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Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 500,000
Max Cl/Cd: 95.44 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-500000.txt
Download as CSV file: xf-daytonwrightt1-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.3655   0.11162   0.10924  -0.0457   0.9989   0.0437
 -13.000  -0.3485   0.10909   0.10671  -0.0472   0.9976   0.0440
 -12.750  -0.5960   0.03943   0.03621  -0.1099   0.9774   0.0357
 -12.500  -0.5945   0.03364   0.02987  -0.1131   0.9722   0.0358
 -12.250  -0.5766   0.03009   0.02591  -0.1151   0.9698   0.0360
 -12.000  -0.5630   0.02792   0.02344  -0.1143   0.9635   0.0363
 -11.750  -0.5415   0.02600   0.02124  -0.1145   0.9594   0.0366
 -11.500  -0.5164   0.02444   0.01942  -0.1148   0.9565   0.0369
 -11.250  -0.4940   0.02345   0.01822  -0.1142   0.9520   0.0373
 -11.000  -0.4756   0.02197   0.01653  -0.1130   0.9462   0.0377
 -10.750  -0.4525   0.02035   0.01477  -0.1126   0.9425   0.0381
 -10.500  -0.4268   0.01929   0.01362  -0.1123   0.9395   0.0386
 -10.250  -0.4065   0.01856   0.01282  -0.1109   0.9332   0.0390
 -10.000  -0.3819   0.01782   0.01201  -0.1102   0.9287   0.0395
  -9.750  -0.3560   0.01713   0.01124  -0.1097   0.9251   0.0400
  -9.500  -0.3321   0.01654   0.01056  -0.1088   0.9203   0.0406
  -9.250  -0.3080   0.01596   0.00991  -0.1079   0.9149   0.0412
  -9.000  -0.2821   0.01541   0.00927  -0.1073   0.9106   0.0418
  -8.750  -0.2554   0.01494   0.00872  -0.1069   0.9068   0.0426
  -8.500  -0.2310   0.01458   0.00829  -0.1060   0.9011   0.0431
  -8.250  -0.2067   0.01382   0.00748  -0.1052   0.8959   0.0440
  -8.000  -0.1807   0.01328   0.00690  -0.1046   0.8917   0.0450
  -7.750  -0.1554   0.01291   0.00652  -0.1039   0.8864   0.0460
  -7.500  -0.1295   0.01256   0.00614  -0.1033   0.8808   0.0472
  -7.250  -0.1024   0.01222   0.00574  -0.1028   0.8761   0.0486
  -7.000  -0.0756   0.01196   0.00542  -0.1023   0.8709   0.0498
  -6.750  -0.0503   0.01152   0.00500  -0.1017   0.8648   0.0524
  -6.500  -0.0229   0.01126   0.00470  -0.1013   0.8596   0.0555
  -6.250   0.0038   0.01096   0.00440  -0.1008   0.8541   0.0600
  -6.000   0.0303   0.01068   0.00415  -0.1003   0.8475   0.0677
  -5.750   0.0577   0.01038   0.00388  -0.1000   0.8420   0.0825
  -5.500   0.0843   0.01018   0.00373  -0.0996   0.8353   0.0970
  -5.250   0.1114   0.00999   0.00356  -0.0992   0.8283   0.1092
  -5.000   0.1387   0.00982   0.00339  -0.0989   0.8209   0.1208
  -4.750   0.1652   0.00965   0.00323  -0.0983   0.8112   0.1329
  -4.500   0.1920   0.00950   0.00309  -0.0979   0.8019   0.1464
  -4.250   0.2189   0.00936   0.00296  -0.0975   0.7929   0.1618
  -4.000   0.2454   0.00922   0.00286  -0.0971   0.7832   0.1791
  -3.750   0.2723   0.00909   0.00275  -0.0967   0.7732   0.2003
  -3.500   0.2986   0.00899   0.00269  -0.0962   0.7615   0.2240
  -3.250   0.3250   0.00889   0.00265  -0.0958   0.7507   0.2475
  -2.750   0.3783   0.00880   0.00258  -0.0950   0.7288   0.2914
  -2.500   0.4049   0.00877   0.00256  -0.0947   0.7177   0.3089
  -2.250   0.4313   0.00876   0.00253  -0.0942   0.7058   0.3254
  -2.000   0.4574   0.00875   0.00251  -0.0938   0.6926   0.3424
  -1.750   0.4834   0.00875   0.00251  -0.0933   0.6792   0.3596
  -1.500   0.5093   0.00876   0.00251  -0.0929   0.6660   0.3769
  -1.250   0.5349   0.00877   0.00252  -0.0924   0.6533   0.3968
  -1.000   0.5599   0.00876   0.00253  -0.0918   0.6403   0.4230
  -0.750   0.5843   0.00867   0.00256  -0.0912   0.6271   0.4682
  -0.500   0.5947   0.00762   0.00271  -0.0873   0.6155   0.8774
  -0.250   0.6478   0.00782   0.00295  -0.0924   0.6003   0.9598
   0.000   0.6884   0.00806   0.00309  -0.0950   0.5855   0.9808
   0.750   0.8189   0.00866   0.00338  -0.1057   0.5323   1.0000
   1.000   0.8394   0.00883   0.00346  -0.1044   0.5160   1.0000
   1.250   0.8595   0.00901   0.00356  -0.1029   0.4992   1.0000
   1.500   0.8790   0.00921   0.00366  -0.1014   0.4815   1.0000
   1.750   0.8979   0.00943   0.00379  -0.0997   0.4632   1.0000
   2.000   0.9163   0.00967   0.00393  -0.0980   0.4445   1.0000
   2.250   0.9342   0.00993   0.00409  -0.0961   0.4258   1.0000
   2.500   0.9517   0.01020   0.00427  -0.0942   0.4076   1.0000
   2.750   0.9692   0.01049   0.00445  -0.0924   0.3906   1.0000
   3.000   0.9869   0.01077   0.00465  -0.0905   0.3750   1.0000
   3.250   1.0049   0.01105   0.00486  -0.0888   0.3612   1.0000
   3.500   1.0228   0.01133   0.00508  -0.0870   0.3494   1.0000
   3.750   1.0400   0.01164   0.00532  -0.0851   0.3386   1.0000
   4.000   1.0588   0.01191   0.00554  -0.0836   0.3281   1.0000
   4.250   1.0774   0.01220   0.00579  -0.0820   0.3188   1.0000
   4.500   1.0958   0.01251   0.00605  -0.0805   0.3104   1.0000
   4.750   1.1144   0.01279   0.00632  -0.0790   0.3041   1.0000
   5.000   1.1333   0.01305   0.00658  -0.0775   0.2979   1.0000
   5.250   1.1500   0.01341   0.00689  -0.0758   0.2918   1.0000
   5.500   1.1702   0.01366   0.00717  -0.0746   0.2870   1.0000
   5.750   1.1900   0.01395   0.00746  -0.0735   0.2821   1.0000
   6.000   1.2086   0.01431   0.00781  -0.0722   0.2775   1.0000
   6.250   1.2276   0.01468   0.00817  -0.0710   0.2731   1.0000
   6.500   1.2487   0.01494   0.00848  -0.0702   0.2688   1.0000
   6.750   1.2680   0.01528   0.00883  -0.0691   0.2637   1.0000
   7.000   1.2851   0.01576   0.00928  -0.0678   0.2582   1.0000
   7.250   1.3067   0.01601   0.00959  -0.0672   0.2536   1.0000
   7.500   1.3258   0.01638   0.00997  -0.0662   0.2483   1.0000
   7.750   1.3425   0.01690   0.01047  -0.0649   0.2433   1.0000
   8.000   1.3632   0.01721   0.01086  -0.0643   0.2391   1.0000
   8.250   1.3823   0.01760   0.01129  -0.0635   0.2338   1.0000
   8.500   1.3987   0.01815   0.01182  -0.0623   0.2287   1.0000
   8.750   1.4178   0.01857   0.01231  -0.0615   0.2240   1.0000
   9.000   1.4362   0.01902   0.01280  -0.0607   0.2180   1.0000
   9.250   1.4508   0.01969   0.01345  -0.0594   0.2115   1.0000
   9.500   1.4699   0.02013   0.01395  -0.0588   0.2038   1.0000
   9.750   1.4843   0.02084   0.01466  -0.0576   0.1955   1.0000
  10.000   1.4993   0.02154   0.01536  -0.0565   0.1839   1.0000
  10.250   1.5120   0.02241   0.01619  -0.0553   0.1688   1.0000
  10.500   1.5202   0.02359   0.01727  -0.0536   0.1457   1.0000
  10.750   1.5215   0.02529   0.01882  -0.0513   0.1229   1.0000
  11.000   1.5233   0.02700   0.02046  -0.0492   0.1085   1.0000
  11.250   1.5268   0.02867   0.02210  -0.0474   0.0980   1.0000
  11.500   1.5302   0.03039   0.02381  -0.0458   0.0886   1.0000
  11.750   1.5319   0.03230   0.02570  -0.0441   0.0786   1.0000
  12.000   1.5307   0.03452   0.02787  -0.0424   0.0648   1.0000
  12.250   1.5211   0.03759   0.03081  -0.0405   0.0452   1.0000
  12.500   1.5101   0.04097   0.03413  -0.0388   0.0335   1.0000
  12.750   1.5039   0.04411   0.03731  -0.0377   0.0291   1.0000
  13.000   1.5010   0.04703   0.04031  -0.0370   0.0269   1.0000
  13.250   1.4955   0.05036   0.04371  -0.0364   0.0253   1.0000
  13.500   1.4919   0.05362   0.04707  -0.0361   0.0243   1.0000
  13.750   1.4883   0.05698   0.05054  -0.0360   0.0234   1.0000
  14.000   1.4823   0.06071   0.05437  -0.0361   0.0227   1.0000
  14.250   1.4736   0.06491   0.05867  -0.0363   0.0221   1.0000
  14.500   1.4623   0.06956   0.06342  -0.0368   0.0216   1.0000
  15.000   1.4391   0.07930   0.07341  -0.0383   0.0208   1.0000
  15.250   1.4296   0.08402   0.07825  -0.0392   0.0204   1.0000
  15.500   1.4188   0.08903   0.08338  -0.0403   0.0201   1.0000
  15.750   1.4071   0.09421   0.08867  -0.0415   0.0198   1.0000
  16.000   1.3951   0.09949   0.09406  -0.0429   0.0195   1.0000
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