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Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Dayton-Wright 6 (daytonwright6-il)
Reynolds number: 200,000
Max Cl/Cd: 66.79 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-daytonwright6-il-200000.txt
Download as CSV file: xf-daytonwright6-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.2789   0.12705   0.12344  -0.0376   1.0000   0.0589
 -12.500  -0.3101   0.12583   0.12233  -0.0412   1.0000   0.0598
 -12.250  -0.3145   0.12247   0.11903  -0.0404   1.0000   0.0601
 -12.000  -0.3003   0.11930   0.11587  -0.0369   1.0000   0.0607
 -11.750  -0.2984   0.11741   0.11402  -0.0344   1.0000   0.0612
 -11.500  -0.3002   0.11594   0.11260  -0.0317   1.0000   0.0621
 -11.250  -0.3061   0.11461   0.11132  -0.0294   1.0000   0.0628
 -11.000  -0.3010   0.11198   0.10870  -0.0303   0.9987   0.0644
 -10.750  -0.2870   0.10789   0.10461  -0.0357   0.9953   0.0672
 -10.500  -0.3047   0.10252   0.09927  -0.0531   0.9865   0.0696
 -10.250  -0.2768   0.09773   0.09447  -0.0499   0.9858   0.0707
 -10.000  -0.2502   0.09456   0.09127  -0.0511   0.9837   0.0719
  -9.750  -0.2334   0.09135   0.08806  -0.0535   0.9787   0.0734
  -9.500  -0.2176   0.08768   0.08439  -0.0579   0.9739   0.0758
  -9.250  -0.2217   0.08296   0.07968  -0.0674   0.9637   0.0796
  -9.000  -0.2403   0.07476   0.07133  -0.0818   0.9484   0.0812
  -8.750  -0.2139   0.07153   0.06816  -0.0810   0.9464   0.0822
  -8.500  -0.1849   0.06892   0.06556  -0.0820   0.9443   0.0836
  -8.250  -0.1717   0.06645   0.06307  -0.0824   0.9359   0.0855
  -8.000  -0.1754   0.06060   0.05666  -0.0926   0.9226   0.0934
  -7.750  -0.1557   0.05504   0.05119  -0.0942   0.9184   0.0947
  -7.500  -0.1244   0.05202   0.04819  -0.0963   0.9159   0.0960
  -7.250  -0.0896   0.04896   0.04508  -0.0997   0.9137   0.0981
  -7.000  -0.1120   0.03584   0.03091  -0.0983   0.9003   0.0720
  -6.750  -0.1201   0.02754   0.02135  -0.0933   0.8900   0.0612
  -6.500  -0.0874   0.02517   0.01862  -0.0944   0.8853   0.0615
  -6.250  -0.0485   0.02278   0.01581  -0.0964   0.8820   0.0612
  -6.000  -0.0268   0.02151   0.01434  -0.0948   0.8717   0.0616
  -5.750   0.0147   0.02001   0.01265  -0.0972   0.8666   0.0625
  -5.500   0.0408   0.01910   0.01160  -0.0964   0.8559   0.0635
  -5.250   0.0832   0.01800   0.01033  -0.0989   0.8489   0.0655
  -5.000   0.1083   0.01739   0.00959  -0.0978   0.8359   0.0678
  -4.750   0.1368   0.01668   0.00875  -0.0974   0.8233   0.0702
  -4.500   0.1667   0.01590   0.00797  -0.0975   0.8112   0.0732
  -4.250   0.1968   0.01536   0.00736  -0.0975   0.7988   0.0774
  -4.000   0.2193   0.01482   0.00677  -0.0960   0.7834   0.0830
  -3.750   0.2422   0.01444   0.00635  -0.0945   0.7675   0.0932
  -3.500   0.2639   0.01398   0.00600  -0.0930   0.7512   0.1176
  -3.250   0.2869   0.01373   0.00575  -0.0917   0.7344   0.1434
  -3.000   0.3102   0.01355   0.00552  -0.0905   0.7174   0.1611
  -2.750   0.3334   0.01339   0.00531  -0.0894   0.7006   0.1782
  -2.500   0.3563   0.01324   0.00512  -0.0882   0.6844   0.1982
  -2.250   0.3790   0.01311   0.00497  -0.0870   0.6690   0.2238
  -2.000   0.4005   0.01295   0.00487  -0.0856   0.6547   0.2587
  -1.750   0.5297   0.01129   0.00519  -0.1065   0.6356   0.9388
  -1.500   0.6179   0.01187   0.00542  -0.1185   0.6186   0.9928
  -1.250   0.6636   0.01196   0.00530  -0.1225   0.6050   1.0000
  -1.000   0.6833   0.01210   0.00532  -0.1209   0.5937   1.0000
  -0.750   0.7042   0.01228   0.00532  -0.1196   0.5835   1.0000
  -0.500   0.7241   0.01243   0.00537  -0.1181   0.5733   1.0000
  -0.250   0.7446   0.01261   0.00543  -0.1167   0.5638   1.0000
   0.000   0.7654   0.01279   0.00548  -0.1154   0.5546   1.0000
   0.250   0.7853   0.01297   0.00559  -0.1139   0.5452   1.0000
   0.500   0.8069   0.01318   0.00566  -0.1128   0.5366   1.0000
   0.750   0.8259   0.01335   0.00580  -0.1111   0.5272   1.0000
   1.250   0.8666   0.01376   0.00607  -0.1083   0.5101   1.0000
   1.500   0.8892   0.01402   0.00619  -0.1074   0.5025   1.0000
   1.750   0.9073   0.01420   0.00638  -0.1055   0.4936   1.0000
   2.000   0.9294   0.01446   0.00651  -0.1045   0.4861   1.0000
   2.250   0.9476   0.01465   0.00674  -0.1027   0.4776   1.0000
   2.500   0.9691   0.01489   0.00688  -0.1016   0.4704   1.0000
   2.750   0.9884   0.01513   0.00713  -0.1001   0.4628   1.0000
   3.000   1.0088   0.01536   0.00731  -0.0987   0.4558   1.0000
   3.250   1.0293   0.01563   0.00755  -0.0975   0.4489   1.0000
   3.500   1.0486   0.01586   0.00777  -0.0959   0.4417   1.0000
   3.750   1.0716   0.01616   0.00798  -0.0952   0.4358   1.0000
   4.000   1.0892   0.01640   0.00829  -0.0934   0.4290   1.0000
   4.250   1.1099   0.01666   0.00851  -0.0922   0.4231   1.0000
   4.500   1.1308   0.01698   0.00880  -0.0911   0.4172   1.0000
   4.750   1.1495   0.01724   0.00912  -0.0895   0.4111   1.0000
   5.000   1.1715   0.01754   0.00936  -0.0887   0.4059   1.0000
   5.250   1.1912   0.01788   0.00973  -0.0874   0.4005   1.0000
   5.500   1.2098   0.01817   0.01007  -0.0859   0.3948   1.0000
   5.750   1.2320   0.01849   0.01035  -0.0851   0.3900   1.0000
   6.000   1.2517   0.01887   0.01077  -0.0839   0.3850   1.0000
   6.250   1.2694   0.01920   0.01116  -0.0823   0.3797   1.0000
   6.500   1.2909   0.01954   0.01149  -0.0814   0.3750   1.0000
   6.750   1.3130   0.01998   0.01193  -0.0808   0.3705   1.0000
   7.000   1.3259   0.02027   0.01233  -0.0783   0.3645   1.0000
   7.250   1.3447   0.02055   0.01257  -0.0769   0.3587   1.0000
   7.500   1.3593   0.02092   0.01300  -0.0748   0.3527   1.0000
   7.750   1.3705   0.02118   0.01331  -0.0720   0.3460   1.0000
   8.000   1.3891   0.02154   0.01360  -0.0708   0.3397   1.0000
   8.250   1.3939   0.02184   0.01405  -0.0668   0.3340   1.0000
   8.500   1.4065   0.02216   0.01441  -0.0644   0.3287   1.0000
   8.750   1.4230   0.02259   0.01482  -0.0628   0.3234   1.0000
   9.000   1.4261   0.02292   0.01529  -0.0588   0.3175   1.0000
   9.250   1.4367   0.02326   0.01561  -0.0562   0.3111   1.0000
   9.500   1.4434   0.02372   0.01617  -0.0531   0.3049   1.0000
   9.750   1.4501   0.02417   0.01672  -0.0501   0.2988   1.0000
  10.000   1.4628   0.02467   0.01719  -0.0483   0.2929   1.0000
  10.250   1.4642   0.02528   0.01798  -0.0448   0.2860   1.0000
  10.500   1.4706   0.02588   0.01855  -0.0422   0.2787   1.0000
  10.750   1.4730   0.02668   0.01954  -0.0393   0.2713   1.0000
  11.000   1.4766   0.02753   0.02038  -0.0368   0.2633   1.0000
  11.250   1.4783   0.02857   0.02159  -0.0343   0.2538   1.0000
  11.500   1.4803   0.02974   0.02281  -0.0320   0.2445   1.0000
  11.750   1.4809   0.03112   0.02424  -0.0299   0.2344   1.0000
  12.000   1.4793   0.03278   0.02597  -0.0278   0.2209   1.0000
  12.250   1.4765   0.03472   0.02795  -0.0260   0.2065   1.0000
  12.500   1.4672   0.03732   0.03052  -0.0240   0.1865   1.0000
  12.750   1.4540   0.04051   0.03365  -0.0223   0.1664   1.0000
  13.000   1.4364   0.04440   0.03746  -0.0209   0.1452   1.0000
  13.250   1.4152   0.04903   0.04201  -0.0199   0.1247   1.0000
  13.500   1.3925   0.05414   0.04706  -0.0195   0.1037   1.0000
  13.750   1.3681   0.05976   0.05263  -0.0195   0.0855   1.0000
  14.000   1.3425   0.06580   0.05863  -0.0198   0.0684   1.0000
  14.250   1.3195   0.07169   0.06450  -0.0204   0.0553   1.0000
  14.500   1.2974   0.07768   0.07049  -0.0212   0.0470   1.0000
  14.750   1.2799   0.08320   0.07607  -0.0221   0.0427   1.0000
  15.000   1.2632   0.08877   0.08170  -0.0232   0.0395   1.0000
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