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DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DORNIER A-5 AIRFOIL (doa5-il)
Reynolds number: 50,000
Max Cl/Cd: 25.57 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-doa5-il-50000-n5.txt
Download as CSV file: xf-doa5-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DORNIER A-5 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5175   0.10511   0.09728  -0.0593   1.0000   0.0750
 -11.500  -0.5361   0.09961   0.09181  -0.0606   1.0000   0.0746
 -11.250  -0.5598   0.09419   0.08640  -0.0616   1.0000   0.0742
 -11.000  -0.5868   0.08927   0.08147  -0.0619   1.0000   0.0737
 -10.750  -0.6170   0.08489   0.07708  -0.0612   1.0000   0.0732
 -10.500  -0.6484   0.08124   0.07339  -0.0594   1.0000   0.0728
 -10.250  -0.6802   0.07827   0.07037  -0.0566   1.0000   0.0724
 -10.000  -0.7133   0.07590   0.06795  -0.0526   1.0000   0.0721
  -9.750  -0.7424   0.07345   0.06541  -0.0486   1.0000   0.0719
  -9.500  -0.7644   0.07072   0.06252  -0.0451   1.0000   0.0718
  -9.250  -0.7815   0.06786   0.05946  -0.0419   1.0000   0.0718
  -9.000  -0.7933   0.06500   0.05637  -0.0390   1.0000   0.0718
  -8.750  -0.8007   0.06214   0.05324  -0.0364   1.0000   0.0719
  -8.500  -0.8034   0.05937   0.05018  -0.0340   1.0000   0.0721
  -8.250  -0.8024   0.05672   0.04722  -0.0319   1.0000   0.0725
  -8.000  -0.7980   0.05422   0.04439  -0.0300   1.0000   0.0731
  -7.750  -0.7913   0.05188   0.04165  -0.0282   1.0000   0.0742
  -7.500  -0.7823   0.04968   0.03895  -0.0265   1.0000   0.0755
  -7.250  -0.7581   0.04774   0.03696  -0.0272   0.9970   0.0772
  -7.000  -0.7325   0.04610   0.03515  -0.0279   0.9938   0.0787
  -6.750  -0.7076   0.04446   0.03330  -0.0281   0.9907   0.0801
  -6.500  -0.6821   0.04300   0.03161  -0.0282   0.9877   0.0816
  -6.250  -0.6545   0.04178   0.03015  -0.0285   0.9847   0.0842
  -6.000  -0.6267   0.04074   0.02889  -0.0287   0.9815   0.0872
  -5.750  -0.5999   0.03989   0.02812  -0.0285   0.9780   0.0902
  -5.500  -0.5707   0.03927   0.02747  -0.0284   0.9749   0.0935
  -5.250  -0.5397   0.03887   0.02695  -0.0283   0.9723   0.0972
  -5.000  -0.5164   0.03837   0.02648  -0.0272   0.9685   0.1016
  -4.750  -0.4922   0.03791   0.02604  -0.0267   0.9644   0.1076
  -4.500  -0.4652   0.03748   0.02555  -0.0267   0.9606   0.1146
  -4.250  -0.4481   0.03677   0.02492  -0.0256   0.9550   0.1220
  -4.000  -0.4259   0.03610   0.02427  -0.0256   0.9504   0.1325
  -3.750  -0.4060   0.03532   0.02355  -0.0253   0.9453   0.1466
  -3.500  -0.3870   0.03430   0.02264  -0.0252   0.9398   0.1692
  -3.250  -0.3649   0.03248   0.02137  -0.0268   0.9355   0.2309
  -3.000  -0.3676   0.03233   0.02331  -0.0191   0.9287   0.5572
  -2.750  -0.3452   0.03389   0.02475  -0.0163   0.9237   0.6325
  -2.500  -0.3278   0.03541   0.02616  -0.0124   0.9184   0.6670
  -2.250  -0.3094   0.03620   0.02678  -0.0102   0.9130   0.6906
  -2.000  -0.2863   0.03741   0.02787  -0.0074   0.9087   0.7107
  -1.750  -0.2715   0.03834   0.02873  -0.0035   0.9029   0.7323
  -1.500  -0.2554   0.03896   0.02927  -0.0003   0.8970   0.7537
  -1.250  -0.2312   0.03935   0.02954   0.0010   0.8928   0.7694
  -1.000  -0.2154   0.03928   0.02939   0.0029   0.8866   0.7777
  -0.750  -0.1925   0.03913   0.02911   0.0029   0.8808   0.7842
  -0.500  -0.1609   0.03899   0.02881   0.0010   0.8765   0.7887
  -0.250  -0.1463   0.03878   0.02854   0.0026   0.8690   0.7924
   0.000  -0.1188   0.03868   0.02834   0.0017   0.8639   0.7964
   0.250  -0.0940   0.03860   0.02816   0.0011   0.8587   0.8009
   0.500  -0.0726   0.03848   0.02797   0.0011   0.8513   0.8052
   0.750  -0.0345   0.03837   0.02778  -0.0010   0.8455   0.8089
   1.000  -0.0136   0.03813   0.02749  -0.0004   0.8340   0.8139
   1.250   0.0176   0.03787   0.02715  -0.0016   0.8239   0.8190
   1.500   0.0515   0.03755   0.02680  -0.0027   0.8143   0.8227
   1.750   0.0741   0.03738   0.02660  -0.0022   0.8037   0.8273
   2.000   0.1077   0.03716   0.02636  -0.0035   0.7958   0.8323
   2.250   0.1279   0.03709   0.02629  -0.0027   0.7857   0.8376
   2.500   0.1586   0.03688   0.02609  -0.0033   0.7777   0.8427
   2.750   0.1790   0.03684   0.02606  -0.0026   0.7670   0.8484
   3.000   0.2117   0.03661   0.02585  -0.0036   0.7592   0.8531
   3.500   0.2665   0.03623   0.02555  -0.0039   0.7404   0.8631
   3.750   0.2837   0.03628   0.02564  -0.0028   0.7272   0.8686
   4.000   0.3085   0.03609   0.02552  -0.0025   0.7161   0.8736
   4.250   0.3420   0.03566   0.02515  -0.0032   0.7064   0.8786
   4.500   0.3630   0.03557   0.02513  -0.0025   0.6917   0.8837
   4.750   0.3890   0.03523   0.02488  -0.0021   0.6783   0.8888
   5.000   0.4287   0.03429   0.02403  -0.0031   0.6692   0.8941
   5.250   0.4537   0.03379   0.02361  -0.0023   0.6531   0.9001
   5.500   0.4813   0.03306   0.02298  -0.0015   0.6358   0.9065
   5.750   0.5093   0.03239   0.02241  -0.0009   0.6172   0.9131
   6.000   0.5397   0.03170   0.02181  -0.0007   0.5979   0.9193
   6.250   0.5727   0.03104   0.02123  -0.0009   0.5792   0.9259
   6.500   0.6047   0.03064   0.02092  -0.0012   0.5578   0.9322
   6.750   0.6358   0.03036   0.02071  -0.0016   0.5327   0.9392
   7.000   0.6706   0.02998   0.02034  -0.0024   0.5043   0.9461
   7.250   0.7054   0.02971   0.01997  -0.0032   0.4721   0.9543
   7.500   0.7388   0.02970   0.01981  -0.0042   0.4394   0.9638
   8.000   0.7825   0.03060   0.02042  -0.0035   0.3817   1.0000
   8.250   0.8000   0.03139   0.02110  -0.0028   0.3561   1.0000
   8.500   0.8170   0.03227   0.02186  -0.0021   0.3321   1.0000
   8.750   0.8329   0.03326   0.02284  -0.0014   0.3089   1.0000
   9.000   0.8492   0.03429   0.02383  -0.0008   0.2876   1.0000
   9.250   0.8653   0.03534   0.02485  -0.0002   0.2682   1.0000
   9.500   0.8809   0.03644   0.02592   0.0003   0.2506   1.0000
   9.750   0.8965   0.03756   0.02703   0.0008   0.2351   1.0000
  10.000   0.9126   0.03871   0.02812   0.0013   0.2221   1.0000
  10.250   0.9302   0.03985   0.02913   0.0015   0.2110   1.0000
  10.500   0.9506   0.04102   0.03032   0.0016   0.2004   1.0000
  10.750   0.9735   0.04221   0.03153   0.0013   0.1909   1.0000
  11.000   0.9987   0.04338   0.03270   0.0009   0.1824   1.0000
  11.250   1.0232   0.04471   0.03412   0.0006   0.1748   1.0000
  11.500   1.0452   0.04609   0.03559   0.0004   0.1675   1.0000
  11.750   1.0695   0.04754   0.03705   0.0000   0.1610   1.0000
  12.000   1.0856   0.04931   0.03904   0.0002   0.1552   1.0000
  12.250   1.1119   0.05072   0.04040  -0.0004   0.1496   1.0000
  12.500   1.1222   0.05283   0.04276   0.0003   0.1449   1.0000
  12.750   1.1274   0.05508   0.04527   0.0012   0.1403   1.0000
  13.000   1.1418   0.05691   0.04717   0.0015   0.1359   1.0000
  13.250   1.1524   0.05909   0.04946   0.0019   0.1321   1.0000
  13.500   1.1416   0.06232   0.05305   0.0034   0.1291   1.0000
  13.750   1.1350   0.06548   0.05648   0.0043   0.1261   1.0000
  14.000   1.1368   0.06813   0.05928   0.0047   0.1231   1.0000
  14.250   1.1487   0.07017   0.06132   0.0048   0.1200   1.0000
  14.500   1.1205   0.07536   0.06689   0.0053   0.1185   1.0000
  14.750   1.0879   0.08157   0.07344   0.0047   0.1174   1.0000
  15.000   1.0446   0.08984   0.08201   0.0024   0.1167   1.0000
  15.250   0.9695   0.10456   0.09703  -0.0045   0.1171   1.0000
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