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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 50,000
Max Cl/Cd: 39.28 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae51-il-50000.txt
Download as CSV file: xf-dae51-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3588   0.10689   0.10045  -0.0304   1.0000   0.2001
  -7.750  -0.3303   0.10066   0.09418  -0.0285   1.0000   0.2107
  -7.500  -0.3580   0.10147   0.09521  -0.0271   1.0000   0.2147
  -7.250  -0.3392   0.09663   0.09038  -0.0253   1.0000   0.2236
  -7.000  -0.3645   0.09688   0.09082  -0.0223   1.0000   0.2287
  -6.750  -0.3691   0.09442   0.08845  -0.0199   1.0000   0.2340
  -6.500  -0.3781   0.09307   0.08720  -0.0175   1.0000   0.2428
  -6.250  -0.3886   0.09120   0.08544  -0.0157   1.0000   0.2487
  -6.000  -0.3983   0.08993   0.08426  -0.0143   1.0000   0.2592
  -5.750  -0.3962   0.08700   0.08139  -0.0112   1.0000   0.2679
  -5.500  -0.4059   0.08523   0.07972  -0.0108   1.0000   0.2788
  -5.250  -0.4109   0.08331   0.07786  -0.0103   1.0000   0.2928
  -5.000  -0.4105   0.08085   0.07546  -0.0079   1.0000   0.3088
  -4.750  -0.4083   0.07837   0.07304  -0.0047   1.0000   0.3268
  -4.500  -0.4116   0.07679   0.07149  -0.0058   1.0000   0.3526
  -4.250  -0.4071   0.07382   0.06859   0.0000   1.0000   0.3724
  -4.000  -0.4064   0.07164   0.06646   0.0024   1.0000   0.4010
  -3.750  -0.4046   0.06938   0.06426   0.0059   1.0000   0.4315
  -3.500  -0.4023   0.06707   0.06201   0.0106   1.0000   0.4639
  -3.000  -0.1783   0.04128   0.03299  -0.0648   1.0000   0.1395
  -2.750  -0.1469   0.03847   0.02982  -0.0668   1.0000   0.1375
  -2.500  -0.1140   0.03606   0.02690  -0.0687   1.0000   0.1366
  -2.250  -0.0816   0.03400   0.02432  -0.0701   1.0000   0.1354
  -2.000  -0.0505   0.03248   0.02229  -0.0711   1.0000   0.1383
  -1.750  -0.0233   0.03131   0.02098  -0.0716   1.0000   0.1480
  -1.500   0.0054   0.03031   0.01968  -0.0720   1.0000   0.1578
  -1.250   0.0324   0.02958   0.01892  -0.0723   1.0000   0.1794
  -1.000   0.0632   0.02882   0.01819  -0.0730   1.0000   0.2191
  -0.750   0.0899   0.02481   0.01737  -0.0706   1.0000   0.9118
  -0.500   0.1083   0.02536   0.01708  -0.0699   1.0000   1.0000
  -0.250   0.1308   0.02611   0.01736  -0.0702   1.0000   1.0000
   0.000   0.1526   0.02691   0.01781  -0.0706   1.0000   1.0000
   0.250   0.1871   0.02794   0.01849  -0.0734   0.9951   1.0000
   0.500   0.2348   0.02917   0.01937  -0.0785   0.9842   1.0000
   0.750   0.2764   0.03030   0.02023  -0.0825   0.9725   1.0000
   1.000   0.3143   0.03138   0.02112  -0.0858   0.9604   1.0000
   1.250   0.3510   0.03247   0.02204  -0.0887   0.9481   1.0000
   1.500   0.3875   0.03357   0.02300  -0.0916   0.9357   1.0000
   1.750   0.4244   0.03467   0.02399  -0.0944   0.9232   1.0000
   2.000   0.4618   0.03576   0.02500  -0.0971   0.9106   1.0000
   2.250   0.5010   0.03682   0.02600  -0.1000   0.8979   1.0000
   2.500   0.5299   0.03782   0.02698  -0.1012   0.8841   1.0000
   2.750   0.5586   0.03885   0.02799  -0.1023   0.8701   1.0000
   3.000   0.5875   0.03987   0.02902  -0.1033   0.8560   1.0000
   3.250   0.6165   0.04087   0.03006  -0.1042   0.8417   1.0000
   3.500   0.6453   0.04186   0.03109  -0.1050   0.8272   1.0000
   3.750   0.6741   0.04282   0.03210  -0.1057   0.8125   1.0000
   4.000   0.7032   0.04373   0.03307  -0.1063   0.7975   1.0000
   4.250   0.7324   0.04459   0.03404  -0.1068   0.7823   1.0000
   4.500   0.7621   0.04537   0.03492  -0.1072   0.7670   1.0000
   4.750   0.7928   0.04604   0.03570  -0.1075   0.7516   1.0000
   5.000   0.8250   0.04652   0.03636  -0.1077   0.7360   1.0000
   5.250   0.8592   0.04678   0.03677  -0.1078   0.7204   1.0000
   5.500   0.8773   0.04776   0.03787  -0.1065   0.7024   1.0000
   5.750   0.9001   0.04844   0.03870  -0.1055   0.6844   1.0000
   6.000   0.9319   0.04842   0.03892  -0.1047   0.6671   1.0000
   6.250   0.9712   0.04761   0.03834  -0.1040   0.6504   1.0000
   6.500   1.0165   0.04583   0.03683  -0.1028   0.6343   1.0000
   6.750   1.0666   0.04316   0.03449  -0.1012   0.6180   1.0000
   7.000   1.0869   0.04311   0.03465  -0.0986   0.5951   1.0000
   7.250   1.1511   0.03837   0.03024  -0.0967   0.5745   1.0000
   7.500   1.1919   0.03575   0.02780  -0.0940   0.5454   1.0000
   7.750   1.2215   0.03412   0.02627  -0.0908   0.5096   1.0000
   8.000   1.2486   0.03262   0.02475  -0.0874   0.4666   1.0000
   8.250   1.2649   0.03220   0.02420  -0.0835   0.4175   1.0000
   8.500   1.2735   0.03264   0.02435  -0.0792   0.3622   1.0000
   8.750   1.2752   0.03400   0.02527  -0.0747   0.3036   1.0000
   9.000   1.2755   0.03615   0.02687  -0.0706   0.2495   1.0000
   9.250   1.2795   0.03868   0.02898  -0.0673   0.2061   1.0000
   9.500   1.2897   0.04129   0.03137  -0.0648   0.1738   1.0000
   9.750   1.3090   0.04411   0.03405  -0.0634   0.1498   1.0000
  10.000   1.3313   0.04717   0.03717  -0.0624   0.1334   1.0000
  10.250   1.3518   0.05045   0.04060  -0.0614   0.1220   1.0000
  10.500   1.3738   0.05393   0.04408  -0.0608   0.1127   1.0000
  10.750   1.3792   0.05772   0.04848  -0.0583   0.1092   1.0000
  11.000   1.3844   0.06147   0.05262  -0.0561   0.1056   1.0000
  11.250   1.4017   0.06573   0.05688  -0.0556   0.1003   1.0000
  11.500   1.3886   0.06948   0.06116  -0.0522   0.0993   1.0000
  11.750   1.3722   0.07336   0.06544  -0.0489   0.0988   1.0000
  12.000   1.3526   0.07737   0.06977  -0.0459   0.0986   1.0000
  12.250   1.3311   0.08178   0.07446  -0.0438   0.0988   1.0000
  12.500   1.3083   0.08666   0.07959  -0.0425   0.0992   1.0000
  12.750   1.2850   0.09205   0.08519  -0.0422   0.0997   1.0000
  13.000   1.2622   0.09798   0.09129  -0.0428   0.1002   1.0000
  13.250   1.2417   0.10441   0.09782  -0.0441   0.1007   1.0000
  13.500   1.1330   0.12405   0.11777  -0.0587   0.1146   1.0000
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