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WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il)
Reynolds number: 100,000
Max Cl/Cd: 39.67 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx72150b-il-100000-n5.txt
Download as CSV file: xf-fx72150b-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 72-MS-150B 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   0.2641   0.10551   0.09926  -0.1490   0.7614   0.0401
 -10.000   0.2719   0.10338   0.09709  -0.1498   0.7568   0.0412
  -9.750   0.2769   0.10170   0.09542  -0.1509   0.7520   0.0425
  -9.500   0.2766   0.10082   0.09457  -0.1522   0.7466   0.0432
  -9.250   0.2888   0.09756   0.09127  -0.1524   0.7428   0.0440
  -9.000   0.3005   0.09502   0.08869  -0.1526   0.7390   0.0451
  -8.750   0.3083   0.09311   0.08679  -0.1529   0.7339   0.0468
  -8.500   0.3148   0.09123   0.08489  -0.1535   0.7296   0.0485
  -8.250   0.3184   0.08975   0.08338  -0.1548   0.7262   0.0499
  -8.000   0.3176   0.08883   0.08250  -0.1560   0.7216   0.0504
  -7.750   0.3148   0.08789   0.08161  -0.1569   0.7166   0.0506
  -7.500   0.3326   0.08405   0.07774  -0.1561   0.7134   0.0514
  -7.250   0.3460   0.08154   0.07517  -0.1561   0.7104   0.0525
  -7.000   0.3537   0.07967   0.07329  -0.1560   0.7068   0.0538
  -6.750   0.3572   0.07818   0.07186  -0.1556   0.7020   0.0551
  -6.500   0.3603   0.07663   0.07033  -0.1555   0.6981   0.0566
  -6.250   0.3575   0.07554   0.06924  -0.1557   0.6947   0.0583
  -6.000   0.3531   0.07478   0.06852  -0.1581   0.6909   0.0592
  -5.750   0.3538   0.07346   0.06727  -0.1611   0.6858   0.0595
  -5.500   0.3631   0.07066   0.06448  -0.1579   0.6827   0.0602
  -5.250   0.3754   0.06843   0.06220  -0.1566   0.6798   0.0615
  -5.000   0.3888   0.06629   0.06001  -0.1578   0.6774   0.0627
  -4.750   0.3920   0.06494   0.05872  -0.1576   0.6731   0.0640
  -4.500   0.3982   0.06331   0.05712  -0.1586   0.6690   0.0657
  -4.250   0.4375   0.05827   0.05195  -0.1785   0.6654   0.0703
  -4.000   0.4372   0.05754   0.05128  -0.1698   0.6633   0.0722
  -3.750   0.4576   0.05554   0.04921  -0.1711   0.6613   0.0759
  -3.250   0.5761   0.03953   0.03222  -0.2063   0.6547   0.0369
  -3.000   0.6133   0.03704   0.02946  -0.2114   0.6517   0.0362
  -2.750   0.6606   0.03419   0.02613  -0.2179   0.6495   0.0356
  -2.500   0.7078   0.03179   0.02316  -0.2235   0.6475   0.0354
  -2.250   0.7538   0.02991   0.02057  -0.2279   0.6459   0.0372
  -2.000   0.7894   0.02900   0.01950  -0.2301   0.6444   0.0393
  -1.750   0.8118   0.02869   0.01903  -0.2301   0.6409   0.0403
  -1.500   0.8344   0.02844   0.01862  -0.2298   0.6373   0.0413
  -1.250   0.8617   0.02803   0.01801  -0.2302   0.6346   0.0429
  -1.000   0.8907   0.02770   0.01766  -0.2309   0.6324   0.0465
  -0.750   0.9213   0.02737   0.01722  -0.2316   0.6307   0.0511
  -0.500   0.9538   0.02704   0.01685  -0.2328   0.6292   0.0569
  -0.250   0.9890   0.02676   0.01647  -0.2345   0.6280   0.0670
   0.000   0.9961   0.02785   0.01768  -0.2322   0.6237   0.0759
   0.250   1.0154   0.02839   0.01830  -0.2318   0.6205   0.1023
   0.500   1.0496   0.02806   0.01892  -0.2343   0.6182   0.4632
   0.750   1.0718   0.02853   0.01947  -0.2333   0.6161   0.5636
   1.000   1.0949   0.02887   0.01982  -0.2321   0.6145   0.6263
   1.250   1.1209   0.02901   0.01991  -0.2316   0.6131   0.6629
   1.500   1.1529   0.02906   0.01979  -0.2324   0.6120   0.6761
   1.750   1.0960   0.03327   0.02435  -0.2215   0.6026   0.6789
   2.000   1.1130   0.03411   0.02510  -0.2205   0.6003   0.6886
   2.250   1.1373   0.03451   0.02542  -0.2203   0.5988   0.6975
   2.500   1.1658   0.03475   0.02554  -0.2208   0.5976   0.7074
   2.750   1.1965   0.03480   0.02550  -0.2215   0.5967   0.7152
   3.000   1.2298   0.03478   0.02537  -0.2225   0.5958   0.7242
   5.000   1.1127   0.06545   0.05695  -0.1968   0.5475   1.0000
   5.500   1.1075   0.07219   0.06372  -0.1943   0.5342   1.0000
   5.750   1.1326   0.07277   0.06423  -0.1944   0.5331   1.0000
   6.000   1.1582   0.07326   0.06465  -0.1944   0.5322   1.0000
   6.500   1.1433   0.08135   0.07283  -0.1918   0.5185   1.0000
   6.750   1.1681   0.08184   0.07329  -0.1917   0.5172   1.0000
   7.000   1.1935   0.08227   0.07368  -0.1917   0.5163   1.0000
   7.500   1.1845   0.08976   0.08129  -0.1895   0.5030   1.0000
   7.750   1.2104   0.08997   0.08149  -0.1894   0.5017   1.0000
   8.250   1.2159   0.09546   0.08707  -0.1877   0.4886   1.0000
   8.500   1.2399   0.09581   0.08743  -0.1875   0.4871   1.0000
   8.750   1.2649   0.09608   0.08770  -0.1873   0.4860   1.0000
   9.250   1.2661   0.10229   0.09407  -0.1858   0.4723   1.0000
   9.500   1.2908   0.10245   0.09426  -0.1856   0.4710   1.0000
  10.000   1.2937   0.10859   0.10055  -0.1844   0.4575   1.0000
  10.250   1.3180   0.10867   0.10070  -0.1841   0.4559   1.0000
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