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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 500,000
Max Cl/Cd: 110.34 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae51-il-500000-n5.txt
Download as CSV file: xf-dae51-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3391   0.08699   0.08465  -0.0386   0.9285   0.0105
  -8.250  -0.3364   0.08323   0.08087  -0.0405   0.9152   0.0104
  -8.000  -0.3333   0.07932   0.07693  -0.0429   0.9033   0.0104
  -7.750  -0.3301   0.07519   0.07278  -0.0461   0.8923   0.0105
  -7.500  -0.3228   0.07008   0.06762  -0.0518   0.8828   0.0107
  -7.250  -0.3100   0.06388   0.06138  -0.0602   0.8737   0.0108
  -7.000  -0.2928   0.05683   0.05424  -0.0700   0.8660   0.0107
  -6.750  -0.2713   0.04730   0.04453  -0.0819   0.8583   0.0104
  -6.500  -0.2560   0.02269   0.01839  -0.0975   0.8517   0.0102
  -6.250  -0.2311   0.01866   0.01367  -0.0986   0.8458   0.0107
  -6.000  -0.2047   0.01678   0.01138  -0.0989   0.8403   0.0110
  -5.750  -0.1776   0.01552   0.00983  -0.0991   0.8350   0.0113
  -5.500  -0.1500   0.01459   0.00867  -0.0992   0.8293   0.0115
  -5.250  -0.1228   0.01356   0.00743  -0.0994   0.8242   0.0119
  -5.000  -0.0951   0.01297   0.00677  -0.0995   0.8187   0.0124
  -4.750  -0.0671   0.01257   0.00629  -0.0997   0.8130   0.0130
  -4.500  -0.0393   0.01208   0.00570  -0.0997   0.8079   0.0136
  -4.250  -0.0110   0.01153   0.00505  -0.0998   0.8021   0.0141
  -4.000   0.0172   0.01108   0.00449  -0.0999   0.7964   0.0147
  -3.750   0.0455   0.01071   0.00404  -0.1000   0.7911   0.0153
  -3.500   0.0739   0.01024   0.00353  -0.1002   0.7851   0.0164
  -3.250   0.1022   0.00998   0.00320  -0.1003   0.7795   0.0175
  -3.000   0.1309   0.00974   0.00292  -0.1004   0.7735   0.0190
  -2.750   0.1594   0.00951   0.00264  -0.1006   0.7673   0.0213
  -2.500   0.1880   0.00932   0.00242  -0.1007   0.7614   0.0244
  -2.250   0.2166   0.00912   0.00220  -0.1008   0.7547   0.0283
  -2.000   0.2452   0.00897   0.00202  -0.1009   0.7485   0.0356
  -1.750   0.2738   0.00879   0.00188  -0.1011   0.7414   0.0485
  -1.250   0.3310   0.00842   0.00166  -0.1015   0.7273   0.1142
  -0.750   0.3878   0.00785   0.00154  -0.1021   0.7120   0.2833
  -0.500   0.4161   0.00761   0.00152  -0.1023   0.7042   0.3779
  -0.250   0.4443   0.00738   0.00153  -0.1026   0.6954   0.4687
   0.000   0.4722   0.00712   0.00156  -0.1027   0.6867   0.5812
   0.250   0.4990   0.00686   0.00160  -0.1025   0.6773   0.6969
   0.500   0.5240   0.00660   0.00165  -0.1016   0.6675   0.8077
   0.750   0.5497   0.00629   0.00158  -0.1007   0.6573   1.0000
   1.000   0.5780   0.00639   0.00159  -0.1008   0.6464   1.0000
   1.250   0.6063   0.00648   0.00161  -0.1008   0.6345   1.0000
   1.500   0.6344   0.00659   0.00164  -0.1009   0.6222   1.0000
   1.750   0.6624   0.00670   0.00168  -0.1009   0.6095   1.0000
   2.000   0.6903   0.00683   0.00174  -0.1009   0.5962   1.0000
   2.250   0.7181   0.00697   0.00181  -0.1009   0.5827   1.0000
   2.500   0.7458   0.00712   0.00189  -0.1009   0.5688   1.0000
   2.750   0.7734   0.00728   0.00198  -0.1009   0.5545   1.0000
   3.000   0.8009   0.00744   0.00209  -0.1009   0.5396   1.0000
   3.250   0.8282   0.00762   0.00221  -0.1008   0.5241   1.0000
   3.500   0.8554   0.00781   0.00234  -0.1008   0.5078   1.0000
   3.750   0.8824   0.00801   0.00248  -0.1007   0.4907   1.0000
   4.000   0.9091   0.00824   0.00265  -0.1006   0.4729   1.0000
   4.250   0.9357   0.00848   0.00283  -0.1004   0.4536   1.0000
   4.500   0.9620   0.00875   0.00302  -0.1002   0.4315   1.0000
   4.750   0.9878   0.00906   0.00325  -0.1000   0.4073   1.0000
   5.000   1.0131   0.00942   0.00350  -0.0997   0.3792   1.0000
   5.250   1.0374   0.00989   0.00380  -0.0993   0.3425   1.0000
   5.500   1.0615   0.01037   0.00412  -0.0989   0.3091   1.0000
   5.750   1.0856   0.01085   0.00447  -0.0984   0.2779   1.0000
   6.000   1.1079   0.01150   0.00490  -0.0978   0.2347   1.0000
   6.250   1.1300   0.01218   0.00536  -0.0971   0.1946   1.0000
   6.500   1.1527   0.01276   0.00581  -0.0965   0.1647   1.0000
   6.750   1.1750   0.01337   0.00629  -0.0959   0.1369   1.0000
   7.000   1.1966   0.01402   0.00680  -0.0951   0.1092   1.0000
   7.250   1.2178   0.01469   0.00735  -0.0943   0.0859   1.0000
   7.500   1.2391   0.01533   0.00789  -0.0935   0.0672   1.0000
   7.750   1.2598   0.01599   0.00849  -0.0926   0.0521   1.0000
   8.000   1.2806   0.01661   0.00907  -0.0917   0.0413   1.0000
   8.250   1.3009   0.01725   0.00968  -0.0907   0.0334   1.0000
   8.500   1.3213   0.01784   0.01027  -0.0898   0.0278   1.0000
   8.750   1.3412   0.01845   0.01091  -0.0887   0.0240   1.0000
   9.000   1.3602   0.01909   0.01158  -0.0876   0.0212   1.0000
   9.250   1.3784   0.01977   0.01230  -0.0863   0.0190   1.0000
   9.500   1.3964   0.02041   0.01299  -0.0850   0.0175   1.0000
   9.750   1.4118   0.02113   0.01375  -0.0834   0.0160   1.0000
  10.000   1.4243   0.02197   0.01465  -0.0812   0.0147   1.0000
  10.250   1.4383   0.02273   0.01549  -0.0795   0.0139   1.0000
  10.500   1.4512   0.02358   0.01642  -0.0776   0.0132   1.0000
  10.750   1.4632   0.02452   0.01744  -0.0758   0.0125   1.0000
  11.000   1.4737   0.02561   0.01859  -0.0740   0.0118   1.0000
  11.250   1.4809   0.02699   0.02004  -0.0719   0.0111   1.0000
  11.500   1.4912   0.02816   0.02131  -0.0703   0.0108   1.0000
  11.750   1.5010   0.02941   0.02267  -0.0687   0.0103   1.0000
  12.000   1.5098   0.03077   0.02413  -0.0672   0.0098   1.0000
  12.250   1.5178   0.03224   0.02569  -0.0657   0.0094   1.0000
  12.500   1.5248   0.03384   0.02738  -0.0643   0.0090   1.0000
  12.750   1.5304   0.03562   0.02924  -0.0629   0.0087   1.0000
  13.000   1.5339   0.03765   0.03137  -0.0616   0.0084   1.0000
  13.250   1.5339   0.04008   0.03390  -0.0602   0.0082   1.0000
  13.500   1.5341   0.04257   0.03651  -0.0591   0.0080   1.0000
  13.750   1.5363   0.04494   0.03900  -0.0582   0.0079   1.0000
  14.000   1.5368   0.04752   0.04173  -0.0573   0.0077   1.0000
  14.250   1.5365   0.05030   0.04464  -0.0567   0.0075   1.0000
  14.500   1.5349   0.05329   0.04776  -0.0562   0.0074   1.0000
  14.750   1.5325   0.05648   0.05108  -0.0559   0.0072   1.0000
  15.000   1.5295   0.05989   0.05462  -0.0558   0.0071   1.0000
  15.250   1.5259   0.06350   0.05836  -0.0559   0.0069   1.0000
  15.500   1.5219   0.06728   0.06227  -0.0563   0.0068   1.0000
  15.750   1.5170   0.07129   0.06641  -0.0568   0.0067   1.0000
  16.000   1.5117   0.07549   0.07074  -0.0576   0.0065   1.0000
  16.250   1.5055   0.07997   0.07534  -0.0587   0.0064   1.0000
  16.500   1.4981   0.08469   0.08018  -0.0599   0.0063   1.0000
  16.750   1.4895   0.08972   0.08535  -0.0614   0.0062   1.0000
  17.000   1.4803   0.09499   0.09074  -0.0631   0.0062   1.0000
  17.250   1.4701   0.10054   0.09642  -0.0650   0.0061   1.0000
  17.500   1.4590   0.10633   0.10233  -0.0672   0.0060   1.0000
  17.750   1.4467   0.11244   0.10857  -0.0696   0.0060   1.0000
  18.000   1.4344   0.11871   0.11497  -0.0723   0.0059   1.0000
  18.250   1.4219   0.12516   0.12154  -0.0753   0.0058   1.0000
  18.500   1.4091   0.13175   0.12826  -0.0784   0.0058   1.0000
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