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FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 500,000
Max Cl/Cd: 107.75 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-500000-n5.txt
Download as CSV file: xf-fx73cl2152-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL2-152                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4651   0.05320   0.04993  -0.1085   0.9673   0.0262
 -11.250  -0.4963   0.04538   0.04195  -0.1152   0.9553   0.0264
 -11.000  -0.5130   0.03854   0.03495  -0.1223   0.9443   0.0265
 -10.750  -0.5021   0.03203   0.02823  -0.1332   0.9359   0.0269
 -10.500  -0.4717   0.02671   0.02265  -0.1453   0.9277   0.0273
 -10.250  -0.4412   0.02398   0.01969  -0.1515   0.9185   0.0277
  -9.750  -0.3696   0.02062   0.01600  -0.1598   0.9000   0.0285
  -9.500  -0.3214   0.01928   0.01456  -0.1652   0.8871   0.0290
  -9.250  -0.2367   0.01781   0.01289  -0.1776   0.8603   0.0298
  -9.000  -0.1487   0.01705   0.01158  -0.1907   0.7775   0.0309
  -8.750  -0.1224   0.01686   0.01096  -0.1911   0.7094   0.0315
  -8.500  -0.0991   0.01658   0.01037  -0.1907   0.6615   0.0319
  -8.250  -0.0736   0.01628   0.00980  -0.1907   0.6257   0.0324
  -8.000  -0.0460   0.01586   0.00923  -0.1913   0.5976   0.0329
  -7.750  -0.0176   0.01555   0.00878  -0.1918   0.5758   0.0334
  -7.500   0.0115   0.01527   0.00836  -0.1923   0.5580   0.0340
  -7.250   0.0409   0.01499   0.00797  -0.1929   0.5429   0.0347
  -7.000   0.0705   0.01474   0.00759  -0.1934   0.5297   0.0355
  -6.750   0.1004   0.01450   0.00722  -0.1939   0.5177   0.0364
  -6.500   0.1308   0.01423   0.00685  -0.1946   0.5078   0.0371
  -6.250   0.1614   0.01396   0.00651  -0.1953   0.4981   0.0380
  -6.000   0.1916   0.01376   0.00623  -0.1958   0.4900   0.0388
  -5.750   0.2220   0.01357   0.00596  -0.1964   0.4819   0.0398
  -5.250   0.2826   0.01325   0.00547  -0.1973   0.4685   0.0419
  -5.000   0.3137   0.01304   0.00524  -0.1980   0.4629   0.0433
  -4.750   0.3439   0.01293   0.00505  -0.1984   0.4577   0.0447
  -4.500   0.3741   0.01282   0.00488  -0.1988   0.4533   0.0462
  -4.250   0.4049   0.01268   0.00470  -0.1993   0.4495   0.0477
  -4.000   0.4356   0.01255   0.00454  -0.1998   0.4455   0.0496
  -3.750   0.4657   0.01248   0.00442  -0.2001   0.4416   0.0520
  -3.500   0.4959   0.01241   0.00430  -0.2005   0.4376   0.0546
  -3.250   0.5261   0.01234   0.00420  -0.2008   0.4341   0.0579
  -2.750   0.5869   0.01220   0.00403  -0.2016   0.4282   0.0668
  -2.500   0.6173   0.01213   0.00396  -0.2020   0.4253   0.0752
  -2.250   0.6481   0.01205   0.00391  -0.2025   0.4226   0.0903
  -2.000   0.6787   0.01199   0.00390  -0.2030   0.4196   0.1149
  -1.500   0.7386   0.01196   0.00395  -0.2037   0.4144   0.1586
  -1.250   0.7681   0.01196   0.00398  -0.2038   0.4122   0.1738
  -1.000   0.7974   0.01199   0.00402  -0.2040   0.4097   0.1868
  -0.750   0.8263   0.01203   0.00406  -0.2040   0.4069   0.1984
  -0.500   0.8552   0.01208   0.00411  -0.2040   0.4039   0.2108
  -0.250   0.8839   0.01215   0.00418  -0.2040   0.4013   0.2238
   0.000   0.9125   0.01223   0.00427  -0.2041   0.3987   0.2423
   0.250   0.9415   0.01229   0.00436  -0.2041   0.3967   0.2594
   0.500   0.9705   0.01233   0.00443  -0.2042   0.3947   0.2726
   0.750   0.9992   0.01238   0.00451  -0.2042   0.3924   0.2843
   1.000   1.0277   0.01245   0.00460  -0.2042   0.3901   0.2985
   1.250   1.0561   0.01252   0.00470  -0.2041   0.3876   0.3152
   1.500   1.0843   0.01261   0.00481  -0.2041   0.3852   0.3321
   1.750   1.1123   0.01272   0.00493  -0.2040   0.3828   0.3512
   2.000   1.1401   0.01285   0.00508  -0.2038   0.3806   0.3721
   2.250   1.1682   0.01295   0.00522  -0.2038   0.3788   0.3921
   2.500   1.1965   0.01302   0.00536  -0.2037   0.3771   0.4130
   2.750   1.2247   0.01311   0.00551  -0.2037   0.3752   0.4364
   3.000   1.2525   0.01321   0.00566  -0.2035   0.3731   0.4594
   3.250   1.2801   0.01331   0.00582  -0.2034   0.3707   0.4817
   3.500   1.3073   0.01343   0.00599  -0.2031   0.3683   0.5071
   3.750   1.3340   0.01357   0.00617  -0.2028   0.3658   0.5331
   4.000   1.3602   0.01373   0.00636  -0.2024   0.3633   0.5565
   4.250   1.3869   0.01388   0.00656  -0.2021   0.3613   0.5809
   4.500   1.4139   0.01398   0.00676  -0.2018   0.3594   0.6072
   4.750   1.4404   0.01410   0.00695  -0.2014   0.3572   0.6344
   5.000   1.4664   0.01423   0.00716  -0.2010   0.3548   0.6608
   5.250   1.4919   0.01437   0.00737  -0.2004   0.3524   0.6891
   5.500   1.5168   0.01452   0.00759  -0.1998   0.3499   0.7188
   6.000   1.5644   0.01487   0.00807  -0.1980   0.3447   0.7906
   6.250   1.5861   0.01490   0.00828  -0.1966   0.3424   0.8554
   6.500   1.5992   0.01486   0.00836  -0.1935   0.3400   1.0000
   6.750   1.6238   0.01507   0.00859  -0.1928   0.3373   1.0000
   7.000   1.6478   0.01530   0.00882  -0.1920   0.3345   1.0000
   7.250   1.6708   0.01556   0.00907  -0.1911   0.3318   1.0000
   7.500   1.6931   0.01585   0.00935  -0.1901   0.3291   1.0000
   7.750   1.7167   0.01608   0.00963  -0.1893   0.3266   1.0000
   8.000   1.7400   0.01632   0.00990  -0.1885   0.3235   1.0000
   8.250   1.7625   0.01658   0.01019  -0.1875   0.3202   1.0000
   8.500   1.7842   0.01688   0.01051  -0.1864   0.3170   1.0000
   8.750   1.8044   0.01723   0.01085  -0.1851   0.3135   1.0000
   9.000   1.8258   0.01752   0.01118  -0.1839   0.3087   1.0000
   9.250   1.8451   0.01788   0.01153  -0.1825   0.3016   1.0000
   9.500   1.8629   0.01832   0.01195  -0.1808   0.2949   1.0000
   9.750   1.8825   0.01870   0.01236  -0.1795   0.2887   1.0000
  10.000   1.8993   0.01921   0.01286  -0.1777   0.2830   1.0000
  10.250   1.9172   0.01968   0.01336  -0.1761   0.2779   1.0000
  10.500   1.9348   0.02018   0.01388  -0.1745   0.2723   1.0000
  10.750   1.9496   0.02081   0.01451  -0.1726   0.2672   1.0000
  11.000   1.9661   0.02137   0.01511  -0.1709   0.2630   1.0000
  11.250   1.9824   0.02195   0.01574  -0.1692   0.2584   1.0000
  11.500   1.9960   0.02267   0.01648  -0.1672   0.2536   1.0000
  11.750   2.0087   0.02345   0.01729  -0.1651   0.2493   1.0000
  12.000   2.0233   0.02415   0.01805  -0.1633   0.2444   1.0000
  12.250   2.0346   0.02505   0.01898  -0.1612   0.2390   1.0000
  12.500   2.0440   0.02608   0.02003  -0.1589   0.2340   1.0000
  12.750   2.0556   0.02700   0.02102  -0.1570   0.2287   1.0000
  13.000   2.0628   0.02823   0.02229  -0.1546   0.2228   1.0000
  13.250   2.0702   0.02950   0.02360  -0.1524   0.2171   1.0000
  13.500   2.0752   0.03099   0.02513  -0.1502   0.2096   1.0000
  13.750   2.0766   0.03282   0.02699  -0.1477   0.2016   1.0000
  14.000   2.0724   0.03520   0.02939  -0.1451   0.1916   1.0000
  14.250   2.0668   0.03790   0.03210  -0.1428   0.1806   1.0000
  14.500   2.0558   0.04133   0.03557  -0.1407   0.1698   1.0000
  14.750   2.0396   0.04564   0.03990  -0.1390   0.1593   1.0000
  15.000   2.0203   0.05074   0.04505  -0.1379   0.1502   1.0000
  15.250   1.9998   0.05642   0.05082  -0.1376   0.1419   1.0000
  15.500   1.9772   0.06277   0.05726  -0.1378   0.1354   1.0000
  15.750   1.9537   0.06954   0.06413  -0.1385   0.1294   1.0000
  16.000   1.9284   0.07683   0.07152  -0.1396   0.1244   1.0000
  16.250   1.9066   0.08377   0.07857  -0.1409   0.1193   1.0000
  16.500   1.8822   0.09127   0.08616  -0.1425   0.1147   1.0000
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