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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 50,000
Max Cl/Cd: 23.77 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du861372-il-50000-n5.txt
Download as CSV file: xf-du861372-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU 86-137/25 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6866   0.10343   0.09567  -0.0271   0.4042   0.0589
 -12.500  -0.7255   0.09374   0.08592  -0.0337   0.4045   0.0585
 -12.250  -0.7604   0.08671   0.07879  -0.0373   0.4047   0.0583
 -12.000  -0.7760   0.08188   0.07383  -0.0384   0.4051   0.0579
 -11.750  -0.7921   0.07748   0.06930  -0.0389   0.4055   0.0576
 -11.500  -0.8078   0.07336   0.06502  -0.0386   0.4061   0.0571
 -11.250  -0.8225   0.06953   0.06099  -0.0377   0.4065   0.0566
 -11.000  -0.8349   0.06606   0.05730  -0.0362   0.4071   0.0561
 -10.750  -0.8459   0.06275   0.05368  -0.0340   0.4076   0.0554
 -10.500  -0.8539   0.05958   0.05019  -0.0315   0.4081   0.0547
 -10.250  -0.8548   0.05632   0.04655  -0.0294   0.4086   0.0540
 -10.000  -0.8491   0.05336   0.04322  -0.0278   0.4090   0.0539
  -9.750  -0.8375   0.05064   0.04016  -0.0265   0.4096   0.0541
  -9.500  -0.8205   0.04796   0.03712  -0.0256   0.4099   0.0540
  -9.250  -0.7959   0.04531   0.03409  -0.0254   0.4105   0.0534
  -8.750  -0.7128   0.04073   0.02885  -0.0280   0.4114   0.0516
  -8.500  -0.6721   0.03934   0.02728  -0.0289   0.4124   0.0510
  -8.250  -0.6423   0.03823   0.02600  -0.0286   0.4140   0.0506
  -8.000  -0.6205   0.03711   0.02473  -0.0277   0.4156   0.0504
  -7.750  -0.6026   0.03599   0.02348  -0.0267   0.4176   0.0502
  -7.500  -0.5862   0.03491   0.02224  -0.0255   0.4198   0.0504
  -7.250  -0.5706   0.03386   0.02107  -0.0243   0.4215   0.0513
  -7.000  -0.5551   0.03287   0.01997  -0.0231   0.4229   0.0520
  -6.750  -0.5397   0.03191   0.01896  -0.0219   0.4244   0.0530
  -6.500  -0.5240   0.03105   0.01800  -0.0206   0.4259   0.0537
  -6.250  -0.5084   0.03022   0.01709  -0.0192   0.4313   0.0543
  -6.000  -0.4922   0.02940   0.01620  -0.0179   0.4444   0.0554
  -5.750  -0.4752   0.02862   0.01542  -0.0166   0.4580   0.0578
  -5.500  -0.4563   0.02802   0.01470  -0.0156   0.4642   0.0684
  -5.250  -0.4368   0.02753   0.01403  -0.0146   0.4646   0.0754
  -5.000  -0.4178   0.02693   0.01339  -0.0136   0.4721   0.0805
  -4.750  -0.4020   0.02601   0.01274  -0.0125   0.4843   0.0961
  -4.500  -0.3819   0.02536   0.01226  -0.0118   0.5059   0.1542
  -4.250  -0.3581   0.02487   0.01194  -0.0119   0.5480   0.1646
  -4.000  -0.3320   0.02443   0.01183  -0.0130   0.6410   0.1738
  -3.750  -0.3117   0.02405   0.01145  -0.0123   0.6539   0.1856
  -3.250  -0.2958   0.02176   0.01073  -0.0072   0.6606   0.4332
  -3.000  -0.2679   0.02189   0.01143  -0.0060   0.6646   0.5262
  -2.750  -0.2353   0.02237   0.01213  -0.0056   0.6677   0.5874
  -2.500  -0.2119   0.02245   0.01218  -0.0047   0.6683   0.6164
  -2.250  -0.1894   0.02254   0.01225  -0.0037   0.6683   0.6414
  -2.000  -0.1695   0.02258   0.01224  -0.0025   0.6671   0.6626
  -1.750  -0.1493   0.02258   0.01220  -0.0015   0.6654   0.6784
  -1.500  -0.1291   0.02255   0.01210  -0.0005   0.6630   0.6908
  -1.250  -0.1107   0.02245   0.01195   0.0006   0.6593   0.7030
  -1.000  -0.0895   0.02254   0.01201   0.0017   0.6549   0.7157
  -0.750  -0.0708   0.02268   0.01214   0.0032   0.6504   0.7335
  -0.500  -0.0496   0.02276   0.01221   0.0042   0.6447   0.7435
  -0.250  -0.0306   0.02274   0.01214   0.0054   0.6387   0.7526
   0.000  -0.0083   0.02280   0.01220   0.0062   0.6321   0.7597
   0.250   0.0122   0.02281   0.01219   0.0073   0.6231   0.7677
   0.500   0.0332   0.02285   0.01222   0.0084   0.6130   0.7762
   0.750   0.0528   0.02300   0.01237   0.0102   0.6028   0.7913
   1.000   0.0750   0.02331   0.01273   0.0119   0.5946   0.8098
   1.250   0.0973   0.02346   0.01292   0.0132   0.5890   0.8223
   1.500   0.1208   0.02353   0.01304   0.0140   0.5852   0.8305
   1.750   0.1418   0.02358   0.01313   0.0151   0.5809   0.8392
   2.000   0.1683   0.02377   0.01341   0.0158   0.5766   0.8534
   2.250   0.1948   0.02391   0.01361   0.0164   0.5710   0.8674
   2.500   0.2290   0.02408   0.01390   0.0158   0.5645   0.8848
   2.750   0.2872   0.02441   0.01437   0.0114   0.5571   0.9138
   3.000   0.3804   0.02440   0.01452  -0.0001   0.5442   0.9368
   3.250   0.4033   0.02424   0.01435   0.0006   0.5277   0.9416
   3.500   0.4292   0.02408   0.01416   0.0008   0.5093   0.9457
   3.750   0.4585   0.02396   0.01401   0.0003   0.4883   0.9494
   4.000   0.4828   0.02397   0.01393   0.0006   0.4657   0.9539
   4.250   0.5047   0.02408   0.01401   0.0012   0.4456   0.9584
   4.500   0.5323   0.02422   0.01418   0.0006   0.4262   0.9622
   4.750   0.5551   0.02453   0.01439   0.0010   0.4083   0.9667
   5.000   0.5749   0.02504   0.01469   0.0018   0.3889   0.9712
   5.250   0.5986   0.02561   0.01522   0.0017   0.3644   0.9753
   5.500   0.6174   0.02597   0.01567   0.0021   0.3074   0.9809
   5.750   0.6587   0.02896   0.01691   0.0003   0.2845   0.9795
   6.000   0.6969   0.03148   0.01968  -0.0018   0.2543   0.9809
   6.250   0.7121   0.03199   0.02095  -0.0009   0.2299   0.9864
   6.500   0.7188   0.03118   0.02123   0.0013   0.1903   0.9949
   6.750   0.7298   0.03122   0.02143   0.0027   0.1653   1.0000
   7.000   0.7236   0.03153   0.02169   0.0073   0.1541   1.0000
   7.250   0.7184   0.03218   0.02229   0.0117   0.1412   1.0000
   7.500   0.7175   0.03299   0.02306   0.0157   0.1263   1.0000
   7.750   0.7189   0.03379   0.02384   0.0194   0.1134   1.0000
   8.000   0.7195   0.03461   0.02464   0.0232   0.1048   1.0000
   8.250   0.7230   0.03541   0.02546   0.0266   0.0959   1.0000
   8.500   0.7279   0.03633   0.02636   0.0296   0.0884   1.0000
   8.750   0.7399   0.03745   0.02755   0.0317   0.0813   1.0000
   9.000   0.7534   0.03892   0.02891   0.0332   0.0759   1.0000
   9.250   0.7737   0.04047   0.03077   0.0341   0.0690   1.0000
   9.500   0.7886   0.04206   0.03242   0.0351   0.0644   1.0000
   9.750   0.8073   0.04441   0.03475   0.0356   0.0615   1.0000
  10.000   0.8217   0.04692   0.03772   0.0366   0.0592   1.0000
  10.250   0.8292   0.04948   0.04066   0.0380   0.0567   1.0000
  10.500   0.8314   0.05191   0.04337   0.0396   0.0544   1.0000
  10.750   0.8305   0.05429   0.04596   0.0413   0.0525   1.0000
  11.000   0.8283   0.05684   0.04868   0.0427   0.0511   1.0000
  11.250   0.8236   0.05975   0.05177   0.0438   0.0502   1.0000
  11.500   0.8151   0.06314   0.05536   0.0444   0.0496   1.0000
  11.750   0.8032   0.06697   0.05938   0.0446   0.0492   1.0000
  12.000   0.7854   0.07144   0.06406   0.0441   0.0493   1.0000
  12.250   0.7607   0.07700   0.06985   0.0423   0.0495   1.0000
  12.500   0.7193   0.08589   0.07898   0.0374   0.0505   1.0000
  12.750   0.6563   0.10354   0.09670   0.0253   0.0537   1.0000
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