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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 200,000
Max Cl/Cd: 84.63 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae51-il-200000-n5.txt
Download as CSV file: xf-dae51-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3707   0.11767   0.11402  -0.0268   1.0000   0.0254
 -10.000  -0.3681   0.11414   0.11052  -0.0298   1.0000   0.0256
  -9.750  -0.3639   0.11050   0.10691  -0.0324   1.0000   0.0257
  -9.500  -0.3599   0.10684   0.10328  -0.0350   1.0000   0.0258
  -9.250  -0.3557   0.10320   0.09968  -0.0376   1.0000   0.0259
  -9.000  -0.3456   0.09983   0.09633  -0.0348   1.0000   0.0270
  -8.750  -0.3378   0.09708   0.09361  -0.0353   1.0000   0.0277
  -8.500  -0.3328   0.09409   0.09065  -0.0366   1.0000   0.0282
  -8.250  -0.3306   0.09116   0.08778  -0.0377   1.0000   0.0285
  -8.000  -0.3222   0.08754   0.08419  -0.0409   0.9902   0.0288
  -7.750  -0.3087   0.08327   0.07992  -0.0459   0.9774   0.0291
  -7.500  -0.2954   0.07885   0.07550  -0.0513   0.9648   0.0293
  -7.250  -0.2822   0.06682   0.06339  -0.0678   0.9489   0.0197
  -7.000  -0.2649   0.06261   0.05914  -0.0729   0.9402   0.0193
  -6.750  -0.2466   0.05719   0.05364  -0.0798   0.9302   0.0189
  -6.500  -0.2266   0.05075   0.04705  -0.0873   0.9207   0.0184
  -6.250  -0.2045   0.04343   0.03944  -0.0943   0.9130   0.0180
  -6.000  -0.1825   0.03615   0.03170  -0.0993   0.9043   0.0177
  -5.750  -0.1586   0.03030   0.02524  -0.1022   0.8983   0.0178
  -5.500  -0.1334   0.02623   0.02055  -0.1036   0.8910   0.0189
  -5.250  -0.1071   0.02323   0.01692  -0.1042   0.8852   0.0196
  -5.000  -0.0804   0.02108   0.01428  -0.1045   0.8793   0.0198
  -4.750  -0.0536   0.01935   0.01218  -0.1045   0.8731   0.0201
  -4.500  -0.0269   0.01795   0.01057  -0.1045   0.8682   0.0207
  -4.250   0.0001   0.01700   0.00947  -0.1045   0.8615   0.0215
  -4.000   0.0272   0.01616   0.00849  -0.1043   0.8558   0.0225
  -3.750   0.0546   0.01546   0.00765  -0.1042   0.8501   0.0241
  -3.500   0.0821   0.01487   0.00694  -0.1040   0.8437   0.0262
  -3.250   0.1093   0.01419   0.00621  -0.1039   0.8386   0.0283
  -3.000   0.1370   0.01368   0.00566  -0.1039   0.8318   0.0306
  -2.750   0.1647   0.01325   0.00514  -0.1038   0.8259   0.0341
  -2.500   0.1926   0.01285   0.00470  -0.1038   0.8199   0.0401
  -2.250   0.2207   0.01246   0.00428  -0.1038   0.8133   0.0477
  -2.000   0.2487   0.01213   0.00394  -0.1038   0.8079   0.0654
  -1.750   0.2766   0.01175   0.00371  -0.1040   0.8006   0.1079
  -1.500   0.3043   0.01124   0.00353  -0.1042   0.7947   0.2099
  -1.250   0.3317   0.01076   0.00349  -0.1044   0.7874   0.3442
  -1.000   0.3585   0.01033   0.00344  -0.1043   0.7809   0.4787
  -0.750   0.3838   0.00992   0.00346  -0.1037   0.7737   0.6178
  -0.500   0.4054   0.00949   0.00345  -0.1018   0.7667   0.7657
  -0.250   0.4341   0.00907   0.00327  -0.1012   0.7594   1.0000
   0.000   0.4624   0.00912   0.00319  -0.1012   0.7517   1.0000
   0.250   0.4906   0.00918   0.00315  -0.1012   0.7436   1.0000
   0.500   0.5187   0.00924   0.00309  -0.1011   0.7358   1.0000
   0.750   0.5468   0.00932   0.00308  -0.1012   0.7268   1.0000
   1.000   0.5748   0.00939   0.00305  -0.1011   0.7185   1.0000
   1.250   0.6027   0.00947   0.00307  -0.1010   0.7088   1.0000
   1.500   0.6305   0.00955   0.00309  -0.1010   0.6992   1.0000
   1.750   0.6583   0.00964   0.00310  -0.1009   0.6896   1.0000
   2.000   0.6859   0.00974   0.00315  -0.1008   0.6787   1.0000
   2.250   0.7135   0.00985   0.00322  -0.1007   0.6675   1.0000
   2.500   0.7410   0.00996   0.00329  -0.1005   0.6560   1.0000
   2.750   0.7683   0.01009   0.00336  -0.1004   0.6439   1.0000
   3.000   0.7955   0.01023   0.00346  -0.1002   0.6312   1.0000
   3.250   0.8225   0.01038   0.00357  -0.1000   0.6178   1.0000
   3.500   0.8494   0.01054   0.00370  -0.0998   0.6036   1.0000
   3.750   0.8761   0.01072   0.00384  -0.0995   0.5889   1.0000
   4.000   0.9026   0.01092   0.00402  -0.0993   0.5736   1.0000
   4.250   0.9289   0.01113   0.00420  -0.0990   0.5574   1.0000
   4.500   0.9550   0.01136   0.00441  -0.0987   0.5402   1.0000
   4.750   0.9809   0.01161   0.00463  -0.0983   0.5221   1.0000
   5.000   1.0063   0.01189   0.00489  -0.0979   0.5028   1.0000
   5.250   1.0313   0.01220   0.00516  -0.0974   0.4815   1.0000
   5.500   1.0557   0.01255   0.00545  -0.0969   0.4577   1.0000
   5.750   1.0795   0.01294   0.00580  -0.0963   0.4303   1.0000
   6.000   1.1020   0.01342   0.00617  -0.0955   0.3982   1.0000
   6.250   1.1239   0.01396   0.00659  -0.0946   0.3625   1.0000
   6.500   1.1449   0.01459   0.00707  -0.0937   0.3265   1.0000
   6.750   1.1651   0.01529   0.00763  -0.0927   0.2881   1.0000
   7.000   1.1838   0.01611   0.00826  -0.0915   0.2465   1.0000
   7.250   1.2017   0.01701   0.00895  -0.0903   0.2055   1.0000
   7.500   1.2189   0.01795   0.00970  -0.0890   0.1675   1.0000
   7.750   1.2360   0.01889   0.01050  -0.0877   0.1341   1.0000
   8.000   1.2523   0.01987   0.01135  -0.0863   0.1055   1.0000
   8.250   1.2679   0.02088   0.01225  -0.0848   0.0817   1.0000
   8.500   1.2823   0.02194   0.01321  -0.0831   0.0637   1.0000
   8.750   1.2967   0.02295   0.01420  -0.0814   0.0518   1.0000
   9.000   1.3098   0.02397   0.01525  -0.0795   0.0435   1.0000
   9.250   1.3215   0.02495   0.01629  -0.0774   0.0379   1.0000
   9.500   1.3303   0.02618   0.01753  -0.0751   0.0335   1.0000
   9.750   1.3416   0.02725   0.01874  -0.0731   0.0306   1.0000
  10.000   1.3511   0.02849   0.02006  -0.0712   0.0281   1.0000
  10.250   1.3565   0.03008   0.02171  -0.0690   0.0259   1.0000
  10.500   1.3656   0.03143   0.02318  -0.0672   0.0242   1.0000
  10.750   1.3734   0.03292   0.02482  -0.0655   0.0227   1.0000
  11.000   1.3797   0.03458   0.02658  -0.0638   0.0216   1.0000
  11.250   1.3842   0.03645   0.02855  -0.0621   0.0206   1.0000
  11.500   1.3846   0.03875   0.03093  -0.0603   0.0197   1.0000
  11.750   1.3888   0.04080   0.03312  -0.0589   0.0190   1.0000
  12.000   1.3934   0.04284   0.03530  -0.0576   0.0181   1.0000
  12.250   1.3973   0.04499   0.03759  -0.0564   0.0173   1.0000
  12.500   1.4006   0.04725   0.03997  -0.0553   0.0166   1.0000
  12.750   1.4027   0.04968   0.04253  -0.0544   0.0160   1.0000
  13.000   1.4031   0.05234   0.04530  -0.0536   0.0155   1.0000
  13.250   1.4018   0.05527   0.04832  -0.0527   0.0151   1.0000
  13.500   1.3991   0.05841   0.05156  -0.0519   0.0148   1.0000
  13.750   1.3993   0.06133   0.05467  -0.0512   0.0145   1.0000
  14.000   1.3983   0.06445   0.05797  -0.0507   0.0142   1.0000
  14.250   1.3964   0.06778   0.06150  -0.0504   0.0139   1.0000
  14.500   1.3935   0.07134   0.06525  -0.0504   0.0135   1.0000
  14.750   1.3897   0.07514   0.06923  -0.0507   0.0132   1.0000
  15.000   1.3850   0.07916   0.07343  -0.0512   0.0129   1.0000
  15.250   1.3794   0.08345   0.07789  -0.0520   0.0126   1.0000
  15.500   1.3732   0.08796   0.08256  -0.0532   0.0123   1.0000
  15.750   1.3662   0.09272   0.08747  -0.0547   0.0121   1.0000
  16.000   1.3585   0.09771   0.09262  -0.0564   0.0119   1.0000
  16.250   1.3504   0.10291   0.09798  -0.0585   0.0117   1.0000
  16.500   1.3414   0.10844   0.10367  -0.0608   0.0116   1.0000
  16.750   1.3316   0.11426   0.10964  -0.0634   0.0115   1.0000
  17.000   1.3209   0.12045   0.11598  -0.0664   0.0114   1.0000
  17.250   1.3092   0.12705   0.12275  -0.0698   0.0113   1.0000
  17.500   1.2965   0.13415   0.13002  -0.0737   0.0113   1.0000
  17.750   1.2829   0.14180   0.13785  -0.0783   0.0112   1.0000
  18.000   1.2680   0.15021   0.14643  -0.0836   0.0112   1.0000
  18.250   1.2504   0.15989   0.15632  -0.0899   0.0112   1.0000
  18.500   1.2124   0.17724   0.17397  -0.1016   0.0115   1.0000
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