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Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright 6 (daytonwright6-il)
Reynolds number: 200,000
Max Cl/Cd: 66.39 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwright6-il-200000-n5.txt
Download as CSV file: xf-daytonwright6-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2346   0.09132   0.08768  -0.0618   0.9772   0.0368
 -10.750  -0.2270   0.08630   0.08266  -0.0667   0.9711   0.0371
 -10.500  -0.2227   0.08135   0.07770  -0.0710   0.9621   0.0370
 -10.250  -0.2213   0.07620   0.07256  -0.0754   0.9516   0.0369
 -10.000  -0.2229   0.07033   0.06670  -0.0812   0.9413   0.0365
  -9.500  -0.3136   0.03635   0.03159  -0.1030   0.9061   0.0352
  -9.250  -0.3000   0.03205   0.02676  -0.1041   0.9005   0.0359
  -9.000  -0.2908   0.02925   0.02352  -0.1025   0.8910   0.0363
  -8.750  -0.2683   0.02670   0.02051  -0.1029   0.8855   0.0367
  -8.500  -0.2503   0.02498   0.01844  -0.1017   0.8775   0.0370
  -8.250  -0.2244   0.02340   0.01653  -0.1018   0.8714   0.0373
  -8.000  -0.1992   0.02213   0.01498  -0.1015   0.8646   0.0377
  -7.750  -0.1737   0.02108   0.01368  -0.1012   0.8571   0.0381
  -7.500  -0.1442   0.02010   0.01247  -0.1016   0.8507   0.0385
  -7.250  -0.1204   0.01936   0.01156  -0.1007   0.8422   0.0388
  -6.750  -0.0680   0.01789   0.00991  -0.1000   0.8260   0.0403
  -6.500  -0.0393   0.01731   0.00924  -0.1001   0.8181   0.0411
  -6.250  -0.0164   0.01685   0.00872  -0.0989   0.8081   0.0419
  -6.000   0.0093   0.01638   0.00815  -0.0983   0.7985   0.0426
  -5.750   0.0339   0.01595   0.00763  -0.0975   0.7879   0.0434
  -5.500   0.0565   0.01557   0.00718  -0.0962   0.7760   0.0441
  -5.250   0.0800   0.01523   0.00675  -0.0951   0.7631   0.0450
  -5.000   0.1031   0.01493   0.00634  -0.0938   0.7484   0.0459
  -4.750   0.1251   0.01460   0.00597  -0.0924   0.7314   0.0474
  -4.500   0.1477   0.01435   0.00565  -0.0911   0.7129   0.0490
  -4.250   0.1707   0.01414   0.00534  -0.0899   0.6926   0.0514
  -4.000   0.1937   0.01394   0.00505  -0.0887   0.6723   0.0557
  -3.750   0.2162   0.01379   0.00482  -0.0874   0.6527   0.0632
  -3.500   0.2385   0.01367   0.00463  -0.0861   0.6348   0.0749
  -3.250   0.2607   0.01359   0.00448  -0.0848   0.6188   0.0892
  -3.000   0.2831   0.01355   0.00437  -0.0835   0.6047   0.1032
  -2.500   0.3284   0.01352   0.00424  -0.0813   0.5801   0.1310
  -2.250   0.3512   0.01351   0.00420  -0.0802   0.5700   0.1466
  -2.000   0.3738   0.01350   0.00418  -0.0791   0.5602   0.1640
  -1.750   0.3963   0.01346   0.00416  -0.0780   0.5509   0.1856
  -1.250   0.4402   0.01335   0.00417  -0.0756   0.5342   0.2494
  -1.000   0.4611   0.01325   0.00419  -0.0743   0.5266   0.3026
  -0.750   0.5865   0.01199   0.00466  -0.0953   0.5131   0.9167
  -0.500   0.6305   0.01232   0.00485  -0.0985   0.5044   0.9625
  -0.250   0.6750   0.01260   0.00502  -0.1020   0.4953   0.9873
   0.000   0.7321   0.01281   0.00508  -0.1085   0.4865   1.0000
   0.250   0.7519   0.01293   0.00513  -0.1070   0.4791   1.0000
   0.500   0.7714   0.01308   0.00519  -0.1054   0.4722   1.0000
   0.750   0.7912   0.01320   0.00526  -0.1039   0.4644   1.0000
   1.000   0.8105   0.01337   0.00534  -0.1023   0.4577   1.0000
   1.250   0.8306   0.01350   0.00544  -0.1008   0.4505   1.0000
   1.500   0.8500   0.01366   0.00555  -0.0992   0.4437   1.0000
   1.750   0.8696   0.01383   0.00566  -0.0977   0.4367   1.0000
   2.000   0.8888   0.01400   0.00579  -0.0961   0.4295   1.0000
   2.250   0.9077   0.01419   0.00593  -0.0945   0.4227   1.0000
   2.500   0.9270   0.01436   0.00608  -0.0929   0.4155   1.0000
   2.750   0.9454   0.01458   0.00623  -0.0912   0.4093   1.0000
   3.000   0.9650   0.01477   0.00642  -0.0897   0.4029   1.0000
   3.250   0.9835   0.01499   0.00660  -0.0880   0.3966   1.0000
   3.500   1.0018   0.01522   0.00680  -0.0863   0.3906   1.0000
   3.750   1.0205   0.01544   0.00701  -0.0847   0.3843   1.0000
   4.000   1.0382   0.01570   0.00723  -0.0829   0.3788   1.0000
   4.250   1.0567   0.01595   0.00748  -0.0814   0.3735   1.0000
   4.500   1.0749   0.01619   0.00773  -0.0797   0.3680   1.0000
   4.750   1.0921   0.01648   0.00798  -0.0779   0.3631   1.0000
   5.000   1.1095   0.01675   0.00826  -0.0761   0.3582   1.0000
   5.250   1.1264   0.01701   0.00854  -0.0743   0.3533   1.0000
   5.500   1.1422   0.01729   0.00881  -0.0722   0.3488   1.0000
   5.750   1.1578   0.01761   0.00911  -0.0702   0.3445   1.0000
   6.000   1.1749   0.01788   0.00944  -0.0684   0.3400   1.0000
   6.250   1.1913   0.01818   0.00977  -0.0666   0.3356   1.0000
   6.500   1.2071   0.01853   0.01010  -0.0647   0.3314   1.0000
   6.750   1.2239   0.01888   0.01048  -0.0631   0.3276   1.0000
   7.000   1.2403   0.01920   0.01088  -0.0614   0.3228   1.0000
   7.250   1.2551   0.01957   0.01127  -0.0595   0.3178   1.0000
   7.500   1.2688   0.01999   0.01167  -0.0574   0.3122   1.0000
   7.750   1.2823   0.02036   0.01213  -0.0553   0.3053   1.0000
   8.000   1.2944   0.02083   0.01259  -0.0531   0.2991   1.0000
   8.250   1.3085   0.02127   0.01310  -0.0514   0.2933   1.0000
   8.500   1.3215   0.02175   0.01363  -0.0495   0.2871   1.0000
   8.750   1.3332   0.02232   0.01421  -0.0474   0.2818   1.0000
   9.000   1.3461   0.02284   0.01484  -0.0457   0.2745   1.0000
   9.250   1.3553   0.02352   0.01552  -0.0435   0.2673   1.0000
   9.500   1.3674   0.02414   0.01624  -0.0419   0.2597   1.0000
   9.750   1.3765   0.02492   0.01705  -0.0399   0.2527   1.0000
  10.000   1.3869   0.02570   0.01791  -0.0382   0.2439   1.0000
  10.250   1.3941   0.02667   0.01891  -0.0363   0.2363   1.0000
  10.500   1.3996   0.02779   0.02005  -0.0343   0.2232   1.0000
  10.750   1.4024   0.02916   0.02142  -0.0323   0.2086   1.0000
  11.000   1.4049   0.03064   0.02291  -0.0304   0.1949   1.0000
  11.250   1.4034   0.03250   0.02473  -0.0285   0.1792   1.0000
  11.500   1.3994   0.03466   0.02686  -0.0265   0.1625   1.0000
  11.750   1.3868   0.03768   0.02979  -0.0244   0.1404   1.0000
  12.000   1.3738   0.04099   0.03303  -0.0228   0.1201   1.0000
  12.250   1.3585   0.04477   0.03674  -0.0215   0.1015   1.0000
  12.500   1.3430   0.04886   0.04081  -0.0206   0.0844   1.0000
  12.750   1.3155   0.05456   0.04640  -0.0201   0.0597   1.0000
  13.000   1.2901   0.06038   0.05216  -0.0201   0.0391   1.0000
  13.250   1.2710   0.06566   0.05745  -0.0204   0.0298   1.0000
  13.500   1.2574   0.07042   0.06228  -0.0209   0.0260   1.0000
  13.750   1.2474   0.07483   0.06677  -0.0214   0.0243   1.0000
  14.000   1.2373   0.07934   0.07139  -0.0221   0.0228   1.0000
  14.250   1.2274   0.08391   0.07606  -0.0228   0.0219   1.0000
  14.500   1.2200   0.08821   0.08048  -0.0237   0.0214   1.0000
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