Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 100,000
Max Cl/Cd: 52.83 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-100000-n5.txt
Download as CSV file: xf-fx73cl2152-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0930   0.09821   0.09328  -0.0639   0.9439   0.0574
  -8.000  -0.0858   0.09444   0.08953  -0.0661   0.9287   0.0568
  -7.500  -0.0788   0.08646   0.08158  -0.0700   0.8894   0.0555
  -7.250  -0.0736   0.08189   0.07701  -0.0732   0.8677   0.0551
  -7.000  -0.0599   0.07752   0.07258  -0.0774   0.8453   0.0559
  -6.750  -0.0470   0.07242   0.06740  -0.0831   0.8202   0.0569
  -6.500  -0.0358   0.06561   0.06047  -0.0912   0.7936   0.0574
  -6.250  -0.0385   0.03286   0.02630  -0.1441   0.7774   0.0580
  -6.000   0.0310   0.02869   0.02131  -0.1568   0.7478   0.0610
  -5.750   0.0873   0.02684   0.01899  -0.1638   0.7143   0.0633
  -5.500   0.1392   0.02511   0.01667  -0.1699   0.6839   0.0656
  -5.250   0.1813   0.02404   0.01519  -0.1735   0.6578   0.0684
  -5.000   0.2184   0.02341   0.01434  -0.1759   0.6360   0.0711
  -4.750   0.2554   0.02266   0.01327  -0.1781   0.6178   0.0740
  -4.500   0.2904   0.02204   0.01245  -0.1798   0.6027   0.0768
  -4.250   0.3252   0.02163   0.01190  -0.1814   0.5902   0.0809
  -4.000   0.3590   0.02118   0.01127  -0.1828   0.5789   0.0855
  -3.750   0.3932   0.02083   0.01083  -0.1843   0.5695   0.0903
  -3.500   0.4265   0.02050   0.01041  -0.1856   0.5601   0.0971
  -3.000   0.4935   0.02002   0.00976  -0.1881   0.5442   0.1189
  -2.750   0.5269   0.01985   0.00961  -0.1894   0.5370   0.1371
  -2.500   0.5604   0.01982   0.00947  -0.1906   0.5313   0.1626
  -2.250   0.5921   0.01981   0.00950  -0.1914   0.5252   0.1871
  -2.000   0.6235   0.01989   0.00951  -0.1921   0.5197   0.2101
  -1.750   0.6548   0.02001   0.00953  -0.1928   0.5148   0.2313
  -1.500   0.6855   0.02015   0.00959  -0.1933   0.5100   0.2516
  -1.250   0.7152   0.02027   0.00971  -0.1936   0.5047   0.2728
  -1.000   0.7451   0.02040   0.00982  -0.1940   0.5000   0.2932
  -0.750   0.7754   0.02054   0.00991  -0.1944   0.4961   0.3100
  -0.500   0.8062   0.02069   0.00999  -0.1949   0.4926   0.3252
  -0.250   0.8350   0.02080   0.01013  -0.1950   0.4882   0.3412
   0.000   0.8641   0.02095   0.01026  -0.1951   0.4838   0.3585
   0.250   0.8934   0.02110   0.01042  -0.1953   0.4799   0.3769
   0.500   0.9232   0.02128   0.01057  -0.1956   0.4764   0.3969
   0.750   0.9536   0.02152   0.01075  -0.1960   0.4733   0.4194
   1.000   0.9811   0.02170   0.01105  -0.1959   0.4693   0.4425
   1.250   1.0088   0.02191   0.01134  -0.1957   0.4653   0.4675
   1.500   1.0368   0.02214   0.01159  -0.1956   0.4616   0.4953
   1.750   1.0649   0.02238   0.01184  -0.1956   0.4582   0.5242
   2.000   1.0935   0.02265   0.01209  -0.1955   0.4553   0.5549
   2.250   1.1197   0.02294   0.01246  -0.1951   0.4520   0.5853
   2.500   1.1450   0.02322   0.01285  -0.1945   0.4484   0.6170
   2.750   1.1698   0.02349   0.01322  -0.1938   0.4449   0.6493
   3.000   1.1947   0.02375   0.01353  -0.1930   0.4416   0.6828
   3.250   1.2195   0.02400   0.01381  -0.1922   0.4386   0.7190
   3.500   1.2439   0.02425   0.01406  -0.1913   0.4360   0.7583
   3.750   1.2629   0.02449   0.01444  -0.1894   0.4331   0.8028
   4.000   1.2751   0.02461   0.01476  -0.1860   0.4299   0.8689
   4.250   1.2949   0.02482   0.01503  -0.1844   0.4265   1.0000
   4.500   1.3228   0.02526   0.01542  -0.1846   0.4231   1.0000
   4.750   1.3514   0.02569   0.01576  -0.1848   0.4200   1.0000
   5.000   1.3809   0.02614   0.01612  -0.1852   0.4175   1.0000
   5.250   1.4065   0.02669   0.01669  -0.1850   0.4147   1.0000
   5.500   1.4286   0.02730   0.01739  -0.1842   0.4113   1.0000
   5.750   1.4518   0.02786   0.01803  -0.1835   0.4078   1.0000
   6.000   1.4762   0.02837   0.01854  -0.1830   0.4046   1.0000
   6.250   1.5022   0.02883   0.01897  -0.1828   0.4016   1.0000
   6.500   1.5299   0.02927   0.01936  -0.1828   0.3990   1.0000
   6.750   1.5523   0.02991   0.02005  -0.1821   0.3961   1.0000
   7.000   1.5695   0.03068   0.02099  -0.1805   0.3926   1.0000
   7.250   1.5888   0.03139   0.02182  -0.1792   0.3893   1.0000
   7.500   1.6101   0.03202   0.02250  -0.1783   0.3863   1.0000
   7.750   1.6336   0.03254   0.02303  -0.1777   0.3835   1.0000
   8.000   1.6599   0.03299   0.02346  -0.1775   0.3811   1.0000
   8.250   1.6791   0.03372   0.02427  -0.1763   0.3781   1.0000
   8.500   1.6882   0.03477   0.02555  -0.1736   0.3743   1.0000
   8.750   1.7017   0.03569   0.02660  -0.1715   0.3711   1.0000
   9.000   1.7182   0.03646   0.02748  -0.1699   0.3682   1.0000
   9.250   1.7388   0.03706   0.02812  -0.1689   0.3656   1.0000
   9.500   1.7640   0.03749   0.02854  -0.1686   0.3633   1.0000
   9.750   1.7737   0.03851   0.02969  -0.1661   0.3603   1.0000
  10.000   1.7656   0.04010   0.03155  -0.1611   0.3565   1.0000
  10.250   1.7665   0.04148   0.03310  -0.1576   0.3533   1.0000
  10.500   1.7745   0.04256   0.03429  -0.1550   0.3505   1.0000
  10.750   1.7917   0.04321   0.03499  -0.1537   0.3479   1.0000
  11.000   1.8185   0.04347   0.03525  -0.1536   0.3457   1.0000
  11.250   1.7934   0.04631   0.03837  -0.1476   0.3419   1.0000
  11.500   1.7599   0.05007   0.04242  -0.1419   0.3373   1.0000
  11.750   1.7589   0.05180   0.04426  -0.1395   0.3333   1.0000
  12.000   1.8023   0.05006   0.04240  -0.1401   0.3296   1.0000
  12.250   1.7302   0.05799   0.05073  -0.1343   0.3242   1.0000
  12.500   1.6175   0.07343   0.06651  -0.1333   0.3152   1.0000
  12.750   1.7075   0.06476   0.05772  -0.1317   0.3142   1.0000
<< Back to FX 73-CL2-152 (fx73cl2152-il)

Polar data table (+)

Polar graphs


<< Back to FX 73-CL2-152 (fx73cl2152-il)