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DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DORNIER A-5 AIRFOIL (doa5-il)
Reynolds number: 200,000
Max Cl/Cd: 52 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-doa5-il-200000.txt
Download as CSV file: xf-doa5-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5657   0.09913   0.09550  -0.0535   1.0000   0.0841
 -11.000  -0.6126   0.09350   0.08985  -0.0545   1.0000   0.0842
 -10.750  -0.6517   0.08973   0.08604  -0.0534   1.0000   0.0842
 -10.500  -0.6914   0.08679   0.08306  -0.0510   1.0000   0.0842
 -10.250  -0.7320   0.08334   0.07942  -0.0525   0.9946   0.0844
 -10.000  -0.7631   0.08022   0.07593  -0.0534   0.9868   0.0847
  -9.750  -0.7386   0.07224   0.06820  -0.0552   0.9869   0.0866
  -9.500  -0.7132   0.06957   0.06559  -0.0567   0.9849   0.0884
  -9.250  -0.7101   0.06655   0.06246  -0.0571   0.9795   0.0901
  -9.000  -0.7077   0.06332   0.05904  -0.0581   0.9743   0.0930
  -8.750  -0.7586   0.04780   0.04187  -0.0536   0.9647   0.0621
  -8.500  -0.7409   0.04422   0.03806  -0.0540   0.9622   0.0606
  -8.250  -0.7188   0.04111   0.03458  -0.0549   0.9601   0.0602
  -8.000  -0.7112   0.03901   0.03222  -0.0523   0.9552   0.0600
  -7.750  -0.6912   0.03672   0.02963  -0.0518   0.9520   0.0597
  -7.500  -0.6645   0.03468   0.02730  -0.0523   0.9495   0.0597
  -7.250  -0.6329   0.03299   0.02537  -0.0536   0.9477   0.0599
  -7.000  -0.6137   0.03188   0.02408  -0.0523   0.9437   0.0609
  -6.750  -0.5927   0.03097   0.02300  -0.0514   0.9398   0.0620
  -6.500  -0.5648   0.03012   0.02195  -0.0517   0.9371   0.0629
  -6.250  -0.5332   0.02901   0.02072  -0.0526   0.9351   0.0638
  -6.000  -0.4994   0.02784   0.01962  -0.0539   0.9336   0.0654
  -5.750  -0.4837   0.02722   0.01902  -0.0519   0.9276   0.0668
  -5.500  -0.4557   0.02657   0.01837  -0.0522   0.9236   0.0687
  -5.250  -0.4212   0.02602   0.01776  -0.0536   0.9208   0.0719
  -5.000  -0.3864   0.02520   0.01697  -0.0551   0.9190   0.0750
  -4.750  -0.3767   0.02473   0.01657  -0.0522   0.9125   0.0773
  -4.500  -0.3523   0.02423   0.01610  -0.0520   0.9085   0.0812
  -4.250  -0.3225   0.02358   0.01546  -0.0529   0.9059   0.0867
  -4.000  -0.2891   0.02299   0.01493  -0.0546   0.9039   0.0960
  -3.750  -0.2759   0.02252   0.01454  -0.0526   0.8976   0.1049
  -3.500  -0.2515   0.02189   0.01399  -0.0527   0.8929   0.1239
  -3.250  -0.2215   0.02058   0.01320  -0.0544   0.8900   0.2153
  -3.000  -0.1991   0.01902   0.01333  -0.0544   0.8878   0.5949
  -2.750  -0.1870   0.01946   0.01378  -0.0512   0.8805   0.6258
  -2.500  -0.1577   0.01998   0.01436  -0.0507   0.8759   0.6491
  -2.250  -0.1195   0.02046   0.01482  -0.0516   0.8731   0.6654
  -2.000  -0.0774   0.02095   0.01530  -0.0531   0.8712   0.6790
  -1.750  -0.0695   0.02158   0.01593  -0.0490   0.8612   0.6887
  -1.500  -0.0342   0.02206   0.01641  -0.0491   0.8581   0.6963
  -1.250   0.0080   0.02209   0.01642  -0.0509   0.8561   0.7022
  -1.000   0.0217   0.02230   0.01657  -0.0486   0.8469   0.7097
  -0.750   0.0570   0.02238   0.01667  -0.0487   0.8433   0.7138
  -0.500   0.1004   0.02210   0.01636  -0.0508   0.8412   0.7193
  -0.250   0.1486   0.02150   0.01570  -0.0543   0.8397   0.7264
   0.000   0.1526   0.02208   0.01632  -0.0494   0.8292   0.7303
   0.250   0.1925   0.02168   0.01591  -0.0511   0.8268   0.7350
   0.500   0.2384   0.02103   0.01519  -0.0548   0.8253   0.7407
   0.750   0.2811   0.02050   0.01467  -0.0572   0.8240   0.7432
   1.000   0.3302   0.01987   0.01404  -0.0607   0.8229   0.7454
   1.250   0.3391   0.01993   0.01412  -0.0569   0.8119   0.7492
   1.500   0.3860   0.01934   0.01352  -0.0604   0.8094   0.7532
   1.750   0.4392   0.01875   0.01290  -0.0656   0.8075   0.7581
   2.000   0.4958   0.01817   0.01234  -0.0707   0.8053   0.7598
   2.250   0.4992   0.01816   0.01237  -0.0656   0.7934   0.7632
   2.500   0.5578   0.01753   0.01173  -0.0712   0.7887   0.7662
   2.750   0.5747   0.01730   0.01151  -0.0692   0.7765   0.7720
   3.000   0.6249   0.01675   0.01095  -0.0732   0.7692   0.7748
   3.250   0.6293   0.01661   0.01087  -0.0681   0.7562   0.7782
   3.500   0.6447   0.01638   0.01067  -0.0654   0.7438   0.7826
   3.750   0.6738   0.01608   0.01035  -0.0657   0.7312   0.7881
   4.000   0.6995   0.01573   0.01002  -0.0648   0.7173   0.7913
   4.250   0.7166   0.01551   0.00982  -0.0622   0.6997   0.7950
   4.500   0.7329   0.01537   0.00966  -0.0597   0.6781   0.8001
   4.750   0.7624   0.01519   0.00937  -0.0599   0.6513   0.8051
   5.000   0.7762   0.01515   0.00928  -0.0568   0.6217   0.8088
   5.250   0.7919   0.01524   0.00921  -0.0542   0.5836   0.8132
   5.500   0.8065   0.01551   0.00925  -0.0518   0.5417   0.8178
   5.750   0.8141   0.01585   0.00939  -0.0480   0.4955   0.8217
   6.000   0.8188   0.01627   0.00960  -0.0437   0.4558   0.8257
   6.250   0.8253   0.01678   0.00991  -0.0400   0.4225   0.8303
   6.500   0.8363   0.01735   0.01029  -0.0374   0.3959   0.8349
   6.750   0.8463   0.01779   0.01062  -0.0344   0.3734   0.8384
   7.000   0.8573   0.01821   0.01099  -0.0317   0.3507   0.8422
   7.250   0.8683   0.01870   0.01139  -0.0291   0.3262   0.8462
   7.500   0.8788   0.01930   0.01187  -0.0266   0.3005   0.8503
   7.750   0.8889   0.01977   0.01229  -0.0240   0.2717   0.8540
   8.000   0.8974   0.02032   0.01274  -0.0211   0.2445   0.8582
   8.250   0.9068   0.02099   0.01327  -0.0186   0.2230   0.8630
   8.500   0.9179   0.02179   0.01393  -0.0165   0.2074   0.8674
   8.750   0.9279   0.02246   0.01455  -0.0141   0.1954   0.8713
   9.000   0.9387   0.02332   0.01529  -0.0121   0.1847   0.8754
   9.250   0.9553   0.02392   0.01595  -0.0108   0.1754   0.8796
   9.500   0.9712   0.02479   0.01670  -0.0096   0.1673   0.8831
   9.750   0.9868   0.02533   0.01732  -0.0082   0.1601   0.8867
  10.000   1.0063   0.02622   0.01807  -0.0076   0.1524   0.8902
  10.250   1.0231   0.02681   0.01880  -0.0065   0.1467   0.8941
  10.500   1.0405   0.02754   0.01951  -0.0057   0.1406   0.8980
  10.750   1.0618   0.02833   0.02031  -0.0054   0.1350   0.9020
  11.000   1.0780   0.02900   0.02110  -0.0044   0.1299   0.9065
  11.250   1.0953   0.02975   0.02186  -0.0038   0.1253   0.9111
  11.500   1.1168   0.03062   0.02275  -0.0037   0.1209   0.9156
  11.750   1.1331   0.03137   0.02367  -0.0030   0.1166   0.9207
  12.000   1.1498   0.03219   0.02454  -0.0025   0.1127   0.9260
  12.250   1.1725   0.03320   0.02554  -0.0029   0.1086   0.9321
  12.500   1.1911   0.03421   0.02676  -0.0031   0.1049   0.9412
  12.750   1.2106   0.03518   0.02783  -0.0038   0.1010   0.9908
  13.000   1.2257   0.03621   0.02876  -0.0027   0.0976   1.0000
  13.250   1.2391   0.03754   0.03025  -0.0021   0.0944   1.0000
  13.500   1.2506   0.03885   0.03168  -0.0013   0.0912   1.0000
  13.750   1.2640   0.04009   0.03293  -0.0009   0.0881   1.0000
  14.000   1.2843   0.04161   0.03442  -0.0010   0.0844   1.0000
  14.250   1.2884   0.04323   0.03626   0.0002   0.0820   1.0000
  14.500   1.2946   0.04483   0.03798   0.0011   0.0792   1.0000
  14.750   1.3050   0.04625   0.03940   0.0016   0.0766   1.0000
  15.000   1.3203   0.04797   0.04111   0.0017   0.0739   1.0000
  15.250   1.3191   0.05008   0.04347   0.0029   0.0720   1.0000
  15.500   1.3207   0.05217   0.04572   0.0036   0.0699   1.0000
  15.750   1.3254   0.05404   0.04765   0.0041   0.0678   1.0000
  16.000   1.3366   0.05564   0.04920   0.0042   0.0658   1.0000
  16.250   1.3376   0.05831   0.05202   0.0046   0.0640   1.0000
  16.500   1.3316   0.06135   0.05531   0.0050   0.0624   1.0000
  16.750   1.3282   0.06430   0.05842   0.0050   0.0608   1.0000
  17.000   1.3290   0.06694   0.06114   0.0048   0.0593   1.0000
  17.250   1.3365   0.06893   0.06309   0.0046   0.0576   1.0000
  17.500   1.3364   0.07212   0.06638   0.0043   0.0561   1.0000
  17.750   1.3221   0.07672   0.07124   0.0034   0.0552   1.0000
  18.000   1.3083   0.08154   0.07630   0.0021   0.0542   1.0000
  18.250   1.2948   0.08659   0.08157   0.0004   0.0532   1.0000
  18.500   1.2837   0.09143   0.08657  -0.0015   0.0521   1.0000
  18.750   1.2799   0.09534   0.09055  -0.0033   0.0510   1.0000
  19.000   1.2917   0.09693   0.09205  -0.0038   0.0496   1.0000
  19.250   1.2789   0.10245   0.09771  -0.0062   0.0488   1.0000
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