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SM701 (sm701-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SM701 (sm701-il)
Reynolds number: 50,000
Max Cl/Cd: 30.52 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sm701-il-50000-n5.txt
Download as CSV file: xf-sm701-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SM701                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3818   0.11072   0.10371  -0.0515   1.0000   0.0580
 -10.500  -0.3921   0.10670   0.09978  -0.0517   1.0000   0.0574
 -10.250  -0.4052   0.10240   0.09558  -0.0520   1.0000   0.0567
 -10.000  -0.4227   0.09740   0.09066  -0.0529   1.0000   0.0559
  -9.750  -0.4485   0.09161   0.08495  -0.0542   1.0000   0.0550
  -9.500  -0.4857   0.08587   0.07925  -0.0554   1.0000   0.0539
  -9.250  -0.5302   0.08113   0.07453  -0.0551   1.0000   0.0530
  -9.000  -0.5816   0.07773   0.07110  -0.0526   1.0000   0.0522
  -8.750  -0.6109   0.07135   0.06430  -0.0569   0.9907   0.0514
  -8.500  -0.6153   0.06629   0.05879  -0.0598   0.9830   0.0512
  -8.250  -0.6117   0.06240   0.05456  -0.0610   0.9757   0.0512
  -8.000  -0.5997   0.05877   0.05060  -0.0626   0.9702   0.0515
  -7.750  -0.5888   0.05592   0.04749  -0.0628   0.9639   0.0520
  -7.500  -0.5700   0.05354   0.04492  -0.0639   0.9592   0.0533
  -7.250  -0.5540   0.05123   0.04233  -0.0642   0.9538   0.0548
  -7.000  -0.5361   0.04885   0.03960  -0.0645   0.9484   0.0564
  -6.750  -0.5118   0.04642   0.03672  -0.0655   0.9444   0.0579
  -6.500  -0.4915   0.04441   0.03432  -0.0652   0.9397   0.0589
  -6.250  -0.4684   0.04266   0.03220  -0.0649   0.9350   0.0601
  -6.000  -0.4409   0.04116   0.03059  -0.0653   0.9313   0.0617
  -5.750  -0.4143   0.04012   0.02951  -0.0656   0.9276   0.0647
  -5.500  -0.3943   0.03923   0.02848  -0.0644   0.9224   0.0682
  -5.250  -0.3678   0.03839   0.02745  -0.0639   0.9183   0.0719
  -5.000  -0.3396   0.03754   0.02667  -0.0640   0.9150   0.0759
  -4.750  -0.3219   0.03689   0.02593  -0.0625   0.9094   0.0804
  -4.500  -0.2998   0.03612   0.02514  -0.0620   0.9045   0.0878
  -4.250  -0.2724   0.03526   0.02429  -0.0627   0.9007   0.1004
  -4.000  -0.2535   0.03432   0.02345  -0.0622   0.8951   0.1184
  -3.750  -0.2309   0.03301   0.02246  -0.0629   0.8900   0.1618
  -3.500  -0.2082   0.03069   0.02197  -0.0644   0.8862   0.3857
  -3.250  -0.1942   0.03155   0.02327  -0.0603   0.8801   0.5644
  -3.000  -0.1758   0.03240   0.02399  -0.0575   0.8739   0.6166
  -2.750  -0.1510   0.03325   0.02469  -0.0553   0.8693   0.6549
  -2.500  -0.1421   0.03395   0.02534  -0.0505   0.8620   0.6783
  -2.250  -0.1250   0.03462   0.02591  -0.0469   0.8561   0.7076
  -2.000  -0.1091   0.03522   0.02643  -0.0427   0.8507   0.7320
  -1.750  -0.0978   0.03551   0.02663  -0.0391   0.8429   0.7508
  -1.500  -0.0689   0.03552   0.02644  -0.0390   0.8380   0.7623
  -1.250  -0.0483   0.03549   0.02625  -0.0386   0.8305   0.7707
  -1.000  -0.0211   0.03542   0.02601  -0.0388   0.8241   0.7771
  -0.750   0.0136   0.03530   0.02571  -0.0403   0.8192   0.7834
  -0.500   0.0329   0.03534   0.02563  -0.0400   0.8100   0.7901
  -0.250   0.0672   0.03520   0.02534  -0.0411   0.8047   0.7952
   0.000   0.0865   0.03529   0.02534  -0.0405   0.7952   0.8013
   0.250   0.1228   0.03514   0.02505  -0.0424   0.7891   0.8070
   0.500   0.1431   0.03521   0.02506  -0.0416   0.7797   0.8123
   0.750   0.1778   0.03504   0.02479  -0.0429   0.7729   0.8182
   1.000   0.2010   0.03513   0.02481  -0.0429   0.7631   0.8241
   1.250   0.2354   0.03487   0.02448  -0.0438   0.7562   0.8295
   1.500   0.2571   0.03499   0.02456  -0.0435   0.7453   0.8363
   1.750   0.2945   0.03461   0.02412  -0.0448   0.7390   0.8421
   2.000   0.3136   0.03475   0.02425  -0.0438   0.7271   0.8488
   2.250   0.3548   0.03421   0.02366  -0.0456   0.7215   0.8555
   2.500   0.3712   0.03436   0.02383  -0.0441   0.7086   0.8631
   2.750   0.3962   0.03432   0.02378  -0.0439   0.6976   0.8714
   3.000   0.4306   0.03374   0.02321  -0.0443   0.6901   0.8789
   3.250   0.4506   0.03381   0.02330  -0.0434   0.6770   0.8885
   3.750   0.5106   0.03294   0.02249  -0.0432   0.6573   0.9094
   4.000   0.5327   0.03292   0.02252  -0.0426   0.6435   0.9228
   4.250   0.5602   0.03274   0.02241  -0.0427   0.6303   0.9379
   4.500   0.5966   0.03230   0.02202  -0.0441   0.6184   0.9564
   4.750   0.6388   0.03144   0.02119  -0.0461   0.6074   0.9931
   5.000   0.6670   0.03141   0.02119  -0.0468   0.5923   1.0000
   5.250   0.6969   0.03133   0.02110  -0.0476   0.5770   1.0000
   5.750   0.7607   0.03102   0.02077  -0.0492   0.5460   1.0000
   6.000   0.7941   0.03083   0.02053  -0.0501   0.5299   1.0000
   6.250   0.8277   0.03067   0.02032  -0.0509   0.5134   1.0000
   6.500   0.8605   0.03062   0.02019  -0.0516   0.4965   1.0000
   6.750   0.8919   0.03069   0.02016  -0.0522   0.4791   1.0000
   7.000   0.9212   0.03095   0.02034  -0.0526   0.4621   1.0000
   7.500   0.9729   0.03192   0.02113  -0.0527   0.4290   1.0000
   7.750   0.9955   0.03262   0.02180  -0.0525   0.4137   1.0000
   8.000   1.0167   0.03341   0.02256  -0.0521   0.3989   1.0000
   8.250   1.0372   0.03424   0.02338  -0.0517   0.3850   1.0000
   8.500   1.0585   0.03508   0.02420  -0.0514   0.3722   1.0000
   8.750   1.0820   0.03584   0.02493  -0.0513   0.3604   1.0000
   9.000   1.1036   0.03669   0.02578  -0.0510   0.3487   1.0000
   9.250   1.1200   0.03781   0.02697  -0.0502   0.3376   1.0000
   9.500   1.1427   0.03867   0.02784  -0.0500   0.3276   1.0000
   9.750   1.1610   0.03972   0.02894  -0.0495   0.3176   1.0000
  10.000   1.1772   0.04092   0.03022  -0.0488   0.3083   1.0000
  10.250   1.2004   0.04178   0.03108  -0.0486   0.2996   1.0000
  10.500   1.2107   0.04331   0.03279  -0.0475   0.2912   1.0000
  10.750   1.2339   0.04417   0.03363  -0.0473   0.2832   1.0000
  11.000   1.2402   0.04597   0.03562  -0.0460   0.2756   1.0000
  11.250   1.2593   0.04707   0.03677  -0.0455   0.2685   1.0000
  11.500   1.2673   0.04885   0.03873  -0.0444   0.2616   1.0000
  11.750   1.2766   0.05053   0.04053  -0.0434   0.2549   1.0000
  12.000   1.2947   0.05176   0.04181  -0.0430   0.2487   1.0000
  12.250   1.2899   0.05447   0.04478  -0.0414   0.2428   1.0000
  12.500   1.3059   0.05576   0.04612  -0.0409   0.2369   1.0000
  12.750   1.3066   0.05826   0.04882  -0.0398   0.2316   1.0000
  13.000   1.2961   0.06168   0.05249  -0.0386   0.2264   1.0000
  13.250   1.3127   0.06297   0.05383  -0.0382   0.2211   1.0000
  13.500   1.3050   0.06643   0.05749  -0.0374   0.2167   1.0000
  13.750   1.2706   0.07271   0.06409  -0.0369   0.2126   1.0000
  14.000   1.2627   0.07658   0.06811  -0.0369   0.2079   1.0000
  14.250   1.2894   0.07671   0.06824  -0.0365   0.2031   1.0000
  14.500   1.0551   0.11653   0.10848  -0.0519   0.1945   1.0000
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