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WORTMANN FX 049-915 AIRFOIL (fx049915-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 049-915 AIRFOIL (fx049915-il)
Reynolds number: 500,000
Max Cl/Cd: 113.48 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx049915-il-500000.txt
Download as CSV file: xf-fx049915-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1168   0.09032   0.08612  -0.0519   0.5000   0.0284
 -10.000  -0.1337   0.08425   0.08009  -0.0563   0.4999   0.0297
  -9.750  -0.1395   0.07935   0.07521  -0.0587   0.4994   0.0299
  -9.500  -0.1384   0.07514   0.07101  -0.0592   0.4987   0.0302
  -9.250  -0.1286   0.07282   0.06868  -0.0588   0.4978   0.0305
  -9.000  -0.1155   0.07140   0.06723  -0.0583   0.4968   0.0314
  -8.750  -0.1150   0.06798   0.06382  -0.0593   0.4961   0.0319
  -8.500  -0.4280   0.02921   0.02361  -0.0699   0.5023   0.0210
  -8.250  -0.4311   0.02453   0.01832  -0.0664   0.5016   0.0216
  -8.000  -0.4121   0.02346   0.01711  -0.0652   0.5004   0.0220
  -7.750  -0.3896   0.02297   0.01655  -0.0643   0.4992   0.0227
  -7.500  -0.3700   0.02169   0.01503  -0.0631   0.4981   0.0235
  -7.250  -0.3493   0.02046   0.01351  -0.0618   0.4970   0.0245
  -7.000  -0.3277   0.01931   0.01206  -0.0607   0.4959   0.0253
  -6.750  -0.3044   0.01877   0.01148  -0.0600   0.4948   0.0265
  -6.500  -0.2795   0.01859   0.01124  -0.0594   0.4934   0.0275
  -6.250  -0.2547   0.01811   0.01063  -0.0587   0.4926   0.0291
  -6.000  -0.2308   0.01725   0.00962  -0.0579   0.4918   0.0305
  -5.750  -0.2050   0.01712   0.00951  -0.0574   0.4909   0.0319
  -5.500  -0.1788   0.01698   0.00933  -0.0569   0.4900   0.0338
  -5.250  -0.1534   0.01651   0.00876  -0.0563   0.4889   0.0360
  -5.000  -0.1266   0.01667   0.00897  -0.0560   0.4877   0.0378
  -4.750  -0.1001   0.01659   0.00882  -0.0556   0.4865   0.0403
  -4.500  -0.0742   0.01627   0.00843  -0.0551   0.4854   0.0428
  -4.250  -0.0472   0.01653   0.00870  -0.0548   0.4844   0.0450
  -4.000  -0.0204   0.01661   0.00870  -0.0544   0.4835   0.0480
  -3.750   0.0058   0.01631   0.00836  -0.0540   0.4826   0.0508
  -3.500   0.0324   0.01640   0.00844  -0.0537   0.4817   0.0531
  -3.250   0.0593   0.01648   0.00845  -0.0534   0.4809   0.0563
  -3.000   0.0857   0.01610   0.00800  -0.0530   0.4800   0.0592
  -2.750   0.1122   0.01599   0.00789  -0.0528   0.4792   0.0617
  -2.500   0.1389   0.01601   0.00788  -0.0525   0.4782   0.0646
  -2.250   0.1654   0.01619   0.00799  -0.0522   0.4771   0.0673
  -2.000   0.1918   0.01577   0.00756  -0.0519   0.4766   0.0697
  -1.750   0.2176   0.01537   0.00722  -0.0515   0.4760   0.0722
  -1.500   0.2438   0.01518   0.00704  -0.0511   0.4751   0.0745
  -1.250   0.2701   0.01504   0.00691  -0.0507   0.4742   0.0769
  -1.000   0.2963   0.01491   0.00678  -0.0503   0.4733   0.0787
  -0.750   0.3226   0.01484   0.00670  -0.0500   0.4725   0.0800
  -0.500   0.3474   0.01460   0.00648  -0.0494   0.4717   0.0820
  -0.250   0.3722   0.01441   0.00630  -0.0487   0.4708   0.0845
   0.000   0.3978   0.01434   0.00625  -0.0483   0.4700   0.0867
   0.250   0.4237   0.01430   0.00622  -0.0479   0.4692   0.0890
   0.500   0.4498   0.01429   0.00622  -0.0475   0.4684   0.0917
   0.750   0.4762   0.01432   0.00624  -0.0472   0.4676   0.0938
   1.000   0.5019   0.01426   0.00620  -0.0468   0.4668   0.0975
   1.250   0.5282   0.01424   0.00619  -0.0465   0.4660   0.1023
   1.500   0.5548   0.01427   0.00620  -0.0462   0.4651   0.1077
   1.750   0.5806   0.01424   0.00626  -0.0459   0.4644   0.1357
   2.000   0.7115   0.01249   0.00676  -0.0683   0.4632   0.9908
   2.250   0.7779   0.01275   0.00695  -0.0767   0.4622   1.0000
   2.500   0.8003   0.01314   0.00733  -0.0758   0.4613   1.0000
   2.750   0.8231   0.01328   0.00749  -0.0750   0.4608   1.0000
   3.000   0.8459   0.01344   0.00768  -0.0741   0.4601   1.0000
   3.250   0.8687   0.01359   0.00786  -0.0733   0.4592   1.0000
   3.500   0.8915   0.01377   0.00806  -0.0724   0.4582   1.0000
   3.750   0.9143   0.01399   0.00832  -0.0716   0.4573   1.0000
   4.000   0.9372   0.01422   0.00858  -0.0708   0.4564   1.0000
   4.250   0.9603   0.01446   0.00884  -0.0701   0.4555   1.0000
   4.500   0.9836   0.01467   0.00908  -0.0694   0.4545   1.0000
   4.750   1.0072   0.01486   0.00929  -0.0687   0.4534   1.0000
   5.000   1.0309   0.01505   0.00950  -0.0681   0.4524   1.0000
   5.250   1.0547   0.01525   0.00972  -0.0675   0.4516   1.0000
   5.500   1.0786   0.01546   0.00997  -0.0669   0.4507   1.0000
   5.750   1.1031   0.01563   0.01014  -0.0664   0.4499   1.0000
   6.000   1.1276   0.01579   0.01032  -0.0659   0.4490   1.0000
   6.250   1.1528   0.01595   0.01048  -0.0656   0.4480   1.0000
   6.500   1.1777   0.01629   0.01082  -0.0653   0.4466   1.0000
   6.750   1.1995   0.01651   0.01112  -0.0644   0.4451   1.0000
   7.000   1.2213   0.01672   0.01143  -0.0635   0.4435   1.0000
   7.250   1.2438   0.01691   0.01171  -0.0627   0.4418   1.0000
   7.500   1.2679   0.01695   0.01180  -0.0622   0.4398   1.0000
   7.750   1.2948   0.01662   0.01148  -0.0620   0.4373   1.0000
   8.000   1.3238   0.01609   0.01092  -0.0620   0.4348   1.0000
   8.250   1.3543   0.01569   0.01043  -0.0624   0.4322   1.0000
   8.500   1.3759   0.01559   0.01044  -0.0614   0.4288   1.0000
   8.750   1.3983   0.01547   0.01042  -0.0605   0.4254   1.0000
   9.000   1.4242   0.01509   0.01006  -0.0601   0.4219   1.0000
   9.250   1.4525   0.01456   0.00947  -0.0600   0.4179   1.0000
   9.500   1.4734   0.01451   0.00956  -0.0589   0.4137   1.0000
   9.750   1.4960   0.01431   0.00945  -0.0581   0.4084   1.0000
  10.000   1.5204   0.01398   0.00909  -0.0574   0.4025   1.0000
  10.250   1.5408   0.01391   0.00919  -0.0563   0.3934   1.0000
  10.500   1.5620   0.01383   0.00917  -0.0552   0.3803   1.0000
  10.750   1.5797   0.01392   0.00923  -0.0537   0.3573   1.0000
  11.000   1.5773   0.01496   0.00998  -0.0492   0.3097   1.0000
  11.250   1.5603   0.01675   0.01157  -0.0428   0.2718   1.0000
  11.500   1.5356   0.01856   0.01329  -0.0356   0.2493   1.0000
  11.750   1.5097   0.02147   0.01620  -0.0312   0.2308   1.0000
  12.000   1.4836   0.02651   0.02132  -0.0309   0.2187   1.0000
  12.250   1.4536   0.03241   0.02728  -0.0309   0.2078   1.0000
  12.500   1.4243   0.03767   0.03257  -0.0300   0.1969   1.0000
  12.750   1.3954   0.04271   0.03760  -0.0290   0.1848   1.0000
  13.000   1.3697   0.04745   0.04231  -0.0281   0.1719   1.0000
  13.250   1.3444   0.05228   0.04709  -0.0274   0.1561   1.0000
  13.500   1.3222   0.05714   0.05185  -0.0271   0.1377   1.0000
  13.750   1.3032   0.06178   0.05637  -0.0268   0.1171   1.0000
  14.000   1.2872   0.06624   0.06072  -0.0267   0.0987   1.0000
  14.250   1.2735   0.07051   0.06486  -0.0267   0.0798   1.0000
  14.500   1.2640   0.07439   0.06865  -0.0267   0.0633   1.0000
  14.750   1.2501   0.07883   0.07291  -0.0269   0.0408   1.0000
  15.000   1.2418   0.08272   0.07672  -0.0270   0.0315   1.0000
  15.250   1.2406   0.08579   0.07981  -0.0272   0.0283   1.0000
  15.500   1.2388   0.08903   0.08309  -0.0274   0.0257   1.0000
  15.750   1.2395   0.09195   0.08606  -0.0277   0.0245   1.0000
  16.000   1.2382   0.09514   0.08928  -0.0280   0.0230   1.0000
  16.250   1.2345   0.09876   0.09295  -0.0284   0.0221   1.0000
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