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Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 200,000
Max Cl/Cd: 65.69 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-200000-n5.txt
Download as CSV file: xf-daytonwrightt1-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.3593   0.11063   0.10673  -0.0457   1.0000   0.0367
 -13.000  -0.3716   0.10699   0.10313  -0.0454   1.0000   0.0371
 -12.500  -0.5854   0.04453   0.03998  -0.1013   0.9726   0.0368
 -12.250  -0.5931   0.03869   0.03357  -0.1039   0.9637   0.0370
 -12.000  -0.5815   0.03500   0.02938  -0.1055   0.9590   0.0375
 -11.750  -0.5678   0.03251   0.02646  -0.1055   0.9536   0.0380
 -11.500  -0.5510   0.03058   0.02416  -0.1051   0.9479   0.0384
 -11.250  -0.5267   0.02891   0.02236  -0.1056   0.9446   0.0389
 -11.000  -0.4992   0.02753   0.02085  -0.1064   0.9422   0.0394
 -10.750  -0.4821   0.02652   0.01971  -0.1048   0.9349   0.0398
 -10.500  -0.4567   0.02542   0.01847  -0.1048   0.9308   0.0403
 -10.250  -0.4289   0.02434   0.01724  -0.1052   0.9277   0.0408
 -10.000  -0.4059   0.02343   0.01620  -0.1045   0.9227   0.0414
  -9.750  -0.3830   0.02259   0.01521  -0.1037   0.9171   0.0420
  -9.500  -0.3559   0.02171   0.01419  -0.1037   0.9133   0.0427
  -9.250  -0.3269   0.02090   0.01323  -0.1039   0.9104   0.0435
  -9.000  -0.3054   0.02031   0.01252  -0.1026   0.9040   0.0443
  -8.750  -0.2801   0.01961   0.01176  -0.1022   0.8990   0.0453
  -8.500  -0.2519   0.01896   0.01108  -0.1022   0.8954   0.0463
  -8.250  -0.2263   0.01844   0.01051  -0.1017   0.8906   0.0473
  -8.000  -0.2023   0.01797   0.00998  -0.1008   0.8845   0.0484
  -7.750  -0.1746   0.01745   0.00939  -0.1006   0.8801   0.0498
  -7.500  -0.1459   0.01695   0.00880  -0.1005   0.8762   0.0513
  -7.250  -0.1232   0.01656   0.00840  -0.0994   0.8692   0.0529
  -7.000  -0.0958   0.01615   0.00796  -0.0991   0.8641   0.0554
  -6.750  -0.0663   0.01575   0.00750  -0.0992   0.8602   0.0591
  -6.500  -0.0430   0.01544   0.00722  -0.0982   0.8526   0.0634
  -6.250  -0.0153   0.01510   0.00685  -0.0979   0.8472   0.0698
  -6.000   0.0128   0.01477   0.00650  -0.0978   0.8420   0.0784
  -5.750   0.0378   0.01451   0.00627  -0.0971   0.8346   0.0876
  -5.500   0.0663   0.01423   0.00598  -0.0969   0.8290   0.0979
  -5.250   0.0926   0.01402   0.00578  -0.0965   0.8220   0.1084
  -5.000   0.1196   0.01382   0.00558  -0.0961   0.8149   0.1203
  -4.750   0.1479   0.01360   0.00536  -0.0960   0.8087   0.1332
  -4.500   0.1735   0.01343   0.00523  -0.0954   0.8001   0.1472
  -4.250   0.2021   0.01320   0.00503  -0.0954   0.7935   0.1671
  -4.000   0.2271   0.01304   0.00496  -0.0947   0.7833   0.1877
  -3.750   0.2542   0.01286   0.00480  -0.0943   0.7730   0.2084
  -3.500   0.2813   0.01270   0.00464  -0.0939   0.7615   0.2279
  -3.250   0.3070   0.01259   0.00453  -0.0932   0.7488   0.2459
  -3.000   0.3334   0.01250   0.00444  -0.0928   0.7371   0.2644
  -2.750   0.3602   0.01241   0.00433  -0.0924   0.7252   0.2832
  -2.500   0.3865   0.01235   0.00424  -0.0919   0.7118   0.3012
  -2.250   0.4123   0.01230   0.00418  -0.0913   0.6976   0.3188
  -2.000   0.4382   0.01226   0.00413  -0.0908   0.6834   0.3373
  -1.750   0.4638   0.01222   0.00409  -0.0902   0.6695   0.3571
  -1.500   0.4893   0.01219   0.00405  -0.0896   0.6560   0.3785
  -1.250   0.5145   0.01216   0.00402  -0.0891   0.6427   0.4015
  -1.000   0.5391   0.01212   0.00401  -0.0884   0.6296   0.4273
  -0.750   0.5629   0.01202   0.00402  -0.0876   0.6164   0.4660
  -0.500   0.5838   0.01114   0.00422  -0.0856   0.6035   0.8408
  -0.250   0.6451   0.01132   0.00442  -0.0923   0.5855   0.9541
   0.000   0.6856   0.01155   0.00453  -0.0950   0.5687   0.9820
   0.250   0.7317   0.01176   0.00461  -0.0991   0.5510   0.9969
   0.500   0.7599   0.01195   0.00469  -0.0993   0.5354   1.0000
   0.750   0.7803   0.01214   0.00478  -0.0979   0.5203   1.0000
   1.000   0.8002   0.01235   0.00489  -0.0964   0.5048   1.0000
   1.250   0.8197   0.01257   0.00501  -0.0949   0.4891   1.0000
   1.500   0.8388   0.01281   0.00515  -0.0933   0.4731   1.0000
   1.750   0.8575   0.01306   0.00531  -0.0916   0.4567   1.0000
   2.000   0.8757   0.01333   0.00548  -0.0898   0.4401   1.0000
   2.250   0.8934   0.01362   0.00567  -0.0880   0.4239   1.0000
   2.500   0.9110   0.01392   0.00587  -0.0862   0.4084   1.0000
   3.000   0.9470   0.01453   0.00633  -0.0827   0.3811   1.0000
   3.250   0.9654   0.01485   0.00659  -0.0811   0.3696   1.0000
   3.500   0.9834   0.01519   0.00687  -0.0795   0.3593   1.0000
   3.750   1.0024   0.01551   0.00715  -0.0781   0.3496   1.0000
   4.000   1.0209   0.01586   0.00745  -0.0766   0.3413   1.0000
   4.250   1.0400   0.01619   0.00777  -0.0752   0.3333   1.0000
   4.500   1.0583   0.01657   0.00810  -0.0738   0.3266   1.0000
   4.750   1.0774   0.01689   0.00844  -0.0724   0.3200   1.0000
   5.000   1.0950   0.01728   0.00880  -0.0709   0.3140   1.0000
   5.250   1.1135   0.01766   0.00918  -0.0695   0.3084   1.0000
   5.500   1.1320   0.01803   0.00956  -0.0682   0.3019   1.0000
   5.750   1.1490   0.01849   0.00997  -0.0667   0.2961   1.0000
   6.000   1.1682   0.01886   0.01040  -0.0656   0.2901   1.0000
   6.250   1.1864   0.01929   0.01084  -0.0643   0.2842   1.0000
   6.500   1.2038   0.01978   0.01131  -0.0630   0.2797   1.0000
   6.750   1.2236   0.02019   0.01178  -0.0621   0.2757   1.0000
   7.000   1.2428   0.02062   0.01228  -0.0612   0.2712   1.0000
   7.250   1.2603   0.02112   0.01279  -0.0600   0.2665   1.0000
   7.500   1.2771   0.02168   0.01334  -0.0588   0.2623   1.0000
   7.750   1.2958   0.02212   0.01390  -0.0579   0.2573   1.0000
   8.000   1.3127   0.02265   0.01449  -0.0568   0.2522   1.0000
   8.250   1.3281   0.02327   0.01512  -0.0555   0.2476   1.0000
   8.500   1.3450   0.02384   0.01576  -0.0544   0.2428   1.0000
   8.750   1.3606   0.02443   0.01644  -0.0533   0.2368   1.0000
   9.000   1.3733   0.02519   0.01722  -0.0518   0.2310   1.0000
   9.250   1.3885   0.02585   0.01798  -0.0508   0.2244   1.0000
   9.500   1.4010   0.02665   0.01883  -0.0494   0.2175   1.0000
   9.750   1.4134   0.02749   0.01973  -0.0482   0.2104   1.0000
  10.000   1.4251   0.02840   0.02071  -0.0469   0.2022   1.0000
  10.250   1.4365   0.02936   0.02175  -0.0457   0.1940   1.0000
  10.500   1.4452   0.03052   0.02294  -0.0444   0.1842   1.0000
  10.750   1.4546   0.03170   0.02417  -0.0432   0.1711   1.0000
  11.000   1.4599   0.03320   0.02566  -0.0418   0.1535   1.0000
  11.250   1.4584   0.03530   0.02766  -0.0400   0.1332   1.0000
  11.500   1.4544   0.03773   0.03001  -0.0383   0.1182   1.0000
  11.750   1.4522   0.04012   0.03239  -0.0369   0.1076   1.0000
  12.000   1.4513   0.04252   0.03482  -0.0358   0.0995   1.0000
  12.250   1.4483   0.04522   0.03756  -0.0348   0.0929   1.0000
  12.500   1.4484   0.04772   0.04013  -0.0340   0.0861   1.0000
  12.750   1.4448   0.05071   0.04318  -0.0334   0.0802   1.0000
  13.000   1.4426   0.05367   0.04622  -0.0331   0.0735   1.0000
  13.250   1.4386   0.05694   0.04957  -0.0329   0.0665   1.0000
  13.500   1.4316   0.06068   0.05337  -0.0328   0.0579   1.0000
  13.750   1.4210   0.06501   0.05773  -0.0330   0.0486   1.0000
  14.000   1.4077   0.06984   0.06259  -0.0335   0.0413   1.0000
  14.250   1.3936   0.07492   0.06773  -0.0342   0.0365   1.0000
  14.750   1.3664   0.08543   0.07841  -0.0362   0.0309   1.0000
  15.000   1.3525   0.09091   0.08399  -0.0375   0.0291   1.0000
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