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WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il)
Reynolds number: 200,000
Max Cl/Cd: 56.07 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx72150b-il-200000.txt
Download as CSV file: xf-fx72150b-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.2932   0.10010   0.09529  -0.1570   0.7744   0.0309
 -10.000   0.2985   0.09840   0.09354  -0.1586   0.7705   0.0315
  -9.750   0.2965   0.09761   0.09281  -0.1601   0.7648   0.0317
  -9.500   0.3087   0.09440   0.08958  -0.1604   0.7601   0.0320
  -9.250   0.3246   0.09125   0.08636  -0.1604   0.7565   0.0327
  -9.000   0.3337   0.08919   0.08430  -0.1609   0.7519   0.0333
  -8.750   0.3422   0.08719   0.08231  -0.1614   0.7471   0.0342
  -8.500   0.3507   0.08509   0.08017  -0.1623   0.7432   0.0352
  -8.250   0.3569   0.08324   0.07828  -0.1636   0.7395   0.0365
  -8.000   0.3566   0.08210   0.07720  -0.1649   0.7340   0.0369
  -7.750   0.3570   0.08026   0.07537  -0.1666   0.7296   0.0373
  -7.500   0.3787   0.07694   0.07195  -0.1656   0.7265   0.0382
  -7.250   0.3889   0.07509   0.07010  -0.1657   0.7224   0.0393
  -7.000   0.3953   0.07342   0.06846  -0.1659   0.7176   0.0411
  -6.750   0.3935   0.07217   0.06723  -0.1676   0.7134   0.0429
  -6.500   0.3875   0.07126   0.06632  -0.1703   0.7099   0.0433
  -6.250   0.4029   0.06820   0.06325  -0.1680   0.7066   0.0440
  -6.000   0.4128   0.06646   0.06155  -0.1669   0.7024   0.0450
  -5.750   0.4213   0.06481   0.05990  -0.1671   0.6987   0.0462
  -5.500   0.4316   0.06295   0.05801  -0.1686   0.6957   0.0478
  -5.250   0.4495   0.06009   0.05509  -0.1818   0.6926   0.0505
  -5.000   0.4571   0.05759   0.05268  -0.1821   0.6887   0.0510
  -4.750   0.4649   0.05621   0.05133  -0.1782   0.6853   0.0519
  -4.500   0.4797   0.05451   0.04961  -0.1784   0.6823   0.0535
  -4.250   0.5020   0.05206   0.04710  -0.1829   0.6797   0.0563
  -4.000   0.5500   0.04597   0.04081  -0.2007   0.6774   0.0608
  -3.750   0.5612   0.04515   0.04007  -0.1986   0.6743   0.0625
  -3.500   0.6176   0.03968   0.03425  -0.2155   0.6708   0.0713
  -3.250   0.6344   0.03844   0.03309  -0.2145   0.6679   0.0735
  -3.000   0.6856   0.03506   0.02931  -0.2244   0.6653   0.0849
  -2.750   0.7127   0.03381   0.02804  -0.2255   0.6631   0.0921
  -2.500   0.7550   0.03158   0.02555  -0.2310   0.6611   0.1049
  -2.250   0.7897   0.03005   0.02385  -0.2346   0.6585   0.1197
  -2.000   0.8557   0.02504   0.01760  -0.2421   0.6559   0.0573
  -1.750   0.8917   0.02357   0.01564  -0.2438   0.6532   0.0499
  -1.500   0.9232   0.02271   0.01459  -0.2449   0.6509   0.0495
  -1.250   0.9546   0.02207   0.01381  -0.2460   0.6489   0.0526
  -1.000   0.9862   0.02159   0.01326  -0.2469   0.6471   0.0550
  -0.750   1.0188   0.02121   0.01278  -0.2479   0.6454   0.0582
  -0.500   1.0516   0.02094   0.01251  -0.2493   0.6437   0.0661
  -0.250   1.0757   0.02103   0.01272  -0.2493   0.6406   0.0767
   0.000   1.1050   0.02093   0.01278  -0.2504   0.6378   0.1240
   0.250   1.1348   0.02077   0.01358  -0.2514   0.6354   0.5513
   0.500   1.1595   0.02118   0.01397  -0.2508   0.6334   0.5923
   0.750   1.1845   0.02155   0.01432  -0.2503   0.6317   0.6252
   1.000   1.2097   0.02185   0.01461  -0.2497   0.6302   0.6548
   1.250   1.2357   0.02211   0.01486  -0.2493   0.6289   0.6816
   1.500   1.2621   0.02251   0.01521  -0.2495   0.6274   0.6945
   1.750   1.2764   0.02334   0.01614  -0.2479   0.6245   0.7024
   2.000   1.2954   0.02399   0.01683  -0.2470   0.6218   0.7104
   2.250   1.3171   0.02452   0.01737  -0.2466   0.6196   0.7174
   2.500   1.3412   0.02499   0.01782  -0.2465   0.6178   0.7252
   2.750   1.3668   0.02534   0.01817  -0.2467   0.6163   0.7335
   3.000   1.3947   0.02565   0.01845  -0.2472   0.6149   0.7410
   3.250   1.4234   0.02592   0.01870  -0.2478   0.6137   0.7489
   3.500   1.4531   0.02624   0.01899  -0.2486   0.6126   0.7578
   3.750   1.4621   0.02760   0.02047  -0.2465   0.6103   0.7672
   4.000   1.4061   0.03228   0.02550  -0.2353   0.6033   0.7743
   4.500   1.4318   0.03417   0.02752  -0.2320   0.5994   0.8070
   4.750   1.4545   0.03407   0.02757  -0.2312   0.5982   0.9385
   5.000   1.4934   0.03401   0.02746  -0.2334   0.5974   1.0000
   5.250   1.5345   0.03384   0.02723  -0.2359   0.5966   1.0000
   5.500   1.5748   0.03373   0.02705  -0.2383   0.5959   1.0000
   5.750   1.0461   0.08561   0.08002  -0.1953   0.5372   1.0000
   6.000   1.0758   0.08581   0.08015  -0.1957   0.5355   1.0000
   6.250   1.1094   0.08547   0.07973  -0.1962   0.5343   1.0000
   6.500   1.0945   0.09004   0.08434  -0.1946   0.5237   1.0000
   6.750   1.1182   0.09061   0.08487  -0.1946   0.5209   1.0000
   7.000   1.1455   0.09084   0.08506  -0.1946   0.5193   1.0000
   7.250   1.1744   0.09084   0.08502  -0.1947   0.5182   1.0000
   7.500   1.1535   0.09646   0.09071  -0.1932   0.5073   1.0000
   7.750   1.1782   0.09678   0.09100  -0.1931   0.5049   1.0000
   8.000   1.2065   0.09666   0.09088  -0.1930   0.5035   1.0000
   8.250   1.2356   0.09648   0.09068  -0.1929   0.5024   1.0000
   8.500   1.2655   0.09622   0.09042  -0.1929   0.5017   1.0000
   8.750   1.2956   0.09593   0.09015  -0.1928   0.5010   1.0000
   9.000   1.2664   0.10244   0.09672  -0.1913   0.4877   1.0000
   9.250   1.2966   0.10192   0.09623  -0.1911   0.4868   1.0000
   9.500   1.3273   0.10133   0.09565  -0.1910   0.4861   1.0000
   9.750   1.3585   0.10066   0.09500  -0.1908   0.4855   1.0000
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