0.1592   0.6172   0.8935
   4.000   1.1312   0.01753   0.00968  -0.1579   0.6039   1.0000
   4.250   1.1596   0.01778   0.00992  -0.1581   0.5909   1.0000
   4.500   1.1876   0.01804   0.01015  -0.1582   0.5781   1.0000
   4.750   1.2150   0.01830   0.01041  -0.1581   0.5651   1.0000
   5.000   1.2417   0.01858   0.01067  -0.1579   0.5516   1.0000
   5.250   1.2670   0.01890   0.01101  -0.1575   0.5370   1.0000
   5.500   1.2920   0.01925   0.01138  -0.1570   0.5224   1.0000
   5.750   1.3163   0.01961   0.01175  -0.1564   0.5071   1.0000
   6.000   1.3395   0.02000   0.01211  -0.1556   0.4895   1.0000
   6.250   1.3608   0.02044   0.01250  -0.1544   0.4687   1.0000
   6.500   1.3808   0.02095   0.01297  -0.1531   0.4463   1.0000
   6.750   1.4004   0.02152   0.01346  -0.1517   0.4252   1.0000
   7.000   1.4199   0.02212   0.01404  -0.1503   0.4065   1.0000
   7.250   1.4385   0.02275   0.01470  -0.1489   0.3874   1.0000
   7.500   1.4558   0.02343   0.01539  -0.1473   0.3674   1.0000
   7.750   1.4715   0.02417   0.01613  -0.1454   0.3469   1.0000
   8.000   1.4853   0.02499   0.01692  -0.1433   0.3258   1.0000
   8.250   1.4959   0.02589   0.01778  -0.1408   0.3026   1.0000
   8.500   1.5033   0.02695   0.01877  -0.1379   0.2796   1.0000
   8.750   1.5102   0.02812   0.01988  -0.1350   0.2566   1.0000
   9.000   1.5153   0.02947   0.02113  -0.1321   0.2358   1.0000
   9.250   1.5208   0.03089   0.02251  -0.1295   0.2164   1.0000
   9.500   1.5263   0.03239   0.02400  -0.1270   0.1988   1.0000
   9.750   1.5313   0.03401   0.02564  -0.1247   0.1825   1.0000
  10.000   1.5358   0.03575   0.02738  -0.1225   0.1675   1.0000
  10.250   1.5398   0.03761   0.02927  -0.1205   0.1541   1.0000
  10.500   1.5427   0.03964   0.03131  -0.1185   0.1423   1.0000
  10.750   1.5449   0.04184   0.03352  -0.1167   0.1317   1.0000
  11.000   1.5483   0.04402   0.03577  -0.1151   0.1223   1.0000
  11.250   1.5497   0.04646   0.03824  -0.1136   0.1148   1.0000
  11.500   1.5517   0.04893   0.04081  -0.1123   0.1078   1.0000
  11.750   1.5522   0.05163   0.04356  -0.1111   0.1024   1.0000
  12.000   1.5549   0.05421   0.04626  -0.1100   0.0971   1.0000
  12.250   1.5543   0.05719   0.04929  -0.1090   0.0929   1.0000
  12.500   1.5561   0.06002   0.05222  -0.1082   0.0889   1.0000
  12.750   1.5583   0.06285   0.05520  -0.1075   0.0847   1.0000
  13.000   1.5582   0.06601   0.05842  -0.1070   0.0813   1.0000
  13.250   1.5588   0.06916   0.06163  -0.1065   0.0782   1.0000
  13.500   1.5621   0.07209   0.06477  -0.1061   0.0749   1.0000
  13.750   1.5636   0.07528   0.06809  -0.1059   0.0718   1.0000
  14.000   1.5633   0.07872   0.07160  -0.1059   0.0690   1.0000
  14.250   1.5642   0.08211   0.07509  -0.1059   0.0662   1.0000
  14.500   1.5649   0.08565   0.07886  -0.1062   0.0633   1.0000
  14.750   1.5640   0.08944   0.08281  -0.1068   0.0605   1.0000
  15.000   1.5621   0.09339   0.08685  -0.1076   0.0583   1.0000
  15.250   1.5613   0.09722   0.09077  -0.1083   0.0561   1.0000
  15.500   1.5594   0.10148   0.09530  -0.1093   0.0538   1.0000
  15.750   1.5567   0.10585   0.09987  -0.1106   0.0515   1.0000
  16.000   1.5537   0.11030   0.10445  -0.1122   0.0496   1.0000
  16.250   1.5505   0.11478   0.10900  -0.1140   0.0479   1.0000
  16.500   1.5473   0.11940   0.11379  -0.1157   0.0462   1.0000
  16.750   1.5418   0.12467   0.11932  -0.1181   0.0444   1.0000
  17.000   1.5357   0.13010   0.12494  -0.1208   0.0427   1.0000
  17.250   1.5312   0.13520   0.13017  -0.1235   0.0412   1.0000
  17.500   1.5281   0.13998   0.13502  -0.1262   0.0398   1.0000
  17.750   1.5231   0.14528   0.14043  -0.1292   0.0385   1.0000
  18.000   1.5131   0.15202   0.14744  -0.1332   0.0375   1.0000
  18.250   1.5013   0.15939   0.15506  -0.1381   0.0364   1.0000
  18.500   1.4898   0.16687   0.16274  -0.1432   0.0355   1.0000
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