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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 50,000
Max Cl/Cd: 36.44 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-davis-il-50000-n5.txt
Download as CSV file: xf-davis-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Davis AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3705   0.10228   0.09545  -0.0435   1.0000   0.0530
  -9.250  -0.3774   0.09856   0.09183  -0.0440   1.0000   0.0521
  -9.000  -0.3871   0.09468   0.08807  -0.0445   1.0000   0.0513
  -8.750  -0.4017   0.09051   0.08405  -0.0451   1.0000   0.0502
  -8.500  -0.4355   0.08426   0.07797  -0.0478   1.0000   0.0482
  -8.250  -0.4504   0.08093   0.07476  -0.0472   1.0000   0.0480
  -8.000  -0.4627   0.07704   0.07093  -0.0473   1.0000   0.0477
  -7.750  -0.4755   0.07281   0.06674  -0.0475   1.0000   0.0475
  -7.500  -0.4879   0.06875   0.06268  -0.0473   1.0000   0.0472
  -7.250  -0.4994   0.06441   0.05826  -0.0472   1.0000   0.0471
  -7.000  -0.5080   0.05991   0.05359  -0.0471   1.0000   0.0469
  -6.750  -0.5127   0.05532   0.04874  -0.0470   1.0000   0.0469
  -6.500  -0.5132   0.05063   0.04363  -0.0468   1.0000   0.0472
  -6.250  -0.5086   0.04620   0.03857  -0.0465   1.0000   0.0481
  -6.000  -0.4988   0.04383   0.03612  -0.0455   1.0000   0.0501
  -5.750  -0.4795   0.04147   0.03347  -0.0460   0.9976   0.0532
  -5.500  -0.4506   0.03800   0.02935  -0.0480   0.9924   0.0562
  -5.250  -0.4184   0.03502   0.02555  -0.0497   0.9871   0.0601
  -5.000  -0.3867   0.03343   0.02387  -0.0515   0.9803   0.0665
  -4.750  -0.3522   0.03150   0.02134  -0.0530   0.9736   0.0731
  -4.500  -0.3176   0.03036   0.02011  -0.0549   0.9667   0.0843
  -4.250  -0.2842   0.02915   0.01875  -0.0562   0.9595   0.0956
  -4.000  -0.2521   0.02825   0.01771  -0.0573   0.9522   0.1162
  -3.750  -0.2157   0.02733   0.01681  -0.0592   0.9466   0.1513
  -3.500  -0.1868   0.02678   0.01619  -0.0598   0.9388   0.1914
  -3.250  -0.1560   0.02670   0.01612  -0.0610   0.9316   0.2427
  -3.000  -0.1259   0.02652   0.01596  -0.0619   0.9243   0.2884
  -2.750  -0.0959   0.02622   0.01557  -0.0625   0.9169   0.3191
  -2.500  -0.0626   0.02592   0.01521  -0.0637   0.9102   0.3521
  -2.250  -0.0340   0.02567   0.01495  -0.0641   0.9025   0.3865
  -2.000  -0.0012   0.02535   0.01465  -0.0652   0.8957   0.4284
  -1.750   0.0261   0.02505   0.01444  -0.0652   0.8877   0.4777
  -1.500   0.0566   0.02456   0.01424  -0.0657   0.8810   0.5475
  -1.250   0.0818   0.02390   0.01424  -0.0644   0.8737   0.6843
  -1.000   0.1558   0.02361   0.01406  -0.0731   0.8699   1.0000
  -0.750   0.1944   0.02369   0.01380  -0.0753   0.8639   1.0000
  -0.500   0.2166   0.02391   0.01379  -0.0746   0.8531   1.0000
  -0.250   0.2463   0.02407   0.01373  -0.0751   0.8447   1.0000
   0.000   0.2779   0.02418   0.01365  -0.0760   0.8366   1.0000
   0.250   0.3038   0.02435   0.01366  -0.0757   0.8262   1.0000
   0.500   0.3444   0.02424   0.01338  -0.0778   0.8194   1.0000
   0.750   0.3710   0.02428   0.01331  -0.0775   0.8071   1.0000
   1.000   0.4016   0.02420   0.01311  -0.0776   0.7949   1.0000
   1.250   0.4342   0.02402   0.01284  -0.0779   0.7829   1.0000
   1.500   0.4701   0.02378   0.01250  -0.0788   0.7725   1.0000
   1.750   0.5016   0.02369   0.01237  -0.0790   0.7617   1.0000
   2.000   0.5274   0.02381   0.01244  -0.0784   0.7499   1.0000
   2.250   0.5559   0.02386   0.01246  -0.0783   0.7391   1.0000
   2.500   0.5926   0.02368   0.01225  -0.0793   0.7303   1.0000
   2.750   0.6170   0.02384   0.01242  -0.0785   0.7174   1.0000
   3.000   0.6420   0.02399   0.01257  -0.0777   0.7044   1.0000
   3.250   0.6675   0.02411   0.01273  -0.0770   0.6912   1.0000
   3.500   0.6930   0.02424   0.01287  -0.0763   0.6776   1.0000
   3.750   0.7179   0.02436   0.01302  -0.0754   0.6635   1.0000
   4.000   0.7420   0.02451   0.01323  -0.0745   0.6488   1.0000
   4.250   0.7655   0.02466   0.01343  -0.0734   0.6335   1.0000
   4.500   0.7889   0.02481   0.01363  -0.0723   0.6178   1.0000
   4.750   0.8131   0.02495   0.01385  -0.0713   0.6020   1.0000
   5.000   0.8382   0.02509   0.01404  -0.0704   0.5863   1.0000
   5.250   0.8640   0.02524   0.01423  -0.0697   0.5706   1.0000
   5.500   0.8901   0.02545   0.01448  -0.0690   0.5549   1.0000
   5.750   0.9158   0.02574   0.01485  -0.0684   0.5394   1.0000
   6.000   0.9408   0.02613   0.01529  -0.0677   0.5242   1.0000
   6.250   0.9649   0.02661   0.01586  -0.0670   0.5096   1.0000
   6.500   0.9881   0.02718   0.01654  -0.0662   0.4957   1.0000
   6.750   1.0106   0.02780   0.01733  -0.0653   0.4825   1.0000
   7.000   1.0334   0.02844   0.01812  -0.0645   0.4703   1.0000
   7.250   1.0583   0.02904   0.01886  -0.0640   0.4594   1.0000
   7.500   1.0775   0.02985   0.01989  -0.0628   0.4485   1.0000
   7.750   1.0970   0.03067   0.02094  -0.0616   0.4383   1.0000
   8.000   1.1214   0.03134   0.02186  -0.0610   0.4293   1.0000
   8.250   1.1388   0.03218   0.02298  -0.0595   0.4190   1.0000
   8.500   1.1537   0.03248   0.02339  -0.0571   0.4023   1.0000
   8.750   1.1563   0.03287   0.02384  -0.0529   0.3800   1.0000
   9.000   1.1563   0.03316   0.02403  -0.0482   0.3539   1.0000
   9.250   1.1495   0.03384   0.02454  -0.0429   0.3263   1.0000
   9.500   1.1387   0.03503   0.02566  -0.0380   0.2971   1.0000
   9.750   1.1297   0.03654   0.02721  -0.0340   0.2667   1.0000
  10.000   1.1232   0.03833   0.02912  -0.0309   0.2306   1.0000
  10.250   1.1134   0.04068   0.03129  -0.0281   0.1660   1.0000
  10.500   1.0957   0.04420   0.03418  -0.0256   0.1131   1.0000
  10.750   1.0801   0.04821   0.03789  -0.0240   0.0891   1.0000
  11.000   1.0677   0.05221   0.04184  -0.0229   0.0760   1.0000
  11.250   1.0583   0.05609   0.04577  -0.0222   0.0681   1.0000
  11.500   1.0481   0.06022   0.04995  -0.0219   0.0622   1.0000
  11.750   1.0401   0.06423   0.05403  -0.0218   0.0581   1.0000
  12.000   1.0343   0.06809   0.05810  -0.0219   0.0537   1.0000
  12.250   1.0289   0.07200   0.06210  -0.0222   0.0508   1.0000
  12.500   1.0220   0.07615   0.06624  -0.0226   0.0483   1.0000
  12.750   1.0224   0.07941   0.06971  -0.0225   0.0456   1.0000
  13.000   1.0243   0.08245   0.07290  -0.0223   0.0437   1.0000
  13.250   1.0269   0.08543   0.07600  -0.0220   0.0417   1.0000
  13.500   1.0298   0.08838   0.07901  -0.0219   0.0398   1.0000
  13.750   1.0345   0.09108   0.08174  -0.0215   0.0379   1.0000
  14.000   1.0407   0.09394   0.08489  -0.0212   0.0361   1.0000
  14.250   1.0453   0.09714   0.08832  -0.0213   0.0345   1.0000
  14.500   1.0499   0.10042   0.09184  -0.0213   0.0337   1.0000
  14.750   1.0518   0.10427   0.09591  -0.0219   0.0330   1.0000
  15.000   1.0506   0.10870   0.10058  -0.0230   0.0326   1.0000
  15.250   1.0461   0.11382   0.10592  -0.0249   0.0323   1.0000
  15.500   1.0383   0.11968   0.11201  -0.0275   0.0321   1.0000
  15.750   1.0275   0.12637   0.11891  -0.0309   0.0321   1.0000
  16.000   1.0133   0.13422   0.12699  -0.0353   0.0323   1.0000
  16.250   0.9932   0.14424   0.13723  -0.0414   0.0329   1.0000
  16.500   0.9714   0.15578   0.14890  -0.0484   0.0337   1.0000
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