Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 100,000
Max Cl/Cd: 50.44 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-100000-n5.txt
Download as CSV file: xf-daytonwrightt1-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3807   0.09094   0.08583  -0.0479   0.9924   0.0549
 -10.750  -0.3842   0.08432   0.07921  -0.0541   0.9857   0.0544
 -10.500  -0.4947   0.05033   0.04438  -0.0832   0.9618   0.0520
 -10.250  -0.4819   0.04543   0.03907  -0.0863   0.9570   0.0525
 -10.000  -0.4736   0.04241   0.03574  -0.0859   0.9488   0.0529
  -9.750  -0.4517   0.03979   0.03282  -0.0872   0.9443   0.0538
  -9.500  -0.4316   0.03773   0.03047  -0.0875   0.9390   0.0549
  -9.250  -0.4134   0.03564   0.02804  -0.0872   0.9325   0.0562
  -9.000  -0.3873   0.03331   0.02527  -0.0882   0.9286   0.0575
  -8.750  -0.3604   0.03130   0.02283  -0.0888   0.9248   0.0586
  -8.500  -0.3416   0.02988   0.02105  -0.0875   0.9174   0.0595
  -8.250  -0.3112   0.02871   0.01982  -0.0884   0.9136   0.0607
  -8.000  -0.2768   0.02768   0.01870  -0.0898   0.9109   0.0623
  -7.750  -0.2563   0.02696   0.01787  -0.0885   0.9036   0.0639
  -7.500  -0.2267   0.02610   0.01682  -0.0889   0.8988   0.0668
  -7.250  -0.1930   0.02519   0.01578  -0.0900   0.8955   0.0698
  -7.000  -0.1656   0.02457   0.01515  -0.0899   0.8903   0.0728
  -6.750  -0.1409   0.02395   0.01444  -0.0893   0.8835   0.0764
  -6.500  -0.1084   0.02319   0.01361  -0.0900   0.8797   0.0811
  -6.250  -0.0747   0.02255   0.01293  -0.0909   0.8763   0.0883
  -6.000  -0.0552   0.02220   0.01259  -0.0893   0.8673   0.0956
  -5.750  -0.0226   0.02165   0.01202  -0.0901   0.8631   0.1071
  -5.500   0.0073   0.02122   0.01156  -0.0903   0.8580   0.1196
  -5.250   0.0314   0.02095   0.01129  -0.0894   0.8501   0.1325
  -5.000   0.0646   0.02053   0.01090  -0.0902   0.8458   0.1498
  -4.750   0.0895   0.02031   0.01075  -0.0896   0.8383   0.1679
  -4.500   0.1181   0.02002   0.01053  -0.0895   0.8318   0.1877
  -4.250   0.1523   0.01961   0.01014  -0.0904   0.8277   0.2080
  -4.000   0.1738   0.01950   0.01007  -0.0891   0.8180   0.2248
  -3.750   0.2062   0.01916   0.00974  -0.0896   0.8126   0.2463
  -3.500   0.2312   0.01902   0.00962  -0.0888   0.8039   0.2667
  -3.250   0.2615   0.01873   0.00938  -0.0889   0.7970   0.2882
  -3.000   0.2882   0.01854   0.00922  -0.0884   0.7879   0.3098
  -2.750   0.3188   0.01824   0.00891  -0.0884   0.7795   0.3337
  -2.500   0.3443   0.01805   0.00875  -0.0876   0.7682   0.3563
  -2.250   0.3765   0.01767   0.00839  -0.0880   0.7597   0.3824
  -2.000   0.4017   0.01748   0.00825  -0.0873   0.7477   0.4082
  -1.750   0.4279   0.01723   0.00808  -0.0867   0.7364   0.4385
  -1.500   0.4564   0.01678   0.00777  -0.0865   0.7265   0.4831
  -1.250   0.5212   0.01565   0.00788  -0.0927   0.7138   0.9397
  -1.000   0.5865   0.01563   0.00771  -0.1002   0.6996   1.0000
  -0.750   0.6102   0.01566   0.00759  -0.0992   0.6861   1.0000
  -0.500   0.6343   0.01569   0.00748  -0.0982   0.6727   1.0000
  -0.250   0.6585   0.01573   0.00739  -0.0973   0.6591   1.0000
   0.000   0.6823   0.01580   0.00732  -0.0964   0.6452   1.0000
   0.250   0.7043   0.01593   0.00733  -0.0952   0.6305   1.0000
   0.500   0.7264   0.01606   0.00737  -0.0940   0.6158   1.0000
   0.750   0.7483   0.01622   0.00742  -0.0928   0.6012   1.0000
   1.000   0.7701   0.01639   0.00749  -0.0915   0.5864   1.0000
   1.250   0.7915   0.01658   0.00758  -0.0903   0.5710   1.0000
   1.500   0.8124   0.01680   0.00769  -0.0889   0.5552   1.0000
   1.750   0.8329   0.01703   0.00782  -0.0875   0.5389   1.0000
   2.000   0.8531   0.01728   0.00799  -0.0861   0.5226   1.0000
   2.250   0.8730   0.01755   0.00817  -0.0846   0.5063   1.0000
   2.500   0.8929   0.01785   0.00837  -0.0832   0.4905   1.0000
   2.750   0.9125   0.01816   0.00860  -0.0818   0.4749   1.0000
   3.000   0.9320   0.01850   0.00885  -0.0804   0.4599   1.0000
   3.250   0.9513   0.01886   0.00913  -0.0789   0.4451   1.0000
   3.500   0.9704   0.01924   0.00945  -0.0775   0.4308   1.0000
   3.750   0.9895   0.01964   0.00979  -0.0762   0.4175   1.0000
   4.000   1.0088   0.02006   0.01014  -0.0748   0.4054   1.0000
   4.250   1.0281   0.02050   0.01049  -0.0736   0.3945   1.0000
   4.500   1.0478   0.02093   0.01093  -0.0724   0.3843   1.0000
   4.750   1.0679   0.02140   0.01133  -0.0713   0.3759   1.0000
   5.000   1.0880   0.02186   0.01181  -0.0703   0.3675   1.0000
   5.250   1.1087   0.02237   0.01225  -0.0694   0.3607   1.0000
   5.500   1.1291   0.02285   0.01279  -0.0685   0.3535   1.0000
   5.750   1.1498   0.02336   0.01329  -0.0676   0.3472   1.0000
   6.000   1.1707   0.02389   0.01383  -0.0669   0.3412   1.0000
   6.250   1.1907   0.02442   0.01442  -0.0659   0.3350   1.0000
   6.500   1.2120   0.02497   0.01495  -0.0653   0.3299   1.0000
   6.750   1.2320   0.02554   0.01557  -0.0644   0.3245   1.0000
   7.000   1.2495   0.02610   0.01622  -0.0632   0.3183   1.0000
   7.250   1.2688   0.02667   0.01675  -0.0622   0.3124   1.0000
   7.500   1.2826   0.02727   0.01747  -0.0604   0.3056   1.0000
   7.750   1.2976   0.02787   0.01811  -0.0589   0.2990   1.0000
   8.000   1.3143   0.02850   0.01878  -0.0576   0.2933   1.0000
   8.250   1.3274   0.02918   0.01961  -0.0559   0.2872   1.0000
   8.500   1.3433   0.02984   0.02032  -0.0547   0.2821   1.0000
   8.750   1.3610   0.03053   0.02105  -0.0538   0.2777   1.0000
   9.000   1.3732   0.03133   0.02206  -0.0521   0.2725   1.0000
   9.250   1.3865   0.03210   0.02293  -0.0507   0.2674   1.0000
   9.500   1.4028   0.03282   0.02365  -0.0496   0.2627   1.0000
   9.750   1.4110   0.03380   0.02486  -0.0477   0.2573   1.0000
  10.000   1.4200   0.03474   0.02594  -0.0459   0.2515   1.0000
  10.250   1.4307   0.03561   0.02683  -0.0444   0.2458   1.0000
  10.500   1.4328   0.03691   0.02837  -0.0422   0.2387   1.0000
  10.750   1.4368   0.03807   0.02958  -0.0403   0.2315   1.0000
  11.000   1.4371   0.03960   0.03130  -0.0382   0.2233   1.0000
  11.250   1.4376   0.04113   0.03288  -0.0364   0.2152   1.0000
  11.500   1.4363   0.04303   0.03498  -0.0348   0.2061   1.0000
  11.750   1.4345   0.04499   0.03700  -0.0333   0.1977   1.0000
  12.000   1.4313   0.04734   0.03953  -0.0320   0.1875   1.0000
  12.250   1.4265   0.04995   0.04228  -0.0310   0.1766   1.0000
  12.500   1.4202   0.05290   0.04532  -0.0302   0.1650   1.0000
  12.750   1.4120   0.05624   0.04873  -0.0297   0.1532   1.0000
  13.000   1.4018   0.06002   0.05254  -0.0295   0.1427   1.0000
  13.250   1.3906   0.06415   0.05673  -0.0295   0.1336   1.0000
  13.500   1.3777   0.06870   0.06134  -0.0299   0.1263   1.0000
  13.750   1.3623   0.07377   0.06646  -0.0305   0.1200   1.0000
  14.000   1.3470   0.07908   0.07186  -0.0314   0.1145   1.0000
  14.250   1.3302   0.08479   0.07766  -0.0327   0.1094   1.0000
  14.500   1.3116   0.09088   0.08380  -0.0342   0.1052   1.0000
<< Back to Dayton-Wright T-1 (daytonwrightt1-il)

Polar data table (+)

Polar graphs


<< Back to Dayton-Wright T-1 (daytonwrightt1-il)