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Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 100,000
Max Cl/Cd: 51.15 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-100000.txt
Download as CSV file: xf-daytonwrightt1-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dayton-Wright T-1                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3805   0.10727   0.10261  -0.0243   1.0000   0.1393
 -10.000  -0.4292   0.10748   0.10296  -0.0232   1.0000   0.1410
  -9.750  -0.4792   0.10693   0.10252  -0.0238   1.0000   0.1415
  -9.500  -0.4774   0.10284   0.09849  -0.0213   1.0000   0.1425
  -9.250  -0.4576   0.09992   0.09558  -0.0165   1.0000   0.1442
  -9.000  -0.4557   0.09786   0.09356  -0.0138   1.0000   0.1461
  -8.750  -0.4622   0.09592   0.09166  -0.0120   1.0000   0.1484
  -8.500  -0.4647   0.09278   0.08853  -0.0158   0.9969   0.1541
  -8.250  -0.4523   0.08683   0.08251  -0.0254   0.9888   0.1599
  -8.000  -0.4246   0.08405   0.07972  -0.0260   0.9838   0.1643
  -7.750  -0.4113   0.07819   0.07367  -0.0380   0.9731   0.1751
  -7.500  -0.3819   0.07501   0.07051  -0.0387   0.9688   0.1779
  -7.250  -0.3876   0.04375   0.03677  -0.0595   0.9608   0.0989
  -7.000  -0.3532   0.04073   0.03360  -0.0624   0.9560   0.1008
  -6.750  -0.3262   0.03897   0.03167  -0.0631   0.9485   0.1026
  -6.500  -0.2908   0.03641   0.02863  -0.0654   0.9427   0.1038
  -6.250  -0.2543   0.03449   0.02629  -0.0674   0.9373   0.1062
  -6.000  -0.2243   0.03302   0.02438  -0.0680   0.9294   0.1097
  -5.750  -0.1817   0.03174   0.02290  -0.0709   0.9246   0.1160
  -5.500  -0.1555   0.03108   0.02211  -0.0708   0.9157   0.1224
  -5.250  -0.1153   0.03002   0.02094  -0.0730   0.9100   0.1320
  -5.000  -0.0833   0.02945   0.02032  -0.0738   0.9025   0.1461
  -4.750  -0.0492   0.02893   0.01984  -0.0750   0.8949   0.1650
  -4.500  -0.0029   0.02844   0.01932  -0.0781   0.8906   0.1919
  -4.250   0.0164   0.02838   0.01935  -0.0768   0.8792   0.2101
  -4.000   0.0612   0.02816   0.01914  -0.0796   0.8745   0.2404
  -3.750   0.0815   0.02813   0.01920  -0.0784   0.8630   0.2604
  -3.500   0.1264   0.02766   0.01881  -0.0810   0.8582   0.2907
  -3.250   0.1483   0.02757   0.01877  -0.0799   0.8468   0.3138
  -3.000   0.1944   0.02689   0.01818  -0.0826   0.8419   0.3494
  -2.750   0.2178   0.02669   0.01805  -0.0816   0.8303   0.3775
  -2.500   0.2660   0.02570   0.01721  -0.0844   0.8257   0.4192
  -2.250   0.2911   0.02532   0.01698  -0.0837   0.8146   0.4539
  -2.000   0.3385   0.02408   0.01603  -0.0862   0.8101   0.5132
  -1.750   0.4585   0.02175   0.01497  -0.1018   0.8100   1.0000
  -1.500   0.4856   0.02161   0.01464  -0.1012   0.7991   1.0000
  -1.250   0.5299   0.02091   0.01375  -0.1032   0.7926   1.0000
  -1.000   0.5532   0.02079   0.01353  -0.1018   0.7807   1.0000
  -0.750   0.5980   0.02002   0.01261  -0.1039   0.7746   1.0000
  -0.500   0.6186   0.01997   0.01248  -0.1021   0.7616   1.0000
  -0.250   0.6473   0.01969   0.01211  -0.1016   0.7507   1.0000
   0.000   0.6848   0.01913   0.01143  -0.1025   0.7417   1.0000
   0.250   0.7074   0.01904   0.01128  -0.1011   0.7281   1.0000
   0.500   0.7336   0.01887   0.01103  -0.1002   0.7151   1.0000
   0.750   0.7635   0.01860   0.01068  -0.1000   0.7027   1.0000
   1.000   0.7961   0.01829   0.01025  -0.1002   0.6902   1.0000
   1.250   0.8212   0.01821   0.01009  -0.0992   0.6747   1.0000
   1.500   0.8461   0.01818   0.00995  -0.0983   0.6584   1.0000
   1.750   0.8713   0.01818   0.00985  -0.0974   0.6413   1.0000
   2.000   0.8962   0.01824   0.00978  -0.0964   0.6237   1.0000
   2.250   0.9172   0.01843   0.00990  -0.0949   0.6045   1.0000
   2.500   0.9386   0.01867   0.01005  -0.0936   0.5853   1.0000
   2.750   0.9603   0.01895   0.01022  -0.0923   0.5661   1.0000
   3.000   0.9820   0.01927   0.01043  -0.0910   0.5475   1.0000
   3.250   1.0037   0.01963   0.01068  -0.0898   0.5295   1.0000
   3.500   1.0251   0.02004   0.01098  -0.0887   0.5125   1.0000
   3.750   1.0465   0.02048   0.01133  -0.0876   0.4967   1.0000
   4.000   1.0685   0.02097   0.01173  -0.0866   0.4825   1.0000
   4.250   1.0927   0.02147   0.01213  -0.0861   0.4702   1.0000
   4.500   1.1148   0.02202   0.01263  -0.0853   0.4584   1.0000
   4.750   1.1358   0.02264   0.01328  -0.0844   0.4477   1.0000
   5.000   1.1639   0.02322   0.01371  -0.0847   0.4390   1.0000
   5.250   1.1814   0.02389   0.01451  -0.0832   0.4294   1.0000
   5.500   1.2092   0.02451   0.01501  -0.0835   0.4218   1.0000
   5.750   1.2266   0.02524   0.01591  -0.0821   0.4138   1.0000
   6.000   1.2542   0.02591   0.01653  -0.0824   0.4075   1.0000
   6.250   1.2730   0.02674   0.01749  -0.0813   0.4008   1.0000
   6.500   1.2948   0.02737   0.01816  -0.0807   0.3934   1.0000
   6.750   1.3164   0.02805   0.01887  -0.0800   0.3857   1.0000
   7.000   1.3345   0.02865   0.01955  -0.0788   0.3775   1.0000
   7.250   1.3570   0.02929   0.02018  -0.0783   0.3699   1.0000
   7.500   1.3725   0.02999   0.02102  -0.0767   0.3624   1.0000
   7.750   1.4045   0.03065   0.02156  -0.0779   0.3563   1.0000
   8.000   1.4121   0.03162   0.02285  -0.0751   0.3502   1.0000
   8.250   1.4323   0.03233   0.02363  -0.0743   0.3438   1.0000
   8.500   1.4555   0.03313   0.02448  -0.0741   0.3376   1.0000
   8.750   1.4644   0.03407   0.02565  -0.0716   0.3310   1.0000
   9.000   1.4947   0.03463   0.02614  -0.0725   0.3242   1.0000
   9.250   1.4983   0.03575   0.02754  -0.0693   0.3177   1.0000
   9.500   1.5187   0.03618   0.02799  -0.0686   0.3094   1.0000
   9.750   1.5239   0.03705   0.02903  -0.0656   0.3012   1.0000
  10.000   1.5500   0.03703   0.02882  -0.0657   0.2903   1.0000
  10.250   1.5374   0.03804   0.03016  -0.0600   0.2827   1.0000
  10.500   1.5510   0.03813   0.03016  -0.0582   0.2725   1.0000
  10.750   1.5398   0.03903   0.03128  -0.0530   0.2645   1.0000
  11.000   1.5435   0.03950   0.03173  -0.0501   0.2551   1.0000
  11.250   1.5377   0.04034   0.03267  -0.0462   0.2463   1.0000
  11.500   1.5315   0.04152   0.03396  -0.0428   0.2379   1.0000
  11.750   1.5311   0.04241   0.03487  -0.0402   0.2289   1.0000
  12.000   1.5190   0.04435   0.03703  -0.0369   0.2208   1.0000
  12.250   1.5212   0.04538   0.03801  -0.0350   0.2120   1.0000
  12.500   1.5039   0.04815   0.04107  -0.0322   0.2038   1.0000
  12.750   1.4989   0.05004   0.04299  -0.0305   0.1953   1.0000
  13.000   1.4848   0.05306   0.04622  -0.0288   0.1865   1.0000
  13.250   1.4729   0.05612   0.04940  -0.0276   0.1778   1.0000
  13.500   1.4624   0.05920   0.05251  -0.0269   0.1688   1.0000
  13.750   1.4450   0.06365   0.05716  -0.0266   0.1593   1.0000
  14.000   1.4293   0.06811   0.06168  -0.0267   0.1499   1.0000
  14.250   1.4129   0.07288   0.06642  -0.0272   0.1404   1.0000
  14.500   1.3934   0.07842   0.07198  -0.0281   0.1309   1.0000
  14.750   1.3721   0.08446   0.07805  -0.0292   0.1214   1.0000
  15.000   1.3519   0.09041   0.08394  -0.0304   0.1116   1.0000
  15.250   1.3337   0.09610   0.08952  -0.0315   0.1016   1.0000
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