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Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright 6 (daytonwright6-il)
Reynolds number: 100,000
Max Cl/Cd: 49.75 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwright6-il-100000-n5.txt
Download as CSV file: xf-daytonwright6-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dayton-Wright 6                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2853   0.13279   0.12762  -0.0406   1.0000   0.0721
 -12.750  -0.2947   0.13068   0.12558  -0.0418   1.0000   0.0724
 -12.500  -0.3004   0.12815   0.12311  -0.0423   1.0000   0.0726
 -12.250  -0.3052   0.12556   0.12058  -0.0423   1.0000   0.0726
 -11.250  -0.2996   0.11457   0.10981  -0.0359   1.0000   0.0744
 -10.750  -0.2708   0.10789   0.10311  -0.0400   0.9938   0.0773
 -10.250  -0.2777   0.09158   0.08674  -0.0561   0.9789   0.0533
 -10.000  -0.2631   0.08786   0.08300  -0.0593   0.9734   0.0527
  -9.750  -0.2566   0.08381   0.07896  -0.0628   0.9650   0.0523
  -9.500  -0.2542   0.07912   0.07427  -0.0677   0.9558   0.0522
  -9.250  -0.2539   0.07363   0.06874  -0.0736   0.9463   0.0523
  -9.000  -0.2530   0.06858   0.06364  -0.0773   0.9348   0.0521
  -8.750  -0.2509   0.06335   0.05830  -0.0808   0.9247   0.0519
  -8.500  -0.2430   0.05732   0.05209  -0.0849   0.9174   0.0513
  -8.250  -0.2437   0.05176   0.04628  -0.0860   0.9066   0.0508
  -8.000  -0.2355   0.04488   0.03894  -0.0885   0.9007   0.0504
  -7.750  -0.2345   0.04052   0.03415  -0.0868   0.8898   0.0504
  -7.500  -0.2156   0.03607   0.02912  -0.0876   0.8848   0.0507
  -7.250  -0.2061   0.03351   0.02611  -0.0852   0.8745   0.0516
  -7.000  -0.1793   0.03065   0.02264  -0.0858   0.8696   0.0529
  -6.750  -0.1618   0.02884   0.02038  -0.0840   0.8603   0.0536
  -6.500  -0.1301   0.02724   0.01858  -0.0849   0.8546   0.0543
  -6.250  -0.1046   0.02612   0.01730  -0.0844   0.8463   0.0550
  -6.000  -0.0736   0.02499   0.01600  -0.0849   0.8390   0.0561
  -5.750  -0.0445   0.02399   0.01483  -0.0849   0.8309   0.0573
  -5.500  -0.0137   0.02301   0.01368  -0.0852   0.8223   0.0588
  -5.250   0.0142   0.02218   0.01268  -0.0849   0.8124   0.0607
  -5.000   0.0476   0.02139   0.01178  -0.0857   0.8037   0.0637
  -4.750   0.0715   0.02092   0.01129  -0.0847   0.7914   0.0668
  -4.500   0.0994   0.02032   0.01058  -0.0843   0.7799   0.0705
  -4.250   0.1300   0.01964   0.00983  -0.0845   0.7688   0.0750
  -4.000   0.1526   0.01920   0.00936  -0.0832   0.7541   0.0816
  -3.750   0.1759   0.01874   0.00889  -0.0820   0.7391   0.0916
  -3.500   0.2002   0.01837   0.00852  -0.0810   0.7237   0.1065
  -3.250   0.2253   0.01809   0.00821  -0.0802   0.7083   0.1247
  -3.000   0.2511   0.01787   0.00792  -0.0795   0.6930   0.1435
  -2.750   0.2772   0.01764   0.00769  -0.0790   0.6779   0.1641
  -2.500   0.3037   0.01744   0.00748  -0.0786   0.6636   0.1893
  -2.250   0.3305   0.01724   0.00728  -0.0782   0.6500   0.2167
  -2.000   0.3579   0.01704   0.00706  -0.0780   0.6372   0.2464
  -1.750   0.3858   0.01685   0.00688  -0.0779   0.6249   0.2840
  -1.500   0.5223   0.01520   0.00698  -0.0999   0.6070   0.9221
  -1.250   0.5864   0.01560   0.00707  -0.1071   0.5929   0.9937
  -1.000   0.6208   0.01576   0.00702  -0.1086   0.5812   1.0000
  -0.750   0.6423   0.01593   0.00700  -0.1073   0.5715   1.0000
  -0.500   0.6630   0.01611   0.00702  -0.1060   0.5616   1.0000
  -0.250   0.6841   0.01631   0.00707  -0.1047   0.5525   1.0000
   0.000   0.7052   0.01651   0.00713  -0.1034   0.5438   1.0000
   0.250   0.7260   0.01672   0.00723  -0.1021   0.5351   1.0000
   0.500   0.7470   0.01694   0.00733  -0.1009   0.5267   1.0000
   0.750   0.7675   0.01717   0.00746  -0.0995   0.5182   1.0000
   1.000   0.7883   0.01741   0.00760  -0.0982   0.5102   1.0000
   1.250   0.8090   0.01765   0.00776  -0.0969   0.5024   1.0000
   1.500   0.8293   0.01790   0.00794  -0.0956   0.4945   1.0000
   1.750   0.8501   0.01816   0.00812  -0.0943   0.4872   1.0000
   2.000   0.8696   0.01842   0.00834  -0.0928   0.4790   1.0000
   2.250   0.8907   0.01869   0.00852  -0.0917   0.4723   1.0000
   2.500   0.9096   0.01897   0.00881  -0.0901   0.4644   1.0000
   2.750   0.9307   0.01924   0.00900  -0.0890   0.4582   1.0000
   3.000   0.9496   0.01955   0.00931  -0.0874   0.4508   1.0000
   3.250   0.9692   0.01984   0.00957  -0.0860   0.4440   1.0000
   3.500   0.9890   0.02015   0.00985  -0.0847   0.4376   1.0000
   3.750   1.0077   0.02047   0.01018  -0.0832   0.4308   1.0000
   4.000   1.0286   0.02078   0.01043  -0.0821   0.4255   1.0000
   4.250   1.0465   0.02114   0.01084  -0.0804   0.4190   1.0000
   4.500   1.0654   0.02148   0.01117  -0.0790   0.4129   1.0000
   4.750   1.0855   0.02182   0.01148  -0.0778   0.4077   1.0000
   5.000   1.1026   0.02221   0.01195  -0.0761   0.4015   1.0000
   5.250   1.1216   0.02258   0.01231  -0.0748   0.3963   1.0000
   5.500   1.1414   0.02296   0.01267  -0.0736   0.3915   1.0000
   5.750   1.1575   0.02340   0.01321  -0.0718   0.3857   1.0000
   6.000   1.1757   0.02380   0.01363  -0.0704   0.3807   1.0000
   6.250   1.1962   0.02420   0.01399  -0.0694   0.3764   1.0000
   6.500   1.2103   0.02471   0.01463  -0.0673   0.3710   1.0000
   6.750   1.2271   0.02517   0.01514  -0.0657   0.3660   1.0000
   7.000   1.2473   0.02558   0.01553  -0.0648   0.3619   1.0000
   7.250   1.2607   0.02615   0.01621  -0.0627   0.3571   1.0000
   7.500   1.2736   0.02667   0.01683  -0.0604   0.3522   1.0000
   7.750   1.2905   0.02714   0.01734  -0.0590   0.3480   1.0000
   8.000   1.3087   0.02765   0.01787  -0.0578   0.3441   1.0000
   8.250   1.3165   0.02831   0.01869  -0.0549   0.3393   1.0000
   8.500   1.3293   0.02888   0.01935  -0.0528   0.3348   1.0000
   8.750   1.3475   0.02930   0.01976  -0.0517   0.3299   1.0000
   9.000   1.3498   0.03005   0.02068  -0.0482   0.3240   1.0000
   9.250   1.3566   0.03063   0.02132  -0.0454   0.3174   1.0000
   9.500   1.3651   0.03123   0.02196  -0.0430   0.3111   1.0000
   9.750   1.3661   0.03212   0.02300  -0.0398   0.3042   1.0000
  10.000   1.3773   0.03266   0.02352  -0.0380   0.2979   1.0000
  10.250   1.3763   0.03387   0.02494  -0.0350   0.2919   1.0000
  10.500   1.3790   0.03485   0.02600  -0.0325   0.2849   1.0000
  10.750   1.3800   0.03606   0.02731  -0.0302   0.2781   1.0000
  11.000   1.3801   0.03746   0.02886  -0.0280   0.2716   1.0000
  11.250   1.3851   0.03861   0.03003  -0.0263   0.2658   1.0000
  11.500   1.3800   0.04061   0.03225  -0.0242   0.2589   1.0000
  11.750   1.3798   0.04218   0.03385  -0.0225   0.2514   1.0000
  12.000   1.3708   0.04481   0.03670  -0.0208   0.2437   1.0000
  12.250   1.3684   0.04688   0.03881  -0.0196   0.2367   1.0000
  12.500   1.3593   0.04996   0.04210  -0.0186   0.2300   1.0000
  12.750   1.3531   0.05279   0.04500  -0.0178   0.2229   1.0000
  13.000   1.3387   0.05683   0.04922  -0.0175   0.2150   1.0000
  13.250   1.3280   0.06057   0.05301  -0.0173   0.2071   1.0000
  13.500   1.3107   0.06554   0.05816  -0.0177   0.1999   1.0000
  13.750   1.2971   0.07007   0.06276  -0.0181   0.1923   1.0000
  14.000   1.2782   0.07564   0.06849  -0.0190   0.1857   1.0000
  14.250   1.2617   0.08090   0.07381  -0.0199   0.1773   1.0000
  14.500   1.2440   0.08657   0.07959  -0.0210   0.1706   1.0000
  14.750   1.2269   0.09221   0.08530  -0.0223   0.1616   1.0000
  15.000   1.2140   0.09730   0.09042  -0.0234   0.1528   1.0000
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