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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 100,000
Max Cl/Cd: 62.66 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100-il-100000.txt
Download as CSV file: xf-fx60100-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3514   0.09961   0.09477  -0.0345   1.0000   0.1037
  -8.500  -0.3694   0.09778   0.09308  -0.0373   1.0000   0.1085
  -8.250  -0.3983   0.09669   0.09218  -0.0393   1.0000   0.1092
  -8.000  -0.3570   0.09152   0.08692  -0.0344   1.0000   0.1146
  -7.750  -0.3678   0.08973   0.08525  -0.0340   1.0000   0.1204
  -7.500  -0.3967   0.08874   0.08443  -0.0329   1.0000   0.1219
  -7.250  -0.4286   0.08677   0.08263  -0.0365   1.0000   0.1227
  -7.000  -0.3945   0.08407   0.07987  -0.0270   1.0000   0.1303
  -6.750  -0.4133   0.08220   0.07813  -0.0270   1.0000   0.1338
  -6.500  -0.4376   0.07790   0.07394  -0.0351   1.0000   0.1369
  -6.250  -0.4218   0.07753   0.07360  -0.0240   1.0000   0.1435
  -6.000  -0.4359   0.07228   0.06841  -0.0343   1.0000   0.1514
  -5.750  -0.4289   0.07159   0.06777  -0.0262   1.0000   0.1555
  -5.250  -0.3616   0.03899   0.03312  -0.0703   1.0000   0.0723
  -5.000  -0.3244   0.03437   0.02748  -0.0731   1.0000   0.0585
  -4.750  -0.2949   0.03021   0.02309  -0.0749   1.0000   0.0555
  -4.500  -0.2625   0.02725   0.01959  -0.0763   1.0000   0.0528
  -4.250  -0.2320   0.02510   0.01699  -0.0769   1.0000   0.0515
  -4.000  -0.2042   0.02353   0.01518  -0.0769   1.0000   0.0517
  -3.750  -0.1778   0.02229   0.01384  -0.0767   1.0000   0.0529
  -3.500  -0.1518   0.02130   0.01281  -0.0765   1.0000   0.0556
  -3.250  -0.1249   0.02038   0.01190  -0.0767   1.0000   0.0614
  -3.000  -0.0964   0.01955   0.01109  -0.0774   1.0000   0.0755
  -2.750  -0.0545   0.01723   0.01037  -0.0813   1.0000   0.4105
  -2.500  -0.0290   0.01827   0.01160  -0.0808   0.9963   0.5032
  -2.250   0.0088   0.01897   0.01224  -0.0824   0.9882   0.5438
  -2.000   0.0479   0.01945   0.01262  -0.0845   0.9803   0.5738
  -1.750   0.0883   0.01979   0.01288  -0.0868   0.9718   0.6014
  -1.500   0.1257   0.01999   0.01300  -0.0887   0.9620   0.6267
  -1.250   0.1660   0.02011   0.01308  -0.0911   0.9538   0.6464
  -1.000   0.2040   0.02016   0.01307  -0.0931   0.9444   0.6658
  -0.750   0.2400   0.02020   0.01307  -0.0948   0.9346   0.6852
  -0.500   0.2845   0.02014   0.01300  -0.0978   0.9274   0.7046
  -0.250   0.3191   0.02004   0.01289  -0.0990   0.9157   0.7221
   0.000   0.3558   0.01993   0.01278  -0.1006   0.9048   0.7413
   0.250   0.4026   0.01963   0.01252  -0.1036   0.8986   0.7626
   0.500   0.4344   0.01952   0.01244  -0.1042   0.8871   0.7848
   0.750   0.4686   0.01929   0.01228  -0.1050   0.8764   0.8076
   1.000   0.5133   0.01869   0.01177  -0.1071   0.8699   0.8358
   1.250   0.5404   0.01828   0.01149  -0.1062   0.8574   0.8716
   1.500   0.5748   0.01774   0.01112  -0.1067   0.8453   1.0000
   1.750   0.6194   0.01759   0.01091  -0.1101   0.8344   1.0000
   2.000   0.6634   0.01725   0.01051  -0.1127   0.8244   1.0000
   2.250   0.7020   0.01693   0.01015  -0.1140   0.8125   1.0000
   2.500   0.7352   0.01675   0.00995  -0.1144   0.7985   1.0000
   2.750   0.7678   0.01649   0.00967  -0.1144   0.7837   1.0000
   3.000   0.7963   0.01632   0.00947  -0.1137   0.7649   1.0000
   3.250   0.8256   0.01607   0.00923  -0.1129   0.7457   1.0000
   3.500   0.8556   0.01583   0.00895  -0.1122   0.7272   1.0000
   3.750   0.8827   0.01580   0.00890  -0.1114   0.7061   1.0000
   4.000   0.9106   0.01573   0.00880  -0.1106   0.6846   1.0000
   4.250   0.9367   0.01578   0.00885  -0.1096   0.6604   1.0000
   4.500   0.9628   0.01586   0.00888  -0.1085   0.6348   1.0000
   4.750   0.9883   0.01600   0.00896  -0.1075   0.6075   1.0000
   5.000   1.0130   0.01624   0.00916  -0.1064   0.5791   1.0000
   5.250   1.0370   0.01655   0.00942  -0.1052   0.5492   1.0000
   5.500   1.0601   0.01692   0.00975  -0.1040   0.5174   1.0000
   5.750   1.0825   0.01734   0.01010  -0.1027   0.4835   1.0000
   6.000   1.1036   0.01784   0.01056  -0.1013   0.4453   1.0000
   6.250   1.1232   0.01845   0.01104  -0.0997   0.4021   1.0000
   6.500   1.1404   0.01926   0.01163  -0.0978   0.3521   1.0000
   6.750   1.1558   0.02033   0.01241  -0.0958   0.2977   1.0000
   7.000   1.1701   0.02166   0.01338  -0.0939   0.2501   1.0000
   7.250   1.1852   0.02305   0.01452  -0.0921   0.2110   1.0000
   7.500   1.2010   0.02449   0.01578  -0.0905   0.1821   1.0000
   7.750   1.2180   0.02603   0.01718  -0.0890   0.1597   1.0000
   8.000   1.2370   0.02754   0.01863  -0.0877   0.1435   1.0000
   8.250   1.2580   0.02922   0.02026  -0.0868   0.1309   1.0000
   8.500   1.2811   0.03109   0.02210  -0.0861   0.1207   1.0000
   8.750   1.3049   0.03291   0.02380  -0.0857   0.1117   1.0000
   9.000   1.3256   0.03451   0.02571  -0.0846   0.1048   1.0000
   9.250   1.3522   0.03660   0.02778  -0.0846   0.0996   1.0000
   9.500   1.3745   0.03903   0.03056  -0.0837   0.0960   1.0000
   9.750   1.3947   0.04146   0.03337  -0.0826   0.0928   1.0000
  10.000   1.4138   0.04386   0.03601  -0.0816   0.0895   1.0000
  10.250   1.4310   0.04703   0.03932  -0.0808   0.0851   1.0000
  10.500   1.4348   0.04897   0.04183  -0.0779   0.0808   1.0000
  10.750   1.4471   0.04967   0.04236  -0.0769   0.0723   1.0000
  11.000   1.4489   0.04966   0.04250  -0.0741   0.0650   1.0000
  11.250   1.4494   0.05208   0.04520  -0.0716   0.0600   1.0000
  11.500   1.4430   0.05399   0.04742  -0.0681   0.0550   1.0000
  11.750   1.4383   0.05689   0.05033  -0.0657   0.0498   1.0000
  12.000   1.4183   0.05983   0.05373  -0.0618   0.0474   1.0000
  12.250   1.4051   0.06273   0.05687  -0.0594   0.0440   1.0000
  12.500   1.4056   0.06621   0.06014  -0.0587   0.0397   1.0000
  12.750   1.3842   0.07047   0.06481  -0.0573   0.0391   1.0000
  13.000   1.3625   0.07556   0.07026  -0.0570   0.0387   1.0000
  13.250   1.3400   0.08129   0.07630  -0.0578   0.0385   1.0000
  13.500   1.3170   0.08767   0.08297  -0.0597   0.0385   1.0000
  13.750   1.2940   0.09463   0.09017  -0.0626   0.0386   1.0000
  14.000   1.2705   0.10229   0.09804  -0.0665   0.0389   1.0000
  14.250   1.2485   0.11040   0.10633  -0.0711   0.0393   1.0000
  14.500   1.2265   0.11924   0.11531  -0.0764   0.0397   1.0000
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