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Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Dayton-Wright 6 (daytonwright6-il)
Reynolds number: 500,000
Max Cl/Cd: 92.63 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-daytonwright6-il-500000.txt
Download as CSV file: xf-daytonwright6-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1942   0.08717   0.08489  -0.0683   0.9818   0.0400
 -10.500  -0.1824   0.08358   0.08130  -0.0717   0.9760   0.0409
 -10.250  -0.2029   0.07090   0.06864  -0.0887   0.9641   0.0445
 -10.000  -0.1851   0.06847   0.06621  -0.0906   0.9597   0.0450
  -9.750  -0.1709   0.06607   0.06380  -0.0928   0.9518   0.0455
  -9.500  -0.1532   0.06308   0.06079  -0.0969   0.9449   0.0462
  -9.250  -0.2472   0.02771   0.02349  -0.1165   0.9154   0.0378
  -9.000  -0.2353   0.02396   0.01944  -0.1155   0.9060   0.0372
  -8.750  -0.2120   0.02212   0.01725  -0.1154   0.8987   0.0374
  -8.500  -0.1944   0.02058   0.01545  -0.1139   0.8898   0.0374
  -8.250  -0.1702   0.01907   0.01365  -0.1135   0.8824   0.0374
  -8.000  -0.1504   0.01811   0.01248  -0.1119   0.8738   0.0375
  -7.750  -0.1249   0.01715   0.01131  -0.1115   0.8665   0.0376
  -7.500  -0.1034   0.01643   0.01043  -0.1101   0.8582   0.0377
  -7.250  -0.0784   0.01549   0.00932  -0.1095   0.8506   0.0379
  -7.000  -0.0564   0.01451   0.00821  -0.1083   0.8423   0.0382
  -6.750  -0.0317   0.01372   0.00732  -0.1076   0.8340   0.0388
  -6.500  -0.0095   0.01321   0.00678  -0.1062   0.8241   0.0395
  -6.250   0.0158   0.01281   0.00628  -0.1055   0.8146   0.0402
  -6.000   0.0374   0.01243   0.00586  -0.1040   0.8038   0.0407
  -5.750   0.0610   0.01208   0.00544  -0.1029   0.7943   0.0414
  -5.500   0.0840   0.01176   0.00505  -0.1016   0.7836   0.0419
  -5.250   0.1060   0.01147   0.00471  -0.1002   0.7719   0.0427
  -5.000   0.1284   0.01121   0.00439  -0.0988   0.7595   0.0433
  -4.750   0.1505   0.01100   0.00409  -0.0973   0.7450   0.0441
  -4.500   0.1709   0.01069   0.00373  -0.0955   0.7273   0.0453
  -4.250   0.1912   0.01050   0.00347  -0.0937   0.7051   0.0468
  -4.000   0.2111   0.01040   0.00326  -0.0918   0.6800   0.0491
  -3.750   0.2309   0.01037   0.00308  -0.0899   0.6550   0.0515
  -3.500   0.2504   0.01031   0.00294  -0.0879   0.6333   0.0569
  -3.250   0.2707   0.01024   0.00285  -0.0862   0.6151   0.0720
  -3.000   0.2916   0.01019   0.00280  -0.0847   0.5999   0.0964
  -2.750   0.3133   0.01019   0.00278  -0.0833   0.5868   0.1140
  -2.500   0.3363   0.01019   0.00277  -0.0822   0.5757   0.1269
  -2.250   0.3588   0.01019   0.00276  -0.0810   0.5661   0.1433
  -2.000   0.3815   0.01018   0.00276  -0.0799   0.5567   0.1600
  -1.750   0.4042   0.01016   0.00276  -0.0788   0.5482   0.1797
  -1.500   0.4265   0.01014   0.00276  -0.0776   0.5398   0.2060
  -1.250   0.4485   0.01008   0.00278  -0.0764   0.5324   0.2412
  -1.000   0.4697   0.00996   0.00281  -0.0750   0.5249   0.2980
  -0.750   0.5958   0.00874   0.00341  -0.0969   0.5125   0.9462
  -0.500   0.6319   0.00909   0.00365  -0.0984   0.5040   0.9737
  -0.250   0.6791   0.00933   0.00381  -0.1025   0.4956   0.9847
   0.000   0.7293   0.00955   0.00390  -0.1074   0.4869   0.9920
   0.250   0.7876   0.00961   0.00390  -0.1142   0.4776   0.9985
   0.500   0.8173   0.00972   0.00391  -0.1148   0.4698   1.0000
   0.750   0.8373   0.00978   0.00395  -0.1133   0.4620   1.0000
   1.000   0.8561   0.00990   0.00400  -0.1116   0.4545   1.0000
   1.250   0.8759   0.00998   0.00406  -0.1101   0.4473   1.0000
   1.500   0.8950   0.01010   0.00413  -0.1084   0.4397   1.0000
   1.750   0.9144   0.01023   0.00421  -0.1068   0.4323   1.0000
   2.000   0.9337   0.01035   0.00430  -0.1052   0.4245   1.0000
   2.250   0.9526   0.01050   0.00440  -0.1035   0.4170   1.0000
   2.500   0.9718   0.01064   0.00450  -0.1019   0.4092   1.0000
   2.750   0.9902   0.01082   0.00463  -0.1001   0.4023   1.0000
   3.000   1.0096   0.01096   0.00476  -0.0985   0.3951   1.0000
   3.250   1.0271   0.01118   0.00491  -0.0966   0.3885   1.0000
   3.500   1.0468   0.01131   0.00505  -0.0951   0.3820   1.0000
   3.750   1.0646   0.01151   0.00521  -0.0933   0.3758   1.0000
   4.000   1.0826   0.01172   0.00540  -0.0915   0.3703   1.0000
   4.250   1.1014   0.01189   0.00557  -0.0898   0.3647   1.0000
   4.500   1.1180   0.01212   0.00575  -0.0878   0.3591   1.0000
   4.750   1.1344   0.01233   0.00596  -0.0857   0.3545   1.0000
   5.000   1.1511   0.01249   0.00614  -0.0837   0.3496   1.0000
   5.250   1.1662   0.01270   0.00633  -0.0813   0.3448   1.0000
   5.500   1.1815   0.01299   0.00658  -0.0791   0.3404   1.0000
   5.750   1.1987   0.01312   0.00677  -0.0772   0.3352   1.0000
   6.000   1.2141   0.01335   0.00698  -0.0751   0.3295   1.0000
   6.250   1.2291   0.01365   0.00724  -0.0729   0.3240   1.0000
   6.500   1.2470   0.01382   0.00747  -0.0713   0.3191   1.0000
   6.750   1.2633   0.01407   0.00773  -0.0694   0.3143   1.0000
   7.000   1.2780   0.01444   0.00806  -0.0674   0.3090   1.0000
   7.250   1.2962   0.01461   0.00830  -0.0659   0.3037   1.0000
   7.500   1.3123   0.01490   0.00861  -0.0642   0.2985   1.0000
   7.750   1.3267   0.01531   0.00898  -0.0622   0.2935   1.0000
   8.000   1.3452   0.01552   0.00928  -0.0609   0.2884   1.0000
   8.250   1.3611   0.01585   0.00962  -0.0592   0.2827   1.0000
   8.500   1.3755   0.01625   0.01003  -0.0574   0.2763   1.0000
   8.750   1.3919   0.01659   0.01041  -0.0560   0.2690   1.0000
   9.000   1.4052   0.01706   0.01087  -0.0541   0.2613   1.0000
   9.250   1.4200   0.01751   0.01133  -0.0525   0.2518   1.0000
   9.500   1.4335   0.01803   0.01186  -0.0508   0.2413   1.0000
   9.750   1.4442   0.01872   0.01252  -0.0489   0.2275   1.0000
  10.000   1.4515   0.01963   0.01335  -0.0465   0.2088   1.0000
  10.250   1.4515   0.02100   0.01456  -0.0435   0.1815   1.0000
  10.500   1.4431   0.02300   0.01634  -0.0398   0.1489   1.0000
  10.750   1.4301   0.02545   0.01858  -0.0360   0.1145   1.0000
  11.000   1.4142   0.02830   0.02125  -0.0324   0.0840   1.0000
  11.250   1.3929   0.03181   0.02459  -0.0289   0.0527   1.0000
  11.500   1.3706   0.03574   0.02842  -0.0262   0.0289   1.0000
  11.750   1.3653   0.03847   0.03120  -0.0248   0.0245   1.0000
  12.000   1.3623   0.04117   0.03397  -0.0238   0.0225   1.0000
  12.250   1.3613   0.04379   0.03668  -0.0232   0.0215   1.0000
  12.500   1.3596   0.04659   0.03959  -0.0227   0.0207   1.0000
  12.750   1.3570   0.04962   0.04272  -0.0224   0.0201   1.0000
  13.000   1.3520   0.05301   0.04621  -0.0223   0.0195   1.0000
  13.250   1.3438   0.05689   0.05019  -0.0223   0.0190   1.0000
  13.500   1.3356   0.06085   0.05426  -0.0225   0.0187   1.0000
  13.750   1.3242   0.06530   0.05883  -0.0228   0.0182   1.0000
  14.000   1.3171   0.06927   0.06290  -0.0232   0.0179   1.0000
  14.250   1.3089   0.07343   0.06718  -0.0237   0.0179   1.0000
  14.500   1.2996   0.07783   0.07169  -0.0243   0.0176   1.0000
  14.750   1.2908   0.08224   0.07620  -0.0250   0.0173   1.0000
  15.000   1.2811   0.08682   0.08089  -0.0258   0.0171   1.0000
  15.250   1.2730   0.09127   0.08543  -0.0267   0.0169   1.0000
  15.500   1.2627   0.09610   0.09035  -0.0277   0.0167   1.0000
  15.750   1.2538   0.10077   0.09511  -0.0288   0.0165   1.0000
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