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Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Dayton-Wright 6 (daytonwright6-il)
Reynolds number: 100,000
Max Cl/Cd: 45.62 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-daytonwright6-il-100000.txt
Download as CSV file: xf-daytonwright6-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3499   0.10508   0.10088  -0.0201   1.0000   0.1181
  -9.000  -0.3705   0.10396   0.09985  -0.0188   1.0000   0.1196
  -8.750  -0.4060   0.10228   0.09821  -0.0306   0.9898   0.1219
  -8.500  -0.3761   0.09654   0.09248  -0.0297   0.9861   0.1242
  -8.250  -0.3413   0.09278   0.08871  -0.0308   0.9813   0.1278
  -8.000  -0.3232   0.08886   0.08476  -0.0368   0.9720   0.1330
  -7.750  -0.3211   0.08301   0.07875  -0.0504   0.9566   0.1391
  -7.500  -0.2964   0.07959   0.07537  -0.0491   0.9488   0.1413
  -7.250  -0.2662   0.07597   0.07172  -0.0525   0.9417   0.1466
  -7.000  -0.1595   0.05920   0.05515  -0.0633   0.9036   0.1624
  -6.750  -0.2310   0.06807   0.06365  -0.0604   0.9182   0.1591
  -6.500  -0.2147   0.06475   0.06002  -0.0657   0.9049   0.1723
  -6.250  -0.1792   0.06102   0.05638  -0.0670   0.8996   0.1767
  -6.000  -0.1618   0.05805   0.05314  -0.0698   0.8862   0.1900
  -5.750  -0.1217   0.05429   0.04940  -0.0726   0.8821   0.1955
  -5.500  -0.1166   0.04109   0.03455  -0.0745   0.8681   0.1046
  -5.250  -0.0946   0.03786   0.03094  -0.0738   0.8570   0.1010
  -5.000  -0.0560   0.03457   0.02714  -0.0756   0.8514   0.1009
  -4.750  -0.0295   0.03238   0.02453  -0.0749   0.8405   0.1014
  -4.500   0.0155   0.02974   0.02139  -0.0772   0.8354   0.1023
  -4.250   0.0665   0.02750   0.01866  -0.0805   0.8310   0.1054
  -4.000   0.0978   0.02607   0.01708  -0.0805   0.8193   0.1101
  -3.750   0.1358   0.02502   0.01592  -0.0817   0.8096   0.1197
  -3.500   0.1804   0.02353   0.01437  -0.0840   0.8016   0.1340
  -3.250   0.2107   0.02250   0.01340  -0.0838   0.7895   0.1587
  -3.000   0.2566   0.02138   0.01234  -0.0865   0.7823   0.1988
  -2.750   0.2800   0.02098   0.01196  -0.0853   0.7685   0.2262
  -2.500   0.3059   0.02058   0.01165  -0.0846   0.7558   0.2592
  -2.250   0.5482   0.01661   0.00982  -0.1253   0.7487   1.0000
  -2.000   0.5685   0.01665   0.00961  -0.1237   0.7337   1.0000
  -1.750   0.5889   0.01669   0.00943  -0.1220   0.7194   1.0000
  -1.500   0.6100   0.01675   0.00929  -0.1206   0.7058   1.0000
  -1.250   0.6327   0.01680   0.00914  -0.1194   0.6932   1.0000
  -1.000   0.6578   0.01683   0.00895  -0.1186   0.6815   1.0000
  -0.750   0.6810   0.01692   0.00885  -0.1175   0.6692   1.0000
  -0.500   0.7009   0.01711   0.00890  -0.1159   0.6565   1.0000
  -0.250   0.7231   0.01730   0.00894  -0.1148   0.6449   1.0000
   0.000   0.7496   0.01746   0.00888  -0.1144   0.6343   1.0000
   0.250   0.7692   0.01774   0.00907  -0.1128   0.6223   1.0000
   0.500   0.7896   0.01806   0.00927  -0.1114   0.6109   1.0000
   0.750   0.8156   0.01832   0.00935  -0.1110   0.6009   1.0000
   1.000   0.8345   0.01869   0.00965  -0.1093   0.5898   1.0000
   1.250   0.8552   0.01908   0.00996  -0.1080   0.5798   1.0000
   1.500   0.8808   0.01940   0.01012  -0.1076   0.5703   1.0000
   1.750   0.8969   0.01987   0.01059  -0.1055   0.5599   1.0000
   2.000   0.9234   0.02024   0.01080  -0.1052   0.5514   1.0000
   2.250   0.9389   0.02073   0.01134  -0.1031   0.5419   1.0000
   2.500   0.9643   0.02116   0.01163  -0.1027   0.5341   1.0000
   2.750   0.9800   0.02166   0.01218  -0.1006   0.5250   1.0000
   3.000   1.0059   0.02209   0.01249  -0.1003   0.5177   1.0000
   3.250   1.0199   0.02266   0.01314  -0.0980   0.5092   1.0000
   3.500   1.0480   0.02307   0.01341  -0.0981   0.5029   1.0000
   3.750   1.0593   0.02374   0.01421  -0.0954   0.4950   1.0000
   4.000   1.0830   0.02416   0.01459  -0.0948   0.4883   1.0000
   4.250   1.1008   0.02479   0.01525  -0.0932   0.4817   1.0000
   4.500   1.1174   0.02539   0.01590  -0.0914   0.4748   1.0000
   4.750   1.1467   0.02579   0.01620  -0.0919   0.4695   1.0000
   5.000   1.1542   0.02662   0.01721  -0.0886   0.4626   1.0000
   5.250   1.1751   0.02713   0.01773  -0.0876   0.4566   1.0000
   5.500   1.2017   0.02764   0.01819  -0.0876   0.4517   1.0000
   5.750   1.2067   0.02857   0.01934  -0.0840   0.4451   1.0000
   6.000   1.2294   0.02905   0.01982  -0.0834   0.4396   1.0000
   6.250   1.2525   0.02965   0.02041  -0.0829   0.4348   1.0000
   6.500   1.2561   0.03070   0.02167  -0.0792   0.4287   1.0000
   6.750   1.2790   0.03117   0.02217  -0.0786   0.4234   1.0000
   7.000   1.3028   0.03178   0.02278  -0.0783   0.4187   1.0000
   7.250   1.3011   0.03306   0.02429  -0.0739   0.4130   1.0000
   7.500   1.3212   0.03365   0.02492  -0.0730   0.4079   1.0000
   7.750   1.3524   0.03403   0.02529  -0.0738   0.4033   1.0000
   8.000   1.3395   0.03569   0.02722  -0.0679   0.3977   1.0000
   8.250   1.3557   0.03640   0.02801  -0.0664   0.3926   1.0000
   8.500   1.3991   0.03639   0.02791  -0.0691   0.3879   1.0000
   8.750   1.3698   0.03858   0.03042  -0.0610   0.3825   1.0000
   9.000   1.3868   0.03904   0.03096  -0.0596   0.3766   1.0000
   9.250   1.4139   0.03889   0.03080  -0.0595   0.3695   1.0000
   9.500   1.4016   0.04025   0.03232  -0.0539   0.3634   1.0000
   9.750   1.4470   0.03877   0.03073  -0.0560   0.3537   1.0000
  10.000   1.4285   0.04024   0.03238  -0.0495   0.3483   1.0000
  10.250   1.2087   0.05794   0.05055  -0.0295   0.3522   1.0000
  10.500   1.2396   0.05679   0.04948  -0.0290   0.3458   1.0000
  10.750   1.1670   0.06738   0.06012  -0.0266   0.3397   1.0000
  11.000   1.2615   0.05793   0.05075  -0.0263   0.3318   1.0000
  11.250   1.2054   0.06677   0.05967  -0.0246   0.3266   1.0000
  11.500   1.4893   0.04171   0.03415  -0.0361   0.3059   1.0000
  11.750   1.4732   0.04347   0.03608  -0.0317   0.3001   1.0000
  12.000   1.4962   0.04275   0.03532  -0.0309   0.2913   1.0000
  12.250   1.4707   0.04545   0.03825  -0.0265   0.2862   1.0000
  12.500   1.4964   0.04443   0.03716  -0.0260   0.2771   1.0000
  12.750   1.4650   0.04806   0.04108  -0.0221   0.2726   1.0000
  13.000   1.4850   0.04724   0.04017  -0.0212   0.2628   1.0000
  13.250   1.4488   0.05188   0.04511  -0.0182   0.2584   1.0000
  13.500   1.4494   0.05299   0.04625  -0.0169   0.2494   1.0000
  13.750   1.4216   0.05768   0.05115  -0.0156   0.2442   1.0000
  14.000   1.4042   0.06142   0.05500  -0.0150   0.2363   1.0000
  14.250   1.3834   0.06612   0.05985  -0.0150   0.2300   1.0000
  14.500   1.3400   0.07458   0.06850  -0.0159   0.2268   1.0000
  14.750   1.3350   0.07752   0.07147  -0.0164   0.2162   1.0000
  15.000   1.2791   0.08898   0.08310  -0.0186   0.2156   1.0000
  15.500   1.2078   0.10662   0.10087  -0.0231   0.2036   1.0000
  15.750   0.9395   0.16881   0.16251  -0.0466   0.2008   1.0000
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