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Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 200,000
Max Cl/Cd: 71.42 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-200000.txt
Download as CSV file: xf-daytonwrightt1-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3469   0.08884   0.08542  -0.0520   0.9839   0.0884
 -10.000  -0.3208   0.08634   0.08291  -0.0535   0.9820   0.0902
  -9.750  -0.4273   0.04945   0.04514  -0.0857   0.9576   0.0667
  -9.500  -0.4052   0.04426   0.03968  -0.0889   0.9548   0.0641
  -9.250  -0.4057   0.03949   0.03450  -0.0875   0.9453   0.0628
  -9.000  -0.3872   0.03400   0.02832  -0.0892   0.9415   0.0619
  -8.750  -0.3661   0.03134   0.02522  -0.0892   0.9364   0.0626
  -8.500  -0.3453   0.02932   0.02282  -0.0885   0.9300   0.0634
  -8.250  -0.3127   0.02731   0.02039  -0.0898   0.9269   0.0642
  -8.000  -0.2753   0.02567   0.01838  -0.0918   0.9248   0.0651
  -7.750  -0.2543   0.02482   0.01727  -0.0904   0.9176   0.0658
  -7.500  -0.2227   0.02327   0.01567  -0.0913   0.9135   0.0675
  -7.250  -0.1837   0.02242   0.01480  -0.0933   0.9110   0.0700
  -7.000  -0.1426   0.02160   0.01386  -0.0957   0.9091   0.0733
  -6.750  -0.1021   0.02056   0.01269  -0.0978   0.9074   0.0765
  -6.500  -0.0854   0.02007   0.01226  -0.0956   0.8979   0.0793
  -6.250  -0.0488   0.01938   0.01152  -0.0969   0.8946   0.0849
  -6.000  -0.0112   0.01853   0.01074  -0.0985   0.8922   0.0935
  -5.750   0.0129   0.01808   0.01032  -0.0976   0.8850   0.1048
  -5.500   0.0435   0.01754   0.00983  -0.0978   0.8796   0.1221
  -5.250   0.0793   0.01702   0.00930  -0.0989   0.8763   0.1411
  -5.000   0.1088   0.01667   0.00898  -0.0989   0.8707   0.1577
  -4.750   0.1350   0.01636   0.00872  -0.0983   0.8632   0.1740
  -4.500   0.1692   0.01584   0.00830  -0.0991   0.8593   0.1938
  -4.250   0.1946   0.01563   0.00817  -0.0984   0.8514   0.2150
  -4.000   0.2251   0.01532   0.00787  -0.0984   0.8448   0.2413
  -3.750   0.2575   0.01486   0.00750  -0.0988   0.8390   0.2670
  -3.500   0.2825   0.01461   0.00728  -0.0978   0.8287   0.2906
  -3.250   0.3136   0.01423   0.00692  -0.0979   0.8219   0.3149
  -3.000   0.3387   0.01402   0.00676  -0.0970   0.8118   0.3371
  -2.750   0.3676   0.01375   0.00649  -0.0968   0.8036   0.3608
  -2.500   0.3945   0.01347   0.00624  -0.0962   0.7937   0.3833
  -2.250   0.4203   0.01321   0.00605  -0.0955   0.7834   0.4069
  -2.000   0.4491   0.01286   0.00574  -0.0953   0.7746   0.4353
  -1.750   0.4722   0.01257   0.00561  -0.0942   0.7629   0.4700
  -1.500   0.4943   0.01195   0.00540  -0.0929   0.7531   0.5568
  -1.250   0.6035   0.01128   0.00560  -0.1081   0.7425   0.9919
  -1.000   0.6484   0.01126   0.00546  -0.1116   0.7298   1.0000
  -0.750   0.6724   0.01128   0.00537  -0.1107   0.7173   1.0000
  -0.500   0.6966   0.01131   0.00526  -0.1099   0.7045   1.0000
  -0.250   0.7204   0.01135   0.00518  -0.1089   0.6910   1.0000
   0.000   0.7427   0.01143   0.00517  -0.1078   0.6761   1.0000
   0.250   0.7650   0.01153   0.00518  -0.1066   0.6613   1.0000
   0.500   0.7872   0.01164   0.00520  -0.1054   0.6464   1.0000
   0.750   0.8091   0.01178   0.00524  -0.1042   0.6312   1.0000
   1.000   0.8306   0.01194   0.00531  -0.1030   0.6156   1.0000
   1.250   0.8517   0.01212   0.00538  -0.1016   0.5995   1.0000
   1.500   0.8722   0.01232   0.00548  -0.1002   0.5828   1.0000
   1.750   0.8921   0.01253   0.00561  -0.0986   0.5653   1.0000
   2.000   0.9113   0.01276   0.00574  -0.0969   0.5469   1.0000
   2.250   0.9298   0.01302   0.00589  -0.0952   0.5278   1.0000
   2.500   0.9478   0.01331   0.00606  -0.0933   0.5084   1.0000
   2.750   0.9653   0.01363   0.00625  -0.0913   0.4892   1.0000
   3.000   0.9825   0.01396   0.00648  -0.0894   0.4701   1.0000
   3.250   0.9999   0.01432   0.00674  -0.0875   0.4521   1.0000
   3.500   1.0176   0.01471   0.00703  -0.0858   0.4357   1.0000
   3.750   1.0357   0.01513   0.00733  -0.0841   0.4210   1.0000
   4.000   1.0545   0.01554   0.00765  -0.0826   0.4076   1.0000
   4.250   1.0740   0.01594   0.00802  -0.0813   0.3956   1.0000
   4.500   1.0944   0.01639   0.00839  -0.0802   0.3856   1.0000
   4.750   1.1149   0.01682   0.00877  -0.0792   0.3761   1.0000
   5.000   1.1361   0.01726   0.00919  -0.0783   0.3676   1.0000
   5.250   1.1572   0.01770   0.00958  -0.0774   0.3597   1.0000
   5.500   1.1789   0.01816   0.01002  -0.0766   0.3523   1.0000
   5.750   1.1991   0.01856   0.01043  -0.0756   0.3448   1.0000
   6.000   1.2220   0.01908   0.01089  -0.0752   0.3382   1.0000
   6.250   1.2420   0.01947   0.01136  -0.0741   0.3321   1.0000
   6.500   1.2640   0.01993   0.01180  -0.0735   0.3265   1.0000
   6.750   1.2863   0.02044   0.01232  -0.0730   0.3208   1.0000
   7.000   1.3051   0.02085   0.01281  -0.0719   0.3152   1.0000
   7.250   1.3260   0.02131   0.01326  -0.0711   0.3097   1.0000
   7.500   1.3477   0.02184   0.01381  -0.0706   0.3046   1.0000
   7.750   1.3650   0.02227   0.01437  -0.0692   0.2999   1.0000
   8.000   1.3833   0.02272   0.01485  -0.0680   0.2949   1.0000
   8.250   1.4043   0.02328   0.01539  -0.0675   0.2893   1.0000
   8.500   1.4140   0.02369   0.01596  -0.0648   0.2836   1.0000
   8.750   1.4272   0.02414   0.01642  -0.0629   0.2772   1.0000
   9.000   1.4397   0.02469   0.01704  -0.0610   0.2709   1.0000
   9.250   1.4493   0.02521   0.01767  -0.0587   0.2646   1.0000
   9.500   1.4649   0.02582   0.01821  -0.0575   0.2583   1.0000
   9.750   1.4711   0.02646   0.01907  -0.0549   0.2521   1.0000
  10.000   1.4799   0.02714   0.01980  -0.0528   0.2454   1.0000
  10.250   1.4880   0.02794   0.02070  -0.0508   0.2385   1.0000
  10.500   1.4938   0.02881   0.02165  -0.0487   0.2307   1.0000
  10.750   1.4999   0.02980   0.02274  -0.0467   0.2227   1.0000
  11.000   1.5045   0.03093   0.02393  -0.0448   0.2140   1.0000
  11.250   1.5104   0.03212   0.02526  -0.0432   0.2047   1.0000
  11.500   1.5140   0.03353   0.02671  -0.0416   0.1957   1.0000
  11.750   1.5182   0.03503   0.02832  -0.0402   0.1844   1.0000
  12.000   1.5212   0.03673   0.03010  -0.0389   0.1711   1.0000
  12.250   1.5206   0.03881   0.03220  -0.0375   0.1559   1.0000
  12.500   1.5164   0.04135   0.03472  -0.0362   0.1400   1.0000
  12.750   1.5086   0.04440   0.03772  -0.0349   0.1262   1.0000
  13.000   1.4981   0.04788   0.04118  -0.0338   0.1147   1.0000
  13.250   1.4856   0.05180   0.04509  -0.0330   0.1046   1.0000
  13.500   1.4733   0.05592   0.04925  -0.0326   0.0941   1.0000
  13.750   1.4587   0.06052   0.05389  -0.0324   0.0835   1.0000
  14.000   1.4417   0.06564   0.05906  -0.0326   0.0731   1.0000
  14.250   1.4239   0.07110   0.06455  -0.0331   0.0638   1.0000
  14.500   1.4064   0.07671   0.07021  -0.0339   0.0570   1.0000
  14.750   1.3877   0.08266   0.07621  -0.0350   0.0530   1.0000
  15.000   1.3727   0.08823   0.08187  -0.0362   0.0494   1.0000
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