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Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 50,000
Max Cl/Cd: 20.91 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-50000.txt
Download as CSV file: xf-daytonwrightt1-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3018   0.12022   0.11312  -0.0278   1.0000   0.2336
 -11.000  -0.3212   0.12008   0.11312  -0.0264   1.0000   0.2393
 -10.750  -0.3645   0.12226   0.11550  -0.0246   1.0000   0.2411
 -10.500  -0.3210   0.11465   0.10780  -0.0230   1.0000   0.2467
 -10.250  -0.3262   0.11299   0.10621  -0.0210   1.0000   0.2530
 -10.000  -0.3630   0.11407   0.10746  -0.0187   1.0000   0.2576
  -9.750  -0.3549   0.11011   0.10355  -0.0170   1.0000   0.2614
  -9.500  -0.3492   0.10757   0.10105  -0.0147   1.0000   0.2691
  -9.250  -0.3832   0.10795   0.10158  -0.0118   1.0000   0.2744
  -9.000  -0.4324   0.10907   0.10289  -0.0084   1.0000   0.2758
  -8.750  -0.3828   0.10264   0.09639  -0.0073   1.0000   0.2866
  -8.500  -0.4211   0.10281   0.09672  -0.0036   1.0000   0.2917
  -8.250  -0.4371   0.10060   0.09461  -0.0018   1.0000   0.2958
  -8.000  -0.4266   0.09770   0.09174   0.0010   1.0000   0.3041
  -7.750  -0.4721   0.09774   0.09191   0.0001   1.0000   0.3116
  -7.500  -0.4498   0.09343   0.08762   0.0044   1.0000   0.3175
  -7.250  -0.4799   0.09271   0.08697   0.0029   1.0000   0.3292
  -7.000  -0.4653   0.08879   0.08309   0.0071   1.0000   0.3342
  -6.750  -0.4801   0.08701   0.08133   0.0062   1.0000   0.3474
  -6.500  -0.4713   0.08383   0.07821   0.0097   1.0000   0.3536
  -6.250  -0.4760   0.08134   0.07573   0.0098   1.0000   0.3670
  -6.000  -0.4257   0.06124   0.05409  -0.0270   1.0000   0.1908
  -5.750  -0.4097   0.05822   0.05095  -0.0272   1.0000   0.1880
  -5.500  -0.3913   0.05481   0.04732  -0.0283   1.0000   0.1847
  -5.250  -0.3684   0.05066   0.04272  -0.0305   1.0000   0.1804
  -5.000  -0.3452   0.04745   0.03905  -0.0319   1.0000   0.1804
  -4.750  -0.3228   0.04527   0.03647  -0.0327   1.0000   0.1854
  -4.500  -0.2978   0.04293   0.03353  -0.0338   1.0000   0.1914
  -4.250  -0.2789   0.04215   0.03278  -0.0333   1.0000   0.1985
  -4.000  -0.2561   0.04097   0.03127  -0.0336   1.0000   0.2102
  -3.750  -0.2341   0.04027   0.03031  -0.0336   1.0000   0.2249
  -3.500  -0.2139   0.03993   0.02990  -0.0333   1.0000   0.2421
  -3.250  -0.1615   0.04038   0.03027  -0.0386   0.9880   0.2765
  -3.000  -0.1104   0.04073   0.03057  -0.0435   0.9740   0.3126
  -2.750  -0.0653   0.04087   0.03066  -0.0473   0.9604   0.3480
  -2.500  -0.0230   0.04091   0.03069  -0.0505   0.9466   0.3854
  -2.250   0.0204   0.04095   0.03065  -0.0538   0.9327   0.4303
  -2.000   0.0652   0.04082   0.03062  -0.0571   0.9188   0.4856
  -1.750   0.1124   0.04030   0.03056  -0.0606   0.9057   0.5660
  -1.500   0.1631   0.03929   0.03080  -0.0640   0.8908   1.0000
  -1.250   0.2028   0.04010   0.03109  -0.0668   0.8748   1.0000
  -1.000   0.2385   0.04083   0.03147  -0.0686   0.8587   1.0000
  -0.750   0.2725   0.04150   0.03188  -0.0700   0.8425   1.0000
  -0.500   0.3058   0.04212   0.03229  -0.0712   0.8264   1.0000
  -0.250   0.3389   0.04266   0.03266  -0.0722   0.8100   1.0000
   0.000   0.3714   0.04317   0.03302  -0.0731   0.7938   1.0000
   0.250   0.4041   0.04359   0.03332  -0.0738   0.7774   1.0000
   0.500   0.4359   0.04396   0.03359  -0.0743   0.7611   1.0000
   0.750   0.4675   0.04427   0.03381  -0.0746   0.7448   1.0000
   1.000   0.4987   0.04453   0.03400  -0.0748   0.7287   1.0000
   1.250   0.5296   0.04474   0.03415  -0.0749   0.7127   1.0000
   1.500   0.5592   0.04497   0.03433  -0.0747   0.6971   1.0000
   1.750   0.5892   0.04512   0.03444  -0.0745   0.6817   1.0000
   2.000   0.6207   0.04515   0.03444  -0.0744   0.6671   1.0000
   2.250   0.6781   0.04350   0.03276  -0.0764   0.6583   1.0000
   2.500   0.7007   0.04387   0.03312  -0.0752   0.6428   1.0000
   2.750   0.7211   0.04445   0.03369  -0.0740   0.6278   1.0000
   3.000   0.7404   0.04520   0.03444  -0.0727   0.6135   1.0000
   3.250   0.8155   0.04229   0.03154  -0.0763   0.6079   1.0000
   3.500   0.8229   0.04376   0.03301  -0.0738   0.5927   1.0000
   3.750   0.8246   0.04580   0.03505  -0.0712   0.5780   1.0000
   4.000   0.9005   0.04306   0.03233  -0.0751   0.5727   1.0000
   4.250   0.8856   0.04635   0.03565  -0.0711   0.5586   1.0000
   4.500   0.8508   0.05169   0.04100  -0.0666   0.5439   1.0000
   4.750   0.9405   0.04750   0.03687  -0.0707   0.5401   1.0000
   5.000   0.8689   0.05608   0.04544  -0.0643   0.5250   1.0000
   5.250   0.7943   0.06737   0.05672  -0.0622   0.5123   1.0000
   5.500   0.8266   0.06780   0.05720  -0.0622   0.5074   1.0000
   5.750   0.7792   0.07634   0.06574  -0.0614   0.5015   1.0000
   6.000   0.7603   0.08184   0.07127  -0.0611   0.4974   1.0000
   6.250   0.7535   0.08636   0.07582  -0.0612   0.4953   1.0000
   6.500   0.7368   0.09207   0.08156  -0.0617   0.4981   1.0000
   6.750   0.7312   0.09678   0.08633  -0.0622   0.5011   1.0000
   7.000   0.7353   0.10089   0.09049  -0.0630   0.5038   1.0000
   7.250   0.6195   0.11520   0.10492  -0.0674   0.6167   1.0000
   7.500   0.6451   0.11850   0.10827  -0.0687   0.6086   1.0000
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