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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 100,000
Max Cl/Cd: 63.29 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae51-il-100000-n5.txt
Download as CSV file: xf-dae51-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-51 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3448   0.09744   0.09273  -0.0404   1.0000   0.0544
  -8.000  -0.3588   0.09602   0.09144  -0.0392   1.0000   0.0546
  -7.750  -0.3755   0.09484   0.09038  -0.0371   1.0000   0.0547
  -7.500  -0.3619   0.09005   0.08559  -0.0453   0.9926   0.0549
  -7.250  -0.3387   0.08400   0.07948  -0.0556   0.9847   0.0550
  -6.750  -0.3025   0.06951   0.06487  -0.0634   0.9735   0.0331
  -6.500  -0.2776   0.06343   0.05868  -0.0717   0.9663   0.0330
  -6.250  -0.2498   0.05695   0.05200  -0.0802   0.9597   0.0329
  -6.000  -0.2240   0.05150   0.04635  -0.0862   0.9530   0.0325
  -5.750  -0.1970   0.04632   0.04091  -0.0914   0.9463   0.0317
  -5.500  -0.1660   0.04084   0.03502  -0.0968   0.9410   0.0310
  -5.250  -0.1388   0.03627   0.02996  -0.1000   0.9335   0.0305
  -5.000  -0.1055   0.03215   0.02524  -0.1032   0.9290   0.0304
  -4.750  -0.0766   0.02909   0.02164  -0.1046   0.9224   0.0307
  -4.500  -0.0451   0.02662   0.01859  -0.1059   0.9169   0.0318
  -4.250  -0.0109   0.02464   0.01606  -0.1073   0.9130   0.0341
  -4.000   0.0150   0.02325   0.01451  -0.1074   0.9055   0.0357
  -3.750   0.0462   0.02192   0.01295  -0.1080   0.9004   0.0373
  -3.500   0.0754   0.02081   0.01164  -0.1082   0.8946   0.0394
  -3.250   0.1039   0.02007   0.01071  -0.1081   0.8880   0.0434
  -3.000   0.1340   0.01904   0.00970  -0.1086   0.8834   0.0480
  -2.750   0.1601   0.01842   0.00899  -0.1082   0.8757   0.0530
  -2.500   0.1894   0.01777   0.00831  -0.1084   0.8701   0.0632
  -2.250   0.2168   0.01723   0.00774  -0.1083   0.8632   0.0785
  -2.000   0.2450   0.01657   0.00725  -0.1084   0.8567   0.1176
  -1.750   0.2726   0.01572   0.00696  -0.1087   0.8509   0.2602
  -1.500   0.2979   0.01504   0.00693  -0.1084   0.8434   0.4545
  -1.250   0.3218   0.01437   0.00686  -0.1069   0.8382   0.6496
  -1.000   0.3386   0.01381   0.00682  -0.1034   0.8297   0.8637
  -0.750   0.3746   0.01363   0.00647  -0.1046   0.8240   1.0000
  -0.500   0.4014   0.01374   0.00640  -0.1044   0.8154   1.0000
  -0.250   0.4303   0.01376   0.00622  -0.1044   0.8093   1.0000
   0.000   0.4570   0.01389   0.00621  -0.1042   0.8004   1.0000
   0.250   0.4857   0.01390   0.00607  -0.1040   0.7942   1.0000
   0.500   0.5122   0.01404   0.00611  -0.1038   0.7849   1.0000
   0.750   0.5406   0.01406   0.00601  -0.1036   0.7782   1.0000
   1.000   0.5671   0.01420   0.00608  -0.1033   0.7687   1.0000
   1.250   0.5946   0.01427   0.00608  -0.1031   0.7606   1.0000
   1.500   0.6220   0.01435   0.00609  -0.1028   0.7518   1.0000
   1.750   0.6488   0.01447   0.00616  -0.1025   0.7422   1.0000
   2.000   0.6767   0.01450   0.00612  -0.1022   0.7342   1.0000
   2.250   0.7031   0.01463   0.00626  -0.1019   0.7234   1.0000
   2.500   0.7299   0.01475   0.00635  -0.1016   0.7131   1.0000
   2.750   0.7573   0.01481   0.00638  -0.1012   0.7035   1.0000
   3.000   0.7840   0.01492   0.00650  -0.1009   0.6924   1.0000
   3.250   0.8104   0.01505   0.00665  -0.1005   0.6804   1.0000
   3.500   0.8369   0.01518   0.00678  -0.1000   0.6683   1.0000
   3.750   0.8635   0.01530   0.00691  -0.0996   0.6558   1.0000
   4.000   0.8899   0.01543   0.00707  -0.0992   0.6428   1.0000
   4.250   0.9161   0.01558   0.00723  -0.0987   0.6289   1.0000
   4.500   0.9421   0.01574   0.00742  -0.0982   0.6142   1.0000
   4.750   0.9678   0.01593   0.00763  -0.0976   0.5985   1.0000
   5.000   0.9932   0.01614   0.00790  -0.0970   0.5819   1.0000
   5.250   1.0184   0.01637   0.00815  -0.0964   0.5644   1.0000
   5.500   1.0432   0.01662   0.00841  -0.0957   0.5459   1.0000
   5.750   1.0674   0.01692   0.00873  -0.0949   0.5257   1.0000
   6.000   1.0911   0.01724   0.00910  -0.0941   0.5034   1.0000
   6.250   1.1140   0.01762   0.00949  -0.0931   0.4786   1.0000
   6.500   1.1359   0.01805   0.00990  -0.0921   0.4508   1.0000
   6.750   1.1566   0.01856   0.01038  -0.0908   0.4187   1.0000
   7.000   1.1758   0.01919   0.01090  -0.0894   0.3830   1.0000
   7.250   1.1938   0.01991   0.01152  -0.0880   0.3439   1.0000
   7.500   1.2102   0.02078   0.01224  -0.0864   0.3033   1.0000
   7.750   1.2248   0.02179   0.01308  -0.0846   0.2613   1.0000
   8.000   1.2378   0.02294   0.01406  -0.0828   0.2184   1.0000
   8.250   1.2494   0.02422   0.01513  -0.0808   0.1775   1.0000
   8.500   1.2596   0.02562   0.01632  -0.0788   0.1407   1.0000
   8.750   1.2690   0.02705   0.01761  -0.0766   0.1101   1.0000
   9.000   1.2760   0.02857   0.01900  -0.0742   0.0884   1.0000
   9.250   1.2821   0.03007   0.02047  -0.0716   0.0741   1.0000
   9.500   1.2871   0.03172   0.02213  -0.0691   0.0642   1.0000
   9.750   1.2935   0.03330   0.02381  -0.0668   0.0563   1.0000
  10.000   1.2969   0.03516   0.02570  -0.0646   0.0510   1.0000
  10.250   1.3019   0.03695   0.02764  -0.0625   0.0468   1.0000
  10.500   1.3044   0.03900   0.02975  -0.0606   0.0437   1.0000
  10.750   1.3072   0.04112   0.03198  -0.0587   0.0409   1.0000
  11.000   1.3122   0.04310   0.03412  -0.0571   0.0379   1.0000
  11.250   1.3157   0.04526   0.03640  -0.0556   0.0357   1.0000
  11.500   1.3174   0.04768   0.03889  -0.0541   0.0342   1.0000
  11.750   1.3208   0.05009   0.04140  -0.0525   0.0328   1.0000
  12.000   1.3266   0.05233   0.04386  -0.0512   0.0312   1.0000
  12.250   1.3310   0.05471   0.04642  -0.0501   0.0295   1.0000
  12.500   1.3339   0.05722   0.04906  -0.0491   0.0281   1.0000
  12.750   1.3359   0.05986   0.05181  -0.0482   0.0270   1.0000
  13.000   1.3385   0.06265   0.05467  -0.0472   0.0262   1.0000
  13.250   1.3413   0.06567   0.05785  -0.0461   0.0255   1.0000
  13.500   1.3416   0.06895   0.06142  -0.0454   0.0249   1.0000
  13.750   1.3388   0.07261   0.06539  -0.0449   0.0244   1.0000
  14.000   1.3333   0.07663   0.06968  -0.0448   0.0238   1.0000
  14.250   1.3253   0.08097   0.07429  -0.0452   0.0233   1.0000
  14.500   1.3155   0.08566   0.07923  -0.0459   0.0228   1.0000
  14.750   1.3041   0.09077   0.08458  -0.0472   0.0224   1.0000
  15.000   1.2913   0.09632   0.09037  -0.0491   0.0221   1.0000
  15.250   1.2772   0.10240   0.09668  -0.0516   0.0219   1.0000
  15.500   1.2614   0.10916   0.10366  -0.0548   0.0217   1.0000
  15.750   1.2434   0.11679   0.11152  -0.0589   0.0217   1.0000
  16.000   1.2222   0.12572   0.12070  -0.0642   0.0218   1.0000
  16.250   1.1948   0.13711   0.13233  -0.0716   0.0222   1.0000
  16.500   1.1569   0.15310   0.14853  -0.0824   0.0233   1.0000
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