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Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 50,000
Max Cl/Cd: 33.39 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-50000-n5.txt
Download as CSV file: xf-daytonwrightt1-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3625   0.10569   0.09849  -0.0381   1.0000   0.0857
 -10.750  -0.3744   0.10319   0.09607  -0.0370   1.0000   0.0855
 -10.500  -0.3883   0.10070   0.09368  -0.0358   1.0000   0.0852
 -10.250  -0.4049   0.09822   0.09129  -0.0343   1.0000   0.0849
 -10.000  -0.4256   0.09575   0.08892  -0.0327   1.0000   0.0843
  -9.750  -0.4479   0.09298   0.08624  -0.0315   1.0000   0.0837
  -9.500  -0.4661   0.08940   0.08273  -0.0314   1.0000   0.0831
  -9.250  -0.4735   0.08406   0.07737  -0.0348   0.9969   0.0824
  -9.000  -0.4693   0.07543   0.06856  -0.0435   0.9886   0.0813
  -8.750  -0.4635   0.06627   0.05906  -0.0513   0.9811   0.0807
  -8.500  -0.4519   0.06002   0.05246  -0.0556   0.9738   0.0809
  -8.250  -0.4333   0.05584   0.04798  -0.0584   0.9675   0.0820
  -8.000  -0.4125   0.05246   0.04430  -0.0605   0.9608   0.0841
  -7.750  -0.3899   0.04848   0.03983  -0.0631   0.9549   0.0866
  -7.500  -0.3689   0.04463   0.03535  -0.0645   0.9480   0.0889
  -7.250  -0.3392   0.04108   0.03103  -0.0668   0.9431   0.0911
  -7.000  -0.3149   0.03975   0.02962  -0.0669   0.9360   0.0932
  -6.750  -0.2845   0.03848   0.02817  -0.0680   0.9300   0.0970
  -6.500  -0.2514   0.03685   0.02605  -0.0696   0.9249   0.1031
  -6.250  -0.2267   0.03592   0.02505  -0.0695   0.9170   0.1077
  -6.000  -0.1918   0.03483   0.02375  -0.0711   0.9117   0.1147
  -5.750  -0.1648   0.03406   0.02286  -0.0712   0.9043   0.1227
  -5.500  -0.1329   0.03331   0.02191  -0.0721   0.8976   0.1347
  -5.250  -0.0965   0.03274   0.02126  -0.0738   0.8925   0.1500
  -5.000  -0.0729   0.03243   0.02088  -0.0732   0.8832   0.1652
  -4.750  -0.0360   0.03207   0.02062  -0.0750   0.8779   0.1851
  -4.500  -0.0126   0.03191   0.02046  -0.0743   0.8685   0.2028
  -4.250   0.0233   0.03160   0.02013  -0.0757   0.8625   0.2247
  -4.000   0.0494   0.03145   0.01993  -0.0754   0.8537   0.2443
  -3.750   0.0840   0.03120   0.01964  -0.0765   0.8469   0.2686
  -3.500   0.1119   0.03106   0.01952  -0.0765   0.8385   0.2913
  -3.250   0.1442   0.03086   0.01926  -0.0772   0.8309   0.3190
  -3.000   0.1734   0.03066   0.01912  -0.0773   0.8227   0.3460
  -2.750   0.2038   0.03040   0.01890  -0.0776   0.8144   0.3764
  -2.500   0.2332   0.03011   0.01867  -0.0778   0.8061   0.4089
  -2.250   0.2632   0.02967   0.01837  -0.0779   0.7975   0.4455
  -2.000   0.2892   0.02921   0.01814  -0.0774   0.7880   0.4905
  -1.750   0.3638   0.02752   0.01787  -0.0848   0.7823   1.0000
  -1.500   0.3931   0.02748   0.01755  -0.0847   0.7720   1.0000
  -1.250   0.4267   0.02727   0.01711  -0.0851   0.7627   1.0000
  -1.000   0.4482   0.02736   0.01704  -0.0838   0.7500   1.0000
  -0.750   0.4779   0.02722   0.01672  -0.0836   0.7398   1.0000
  -0.500   0.5084   0.02702   0.01637  -0.0834   0.7296   1.0000
  -0.250   0.5297   0.02710   0.01634  -0.0820   0.7165   1.0000
   0.000   0.5563   0.02701   0.01614  -0.0813   0.7050   1.0000
   0.250   0.5905   0.02665   0.01565  -0.0817   0.6953   1.0000
   0.750   0.6353   0.02675   0.01560  -0.0791   0.6682   1.0000
   1.000   0.6624   0.02666   0.01542  -0.0785   0.6556   1.0000
   1.250   0.6951   0.02637   0.01502  -0.0786   0.6443   1.0000
   1.500   0.7183   0.02645   0.01503  -0.0775   0.6298   1.0000
   1.750   0.7412   0.02657   0.01510  -0.0764   0.6151   1.0000
   2.000   0.7648   0.02668   0.01515  -0.0754   0.6003   1.0000
   2.250   0.7889   0.02681   0.01521  -0.0745   0.5855   1.0000
   2.500   0.8133   0.02696   0.01530  -0.0736   0.5709   1.0000
   2.750   0.8379   0.02714   0.01540  -0.0729   0.5562   1.0000
   3.000   0.8628   0.02733   0.01551  -0.0722   0.5419   1.0000
   3.250   0.8866   0.02760   0.01572  -0.0714   0.5276   1.0000
   3.500   0.9066   0.02804   0.01613  -0.0701   0.5128   1.0000
   3.750   0.9269   0.02850   0.01657  -0.0690   0.4986   1.0000
   4.000   0.9480   0.02897   0.01701  -0.0680   0.4853   1.0000
   4.250   0.9713   0.02940   0.01738  -0.0673   0.4732   1.0000
   4.500   0.9945   0.02987   0.01781  -0.0667   0.4618   1.0000
   4.750   1.0132   0.03057   0.01855  -0.0655   0.4505   1.0000
   5.000   1.0379   0.03108   0.01903  -0.0652   0.4409   1.0000
   5.250   1.0577   0.03177   0.01976  -0.0643   0.4309   1.0000
   5.500   1.0788   0.03247   0.02048  -0.0636   0.4219   1.0000
   5.750   1.1010   0.03313   0.02117  -0.0630   0.4135   1.0000
   6.000   1.1212   0.03394   0.02204  -0.0623   0.4058   1.0000
   6.250   1.1413   0.03479   0.02296  -0.0616   0.3986   1.0000
   6.500   1.1675   0.03545   0.02365  -0.0616   0.3925   1.0000
   6.750   1.1795   0.03663   0.02500  -0.0599   0.3853   1.0000
   7.000   1.2047   0.03731   0.02571  -0.0599   0.3792   1.0000
   7.250   1.2187   0.03849   0.02702  -0.0586   0.3731   1.0000
   7.500   1.2320   0.03970   0.02840  -0.0571   0.3673   1.0000
   7.750   1.2598   0.04040   0.02915  -0.0575   0.3621   1.0000
   8.000   1.2638   0.04194   0.03089  -0.0550   0.3564   1.0000
   8.250   1.2722   0.04322   0.03230  -0.0530   0.3499   1.0000
   8.500   1.2946   0.04380   0.03292  -0.0525   0.3428   1.0000
   8.750   1.2860   0.04571   0.03504  -0.0487   0.3354   1.0000
   9.000   1.3142   0.04579   0.03508  -0.0487   0.3273   1.0000
   9.250   1.2958   0.04839   0.03794  -0.0444   0.3205   1.0000
   9.500   1.3201   0.04867   0.03823  -0.0440   0.3131   1.0000
   9.750   1.3068   0.05136   0.04115  -0.0408   0.3073   1.0000
  10.000   1.3008   0.05374   0.04372  -0.0385   0.3009   1.0000
  10.250   1.3310   0.05366   0.04366  -0.0385   0.2946   1.0000
  10.500   1.2855   0.05929   0.04960  -0.0346   0.2891   1.0000
  10.750   1.2870   0.06140   0.05184  -0.0334   0.2827   1.0000
  11.000   1.2908   0.06339   0.05395  -0.0323   0.2767   1.0000
  11.250   1.1879   0.07774   0.06853  -0.0317   0.2688   1.0000
  11.500   1.2622   0.07123   0.06209  -0.0302   0.2638   1.0000
  11.750   1.1108   0.09539   0.08634  -0.0347   0.2501   1.0000
  12.000   1.1623   0.09021   0.08131  -0.0321   0.2474   1.0000
  12.500   1.1167   0.10398   0.09522  -0.0351   0.2297   1.0000
  12.750   1.0631   0.11735   0.10860  -0.0396   0.2158   1.0000
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