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Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright 6 (daytonwright6-il)
Reynolds number: 500,000
Max Cl/Cd: 89.58 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwright6-il-500000-n5.txt
Download as CSV file: xf-daytonwright6-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5385   0.03634   0.03316  -0.1098   0.9488   0.0243
 -12.000  -0.5319   0.03304   0.02958  -0.1106   0.9378   0.0245
 -11.750  -0.5114   0.03050   0.02679  -0.1125   0.9306   0.0248
 -11.500  -0.4888   0.02812   0.02413  -0.1142   0.9211   0.0252
 -11.250  -0.4619   0.02581   0.02149  -0.1164   0.9127   0.0254
 -11.000  -0.4337   0.02398   0.01938  -0.1181   0.9021   0.0256
 -10.750  -0.4072   0.02257   0.01770  -0.1189   0.8897   0.0259
 -10.500  -0.3829   0.02137   0.01626  -0.1190   0.8770   0.0262
 -10.250  -0.3602   0.02039   0.01505  -0.1184   0.8664   0.0264
 -10.000  -0.3400   0.01952   0.01399  -0.1173   0.8574   0.0266
  -9.750  -0.3184   0.01880   0.01308  -0.1163   0.8495   0.0268
  -9.500  -0.2973   0.01816   0.01229  -0.1150   0.8415   0.0271
  -9.250  -0.2746   0.01769   0.01166  -0.1141   0.8341   0.0273
  -9.000  -0.2532   0.01714   0.01097  -0.1128   0.8269   0.0275
  -8.750  -0.2308   0.01656   0.01025  -0.1117   0.8204   0.0276
  -8.500  -0.2103   0.01576   0.00934  -0.1103   0.8139   0.0279
  -8.250  -0.1885   0.01515   0.00865  -0.1091   0.8067   0.0281
  -8.000  -0.1660   0.01464   0.00804  -0.1080   0.8000   0.0284
  -7.750  -0.1437   0.01420   0.00755  -0.1068   0.7926   0.0287
  -7.500  -0.1205   0.01382   0.00709  -0.1058   0.7853   0.0289
  -7.250  -0.0980   0.01345   0.00667  -0.1045   0.7766   0.0292
  -7.000  -0.0750   0.01313   0.00628  -0.1034   0.7676   0.0295
  -6.750  -0.0523   0.01283   0.00592  -0.1022   0.7567   0.0298
  -6.500  -0.0301   0.01254   0.00556  -0.1008   0.7430   0.0301
  -6.250  -0.0085   0.01229   0.00522  -0.0993   0.7247   0.0305
  -6.000   0.0120   0.01209   0.00490  -0.0976   0.6998   0.0308
  -5.750   0.0315   0.01196   0.00461  -0.0957   0.6710   0.0312
  -5.500   0.0507   0.01189   0.00437  -0.0937   0.6420   0.0317
  -5.250   0.0713   0.01181   0.00416  -0.0920   0.6197   0.0321
  -5.000   0.0925   0.01174   0.00397  -0.0905   0.6012   0.0326
  -4.750   0.1143   0.01166   0.00379  -0.0891   0.5859   0.0329
  -4.500   0.1360   0.01153   0.00358  -0.0876   0.5724   0.0334
  -4.250   0.1584   0.01142   0.00339  -0.0864   0.5603   0.0341
  -4.000   0.1814   0.01131   0.00323  -0.0853   0.5507   0.0350
  -3.500   0.2279   0.01118   0.00299  -0.0831   0.5331   0.0368
  -3.250   0.2510   0.01114   0.00289  -0.0820   0.5250   0.0381
  -3.000   0.2748   0.01107   0.00280  -0.0810   0.5179   0.0401
  -2.750   0.2980   0.01100   0.00272  -0.0800   0.5110   0.0442
  -2.500   0.3204   0.01086   0.00268  -0.0788   0.5050   0.0679
  -2.250   0.3440   0.01080   0.00264  -0.0779   0.4986   0.0839
  -2.000   0.3668   0.01078   0.00263  -0.0768   0.4916   0.0948
  -1.750   0.3904   0.01074   0.00261  -0.0758   0.4852   0.1068
  -1.500   0.4136   0.01072   0.00260  -0.0748   0.4786   0.1205
  -1.250   0.4364   0.01072   0.00261  -0.0737   0.4729   0.1335
  -1.000   0.4601   0.01069   0.00261  -0.0729   0.4668   0.1493
  -0.750   0.4826   0.01068   0.00263  -0.0717   0.4603   0.1670
  -0.500   0.5049   0.01066   0.00265  -0.0706   0.4537   0.1922
  -0.250   0.5268   0.01060   0.00269  -0.0694   0.4466   0.2282
   0.000   0.5472   0.01054   0.00274  -0.0679   0.4400   0.2786
   0.250   0.5684   0.01044   0.00279  -0.0666   0.4335   0.3377
   0.500   0.5858   0.01024   0.00284  -0.0646   0.4269   0.4367
   1.000   0.7715   0.00994   0.00378  -0.0936   0.4020   0.9848
   1.500   0.8581   0.01033   0.00403  -0.1008   0.3849   0.9967
   2.000   0.9195   0.01063   0.00421  -0.1026   0.3705   1.0000
   2.250   0.9380   0.01079   0.00432  -0.1009   0.3633   1.0000
   2.500   0.9571   0.01094   0.00444  -0.0992   0.3579   1.0000
   2.750   0.9763   0.01108   0.00455  -0.0976   0.3522   1.0000
   3.000   0.9945   0.01126   0.00470  -0.0958   0.3470   1.0000
   3.250   1.0133   0.01142   0.00484  -0.0942   0.3424   1.0000
   3.500   1.0320   0.01158   0.00498  -0.0925   0.3369   1.0000
   3.750   1.0497   0.01177   0.00515  -0.0906   0.3322   1.0000
   4.000   1.0671   0.01196   0.00532  -0.0887   0.3280   1.0000
   4.250   1.0844   0.01211   0.00547  -0.0867   0.3240   1.0000
   4.500   1.1001   0.01228   0.00564  -0.0845   0.3197   1.0000
   4.750   1.1151   0.01247   0.00582  -0.0821   0.3157   1.0000
   5.000   1.1311   0.01267   0.00601  -0.0800   0.3121   1.0000
   5.250   1.1486   0.01283   0.00620  -0.0781   0.3085   1.0000
   5.500   1.1648   0.01305   0.00641  -0.0761   0.3031   1.0000
   5.750   1.1795   0.01333   0.00665  -0.0738   0.2974   1.0000
   6.000   1.1978   0.01351   0.00687  -0.0723   0.2932   1.0000
   6.250   1.2144   0.01376   0.00712  -0.0705   0.2872   1.0000
   6.500   1.2294   0.01408   0.00741  -0.0684   0.2815   1.0000
   6.750   1.2478   0.01430   0.00766  -0.0670   0.2768   1.0000
   7.000   1.2638   0.01460   0.00796  -0.0652   0.2702   1.0000
   7.250   1.2796   0.01493   0.00829  -0.0634   0.2638   1.0000
   7.500   1.2965   0.01524   0.00862  -0.0618   0.2575   1.0000
   7.750   1.3109   0.01564   0.00901  -0.0599   0.2510   1.0000
   8.000   1.3280   0.01597   0.00936  -0.0585   0.2446   1.0000
   8.250   1.3410   0.01648   0.00983  -0.0565   0.2333   1.0000
   8.500   1.3532   0.01704   0.01035  -0.0544   0.2214   1.0000
   8.750   1.3648   0.01767   0.01094  -0.0524   0.2082   1.0000
   9.000   1.3737   0.01846   0.01166  -0.0501   0.1913   1.0000
   9.250   1.3762   0.01963   0.01269  -0.0470   0.1669   1.0000
   9.500   1.3749   0.02109   0.01400  -0.0438   0.1404   1.0000
   9.750   1.3692   0.02292   0.01565  -0.0402   0.1117   1.0000
  10.000   1.3518   0.02565   0.01815  -0.0359   0.0733   1.0000
  10.250   1.3275   0.02913   0.02142  -0.0316   0.0319   1.0000
  10.500   1.3206   0.03157   0.02385  -0.0292   0.0194   1.0000
  10.750   1.3235   0.03337   0.02570  -0.0278   0.0170   1.0000
  11.000   1.3285   0.03507   0.02747  -0.0267   0.0161   1.0000
  11.250   1.3321   0.03696   0.02943  -0.0257   0.0154   1.0000
  11.500   1.3351   0.03898   0.03154  -0.0249   0.0149   1.0000
  11.750   1.3353   0.04139   0.03403  -0.0241   0.0142   1.0000
  12.000   1.3361   0.04384   0.03657  -0.0235   0.0137   1.0000
  12.250   1.3378   0.04627   0.03910  -0.0232   0.0133   1.0000
  12.500   1.3385   0.04891   0.04182  -0.0229   0.0129   1.0000
  12.750   1.3377   0.05181   0.04482  -0.0228   0.0125   1.0000
  13.000   1.3353   0.05495   0.04806  -0.0228   0.0122   1.0000
  13.250   1.3321   0.05824   0.05145  -0.0229   0.0120   1.0000
  13.500   1.3276   0.06177   0.05506  -0.0231   0.0116   1.0000
  13.750   1.3219   0.06549   0.05888  -0.0233   0.0115   1.0000
  14.000   1.3148   0.06943   0.06292  -0.0237   0.0113   1.0000
  14.250   1.3053   0.07377   0.06738  -0.0242   0.0111   1.0000
  14.500   1.2978   0.07792   0.07163  -0.0248   0.0111   1.0000
  14.750   1.2867   0.08265   0.07645  -0.0256   0.0108   1.0000
  15.000   1.2792   0.08693   0.08083  -0.0264   0.0108   1.0000
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