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WORTMANN FX 049-915 AIRFOIL (fx049915-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 049-915 AIRFOIL (fx049915-il)
Reynolds number: 200,000
Max Cl/Cd: 49.24 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx049915-il-200000-n5.txt
Download as CSV file: xf-fx049915-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 049-915 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1648   0.10712   0.10120  -0.0552   0.5098   0.0188
 -10.750  -0.1637   0.10320   0.09728  -0.0569   0.5091   0.0184
 -10.500  -0.1683   0.09810   0.09220  -0.0591   0.5086   0.0179
 -10.250  -0.1529   0.09755   0.09166  -0.0591   0.5076   0.0197
 -10.000  -0.1509   0.09407   0.08822  -0.0605   0.5067   0.0197
  -9.750  -0.1550   0.08939   0.08357  -0.0625   0.5061   0.0187
  -9.500  -0.1503   0.08674   0.08095  -0.0635   0.5052   0.0194
  -9.250  -0.1525   0.08279   0.07705  -0.0652   0.5044   0.0193
  -9.000  -0.1556   0.07884   0.07314  -0.0669   0.5037   0.0192
  -8.750  -0.1614   0.07463   0.06899  -0.0688   0.5030   0.0191
  -8.500  -0.1701   0.07034   0.06475  -0.0710   0.5023   0.0191
  -8.250  -0.1891   0.06557   0.06004  -0.0733   0.5019   0.0190
  -8.000  -0.2015   0.06079   0.05524  -0.0751   0.5013   0.0191
  -7.750  -0.2160   0.05448   0.04881  -0.0767   0.5008   0.0189
  -7.500  -0.2216   0.04919   0.04334  -0.0769   0.5002   0.0191
  -7.250  -0.2219   0.04441   0.03832  -0.0762   0.4994   0.0196
  -7.000  -0.2183   0.04000   0.03359  -0.0749   0.4987   0.0206
  -6.750  -0.2183   0.03416   0.02723  -0.0726   0.4980   0.0218
  -6.500  -0.2160   0.02824   0.02053  -0.0696   0.4973   0.0229
  -6.250  -0.2016   0.02526   0.01705  -0.0678   0.4964   0.0242
  -6.000  -0.1781   0.02489   0.01657  -0.0671   0.4953   0.0257
  -5.750  -0.1537   0.02463   0.01619  -0.0665   0.4942   0.0273
  -5.500  -0.1300   0.02384   0.01518  -0.0658   0.4931   0.0297
  -5.250  -0.1070   0.02233   0.01327  -0.0648   0.4922   0.0326
  -5.000  -0.0825   0.02160   0.01241  -0.0641   0.4910   0.0352
  -4.750  -0.0566   0.02189   0.01271  -0.0638   0.4899   0.0377
  -4.500  -0.0309   0.02163   0.01234  -0.0633   0.4888   0.0416
  -4.250  -0.0052   0.02098   0.01144  -0.0627   0.4878   0.0463
  -4.000   0.0204   0.02115   0.01163  -0.0623   0.4867   0.0491
  -3.750   0.0463   0.02104   0.01139  -0.0619   0.4856   0.0534
  -3.500   0.0725   0.02089   0.01103  -0.0614   0.4846   0.0574
  -3.250   0.0980   0.02053   0.01068  -0.0610   0.4836   0.0607
  -3.000   0.1239   0.02035   0.01043  -0.0607   0.4826   0.0644
  -2.750   0.1502   0.02018   0.01011  -0.0603   0.4817   0.0684
  -2.500   0.1767   0.02006   0.00982  -0.0599   0.4808   0.0707
  -2.250   0.2028   0.01955   0.00933  -0.0596   0.4799   0.0724
  -2.000   0.2289   0.01926   0.00901  -0.0593   0.4789   0.0741
  -1.750   0.2550   0.01903   0.00874  -0.0589   0.4780   0.0758
  -1.500   0.2811   0.01888   0.00852  -0.0586   0.4772   0.0781
  -1.250   0.3074   0.01882   0.00837  -0.0582   0.4764   0.0806
  -1.000   0.3323   0.01862   0.00821  -0.0578   0.4757   0.0825
  -0.750   0.3568   0.01851   0.00816  -0.0572   0.4748   0.0839
  -0.500   0.3813   0.01845   0.00814  -0.0566   0.4739   0.0858
  -0.250   0.4059   0.01845   0.00816  -0.0561   0.4729   0.0880
   0.000   0.4307   0.01849   0.00821  -0.0556   0.4719   0.0898
   0.250   0.4552   0.01850   0.00826  -0.0550   0.4709   0.0919
   0.500   0.4800   0.01857   0.00834  -0.0546   0.4699   0.0946
   0.750   0.5051   0.01865   0.00842  -0.0541   0.4688   0.0975
   1.000   0.5300   0.01870   0.00850  -0.0537   0.4676   0.1023
   1.250   0.5551   0.01877   0.00859  -0.0532   0.4665   0.1097
   1.500   0.5796   0.01878   0.00870  -0.0527   0.4656   0.1294
   2.000   0.7422   0.01717   0.00929  -0.0759   0.4637   1.0000
   2.250   0.7654   0.01741   0.00948  -0.0752   0.4630   1.0000
   2.500   0.7888   0.01765   0.00968  -0.0745   0.4623   1.0000
   2.750   0.8124   0.01790   0.00988  -0.0738   0.4616   1.0000
   3.000   0.8363   0.01814   0.01008  -0.0732   0.4609   1.0000
   3.250   0.8604   0.01840   0.01030  -0.0727   0.4602   1.0000
   3.500   0.8813   0.01880   0.01076  -0.0717   0.4590   1.0000
   3.750   0.9015   0.01928   0.01131  -0.0706   0.4577   1.0000
   4.000   0.9218   0.01976   0.01187  -0.0696   0.4565   1.0000
   4.250   0.9421   0.02026   0.01243  -0.0686   0.4552   1.0000
   4.500   0.9628   0.02072   0.01295  -0.0677   0.4538   1.0000
   4.750   0.9840   0.02112   0.01340  -0.0668   0.4523   1.0000
   5.000   1.0055   0.02151   0.01383  -0.0660   0.4511   1.0000
   5.250   1.0271   0.02192   0.01428  -0.0652   0.4500   1.0000
   5.500   1.0491   0.02231   0.01471  -0.0645   0.4490   1.0000
   5.750   1.0719   0.02261   0.01504  -0.0639   0.4480   1.0000
   6.000   1.0953   0.02288   0.01534  -0.0633   0.4471   1.0000
   6.250   1.1191   0.02314   0.01562  -0.0628   0.4463   1.0000
   6.500   1.1428   0.02343   0.01594  -0.0624   0.4455   1.0000
   6.750   1.1671   0.02370   0.01624  -0.0620   0.4448   1.0000
   7.000   1.1759   0.02485   0.01761  -0.0598   0.4421   1.0000
   7.250   1.1837   0.02603   0.01897  -0.0575   0.4389   1.0000
   7.500   1.1992   0.02667   0.01971  -0.0561   0.4365   1.0000
   7.750   1.2187   0.02704   0.02015  -0.0551   0.4347   1.0000
   8.000   1.2404   0.02727   0.02046  -0.0544   0.4333   1.0000
   8.250   1.2635   0.02743   0.02067  -0.0539   0.4321   1.0000
   8.500   1.2878   0.02754   0.02083  -0.0535   0.4311   1.0000
   8.750   1.3140   0.02754   0.02088  -0.0533   0.4302   1.0000
   9.000   1.3071   0.02939   0.02295  -0.0495   0.4265   1.0000
   9.250   1.1590   0.04050   0.03430  -0.0373   0.4105   1.0000
   9.500   1.1940   0.03923   0.03309  -0.0367   0.4112   1.0000
   9.750   1.2332   0.03770   0.03162  -0.0364   0.4118   1.0000
  10.000   1.2829   0.03537   0.02937  -0.0366   0.4120   1.0000
  10.250   1.0796   0.05847   0.05244  -0.0356   0.3758   1.0000
  10.500   1.1009   0.05861   0.05265  -0.0352   0.3743   1.0000
  10.750   1.1277   0.05805   0.05217  -0.0348   0.3732   1.0000
  11.000   1.1579   0.05705   0.05126  -0.0344   0.3723   1.0000
  12.500   1.1822   0.06827   0.06284  -0.0329   0.3233   1.0000
  12.750   1.2022   0.06834   0.06294  -0.0326   0.3123   1.0000
  13.000   1.2292   0.06755   0.06214  -0.0323   0.2989   1.0000
  13.250   1.2767   0.06404   0.05847  -0.0316   0.2770   1.0000
  13.500   1.2934   0.06415   0.05835  -0.0309   0.2490   1.0000
  13.750   1.2907   0.06680   0.06086  -0.0306   0.2246   1.0000
  14.000   1.2805   0.07045   0.06435  -0.0303   0.1977   1.0000
  14.250   1.2665   0.07471   0.06842  -0.0303   0.1714   1.0000
  14.500   1.2509   0.07930   0.07281  -0.0304   0.1454   1.0000
  14.750   1.2362   0.08391   0.07725  -0.0306   0.1229   1.0000
  15.000   1.2273   0.08790   0.08114  -0.0309   0.1060   1.0000
  15.250   1.2193   0.09186   0.08501  -0.0312   0.0902   1.0000
  15.500   1.2114   0.09585   0.08889  -0.0316   0.0705   1.0000
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