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Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright 6 (daytonwright6-il)
Reynolds number: 50,000
Max Cl/Cd: 31.1 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwright6-il-50000-n5.txt
Download as CSV file: xf-daytonwright6-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3118   0.10999   0.10366  -0.0273   1.0000   0.1376
  -9.500  -0.3227   0.10809   0.10184  -0.0258   1.0000   0.1366
  -9.000  -0.3639   0.09605   0.08981  -0.0365   0.9890   0.0838
  -8.750  -0.3477   0.09197   0.08570  -0.0398   0.9814   0.0822
  -8.500  -0.3348   0.08733   0.08102  -0.0446   0.9726   0.0805
  -8.250  -0.3256   0.08252   0.07615  -0.0491   0.9620   0.0791
  -8.000  -0.3165   0.07774   0.07129  -0.0533   0.9510   0.0785
  -7.750  -0.3058   0.07318   0.06661  -0.0570   0.9404   0.0789
  -7.500  -0.2894   0.06826   0.06150  -0.0613   0.9316   0.0791
  -7.250  -0.2801   0.06402   0.05708  -0.0630   0.9198   0.0788
  -7.000  -0.2677   0.05968   0.05246  -0.0647   0.9090   0.0782
  -6.750  -0.2469   0.05494   0.04735  -0.0674   0.9009   0.0777
  -6.500  -0.2345   0.05142   0.04349  -0.0672   0.8890   0.0776
  -6.250  -0.2157   0.04806   0.03974  -0.0676   0.8792   0.0779
  -6.000  -0.1912   0.04489   0.03613  -0.0684   0.8706   0.0787
  -5.750  -0.1720   0.04255   0.03338  -0.0677   0.8593   0.0805
  -5.500  -0.1401   0.03974   0.02995  -0.0689   0.8528   0.0833
  -5.250  -0.1202   0.03784   0.02759  -0.0676   0.8408   0.0853
  -5.000  -0.0871   0.03622   0.02580  -0.0686   0.8333   0.0874
  -4.750  -0.0597   0.03489   0.02425  -0.0684   0.8228   0.0901
  -4.500  -0.0302   0.03357   0.02265  -0.0684   0.8130   0.0934
  -4.250   0.0072   0.03213   0.02084  -0.0696   0.8049   0.0993
  -4.000   0.0337   0.03147   0.02019  -0.0692   0.7932   0.1064
  -3.750   0.0781   0.03024   0.01879  -0.0716   0.7866   0.1181
  -3.500   0.1074   0.02955   0.01798  -0.0716   0.7740   0.1314
  -3.250   0.1427   0.02891   0.01729  -0.0726   0.7637   0.1528
  -3.000   0.1785   0.02833   0.01673  -0.0738   0.7541   0.1862
  -2.750   0.2034   0.02800   0.01639  -0.0731   0.7411   0.2154
  -2.500   0.2335   0.02745   0.01585  -0.0732   0.7297   0.2423
  -2.250   0.2703   0.02666   0.01509  -0.0743   0.7209   0.2750
  -2.000   0.2929   0.02627   0.01482  -0.0732   0.7080   0.3128
  -1.750   0.4489   0.02351   0.01391  -0.0969   0.6991   1.0000
  -1.500   0.4790   0.02341   0.01342  -0.0969   0.6883   1.0000
  -1.250   0.4996   0.02356   0.01332  -0.0954   0.6753   1.0000
  -1.000   0.5220   0.02369   0.01321  -0.0942   0.6633   1.0000
  -0.750   0.5483   0.02375   0.01300  -0.0937   0.6528   1.0000
  -0.500   0.5744   0.02382   0.01284  -0.0931   0.6421   1.0000
  -0.250   0.5952   0.02408   0.01292  -0.0917   0.6306   1.0000
   0.000   0.6212   0.02422   0.01285  -0.0912   0.6207   1.0000
   0.250   0.6452   0.02443   0.01288  -0.0904   0.6104   1.0000
   0.500   0.6659   0.02476   0.01307  -0.0891   0.5998   1.0000
   0.750   0.6957   0.02488   0.01297  -0.0892   0.5911   1.0000
   1.000   0.7120   0.02536   0.01339  -0.0873   0.5803   1.0000
   1.250   0.7371   0.02565   0.01354  -0.0868   0.5716   1.0000
   1.500   0.7575   0.02606   0.01386  -0.0855   0.5619   1.0000
   1.750   0.7790   0.02647   0.01418  -0.0845   0.5529   1.0000
   2.000   0.8014   0.02687   0.01449  -0.0835   0.5442   1.0000
   2.250   0.8208   0.02737   0.01494  -0.0822   0.5357   1.0000
   2.500   0.8427   0.02781   0.01530  -0.0813   0.5274   1.0000
   2.750   0.8617   0.02835   0.01581  -0.0799   0.5193   1.0000
   3.000   0.8816   0.02887   0.01629  -0.0787   0.5112   1.0000
   3.250   0.9026   0.02939   0.01677  -0.0777   0.5040   1.0000
   3.500   0.9178   0.03007   0.01746  -0.0758   0.4960   1.0000
   3.750   0.9456   0.03041   0.01772  -0.0758   0.4898   1.0000
   4.000   0.9520   0.03138   0.01878  -0.0727   0.4816   1.0000
   4.250   0.9773   0.03180   0.01916  -0.0724   0.4755   1.0000
   4.500   0.9869   0.03273   0.02017  -0.0698   0.4683   1.0000
   4.750   1.0033   0.03343   0.02090  -0.0683   0.4617   1.0000
   5.000   1.0292   0.03386   0.02128  -0.0681   0.4564   1.0000
   5.250   1.0286   0.03517   0.02274  -0.0642   0.4490   1.0000
   5.500   1.0503   0.03574   0.02332  -0.0635   0.4436   1.0000
   5.750   1.0618   0.03669   0.02433  -0.0614   0.4378   1.0000
   6.000   1.0633   0.03799   0.02574  -0.0580   0.4313   1.0000
   6.250   1.0891   0.03840   0.02615  -0.0578   0.4265   1.0000
   6.500   1.0841   0.04000   0.02788  -0.0537   0.4205   1.0000
   6.750   1.0805   0.04154   0.02951  -0.0498   0.4146   1.0000
   7.000   1.1099   0.04179   0.02978  -0.0501   0.4102   1.0000
   7.250   1.0841   0.04448   0.03261  -0.0442   0.4038   1.0000
   7.500   1.0781   0.04651   0.03473  -0.0409   0.3978   1.0000
   7.750   1.1117   0.04643   0.03469  -0.0414   0.3941   1.0000
   8.000   1.0365   0.05348   0.04189  -0.0341   0.3843   1.0000
   8.250   1.0549   0.05422   0.04269  -0.0334   0.3800   1.0000
   8.500   1.0993   0.05298   0.04152  -0.0339   0.3775   1.0000
   8.750   0.9986   0.06476   0.05338  -0.0297   0.3638   1.0000
   9.000   1.0349   0.06356   0.05227  -0.0292   0.3617   1.0000
   9.500   0.9848   0.07537   0.06421  -0.0283   0.3449   1.0000
  10.000   0.9527   0.08629   0.07527  -0.0289   0.3286   1.0000
  10.500   0.9349   0.09538   0.08450  -0.0295   0.3145   1.0000
  11.000   0.9139   0.10503   0.09428  -0.0307   0.3002   1.0000
  11.250   0.9377   0.10509   0.09443  -0.0299   0.2979   1.0000
  11.500   0.8994   0.11393   0.10331  -0.0321   0.2870   1.0000
  11.750   0.9176   0.11476   0.10424  -0.0316   0.2837   1.0000
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