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WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il)
Reynolds number: 50,000
Max Cl/Cd: 26.6 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-wb13535sm-il-50000.txt
Download as CSV file: xf-wb13535sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WB-135/35  13.5%  smoothed                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3095   0.11238   0.10564  -0.0342   1.0000   0.2451
  -9.500  -0.3253   0.11078   0.10417  -0.0345   1.0000   0.2475
  -9.250  -0.3332   0.10814   0.10165  -0.0344   1.0000   0.2478
  -9.000  -0.3338   0.10461   0.09820  -0.0338   1.0000   0.2473
  -8.500  -0.4981   0.07848   0.07275  -0.0492   1.0000   0.1178
  -8.250  -0.5144   0.07541   0.06977  -0.0474   1.0000   0.1170
  -8.000  -0.5359   0.07179   0.06622  -0.0461   1.0000   0.1160
  -7.750  -0.5569   0.06786   0.06229  -0.0451   1.0000   0.1145
  -7.500  -0.5809   0.06268   0.05701  -0.0450   1.0000   0.1125
  -7.250  -0.6012   0.05671   0.05077  -0.0454   1.0000   0.1108
  -7.000  -0.6108   0.05136   0.04500  -0.0455   1.0000   0.1104
  -6.750  -0.6102   0.04727   0.04047  -0.0448   1.0000   0.1128
  -6.500  -0.6053   0.04318   0.03573  -0.0442   1.0000   0.1159
  -6.250  -0.5938   0.04066   0.03295  -0.0430   1.0000   0.1210
  -6.000  -0.5798   0.03852   0.03054  -0.0417   1.0000   0.1274
  -5.750  -0.5648   0.03676   0.02859  -0.0404   1.0000   0.1369
  -5.500  -0.5493   0.03553   0.02727  -0.0389   1.0000   0.1523
  -5.250  -0.5332   0.03406   0.02560  -0.0374   1.0000   0.1754
  -5.000  -0.5192   0.03385   0.02564  -0.0350   1.0000   0.2200
  -4.750  -0.5068   0.03530   0.02753  -0.0315   1.0000   0.2716
  -4.500  -0.4931   0.03604   0.02818  -0.0290   1.0000   0.3087
  -4.250  -0.4808   0.03756   0.02992  -0.0256   1.0000   0.3405
  -4.000  -0.4685   0.03867   0.03117  -0.0222   1.0000   0.3686
  -3.750  -0.4527   0.03818   0.03049  -0.0207   1.0000   0.3870
  -3.500  -0.4354   0.03747   0.02957  -0.0197   1.0000   0.4004
  -3.250  -0.4185   0.03690   0.02888  -0.0185   1.0000   0.4120
  -3.000  -0.4003   0.03616   0.02794  -0.0179   1.0000   0.4232
  -2.750  -0.3810   0.03541   0.02692  -0.0177   1.0000   0.4349
  -2.500  -0.3620   0.03488   0.02613  -0.0173   1.0000   0.4473
  -2.250  -0.3441   0.03446   0.02564  -0.0164   1.0000   0.4580
  -2.000  -0.3250   0.03405   0.02506  -0.0159   1.0000   0.4700
  -1.750  -0.3057   0.03374   0.02461  -0.0155   1.0000   0.4842
  -1.500  -0.2860   0.03349   0.02421  -0.0152   1.0000   0.4986
  -1.250  -0.2673   0.03332   0.02392  -0.0147   1.0000   0.5140
  -1.000  -0.2492   0.03321   0.02374  -0.0140   1.0000   0.5311
  -0.750  -0.2310   0.03315   0.02362  -0.0133   1.0000   0.5502
  -0.500  -0.1933   0.03378   0.02413  -0.0163   0.9925   0.5775
  -0.250  -0.1390   0.03476   0.02501  -0.0222   0.9742   0.6162
   0.000  -0.0834   0.03563   0.02590  -0.0280   0.9561   0.6625
   0.250  -0.0409   0.03579   0.02626  -0.0312   0.9389   0.7132
   0.500   0.0084   0.03563   0.02665  -0.0353   0.9216   0.8053
   0.750   0.1055   0.03641   0.02727  -0.0511   0.8993   1.0000
   1.000   0.1545   0.03742   0.02787  -0.0561   0.8823   1.0000
   1.250   0.1988   0.03831   0.02848  -0.0597   0.8656   1.0000
   1.500   0.2299   0.03900   0.02899  -0.0610   0.8481   1.0000
   1.750   0.2627   0.03970   0.02955  -0.0623   0.8303   1.0000
   2.000   0.2976   0.04039   0.03011  -0.0638   0.8125   1.0000
   2.250   0.3358   0.04098   0.03061  -0.0656   0.7948   1.0000
   2.500   0.3765   0.04146   0.03102  -0.0675   0.7775   1.0000
   2.750   0.4193   0.04179   0.03131  -0.0693   0.7607   1.0000
   3.000   0.4390   0.04250   0.03197  -0.0683   0.7400   1.0000
   3.250   0.4711   0.04292   0.03237  -0.0687   0.7214   1.0000
   3.500   0.5066   0.04317   0.03261  -0.0693   0.7041   1.0000
   3.750   0.5428   0.04331   0.03276  -0.0698   0.6876   1.0000
   4.000   0.5770   0.04345   0.03291  -0.0700   0.6718   1.0000
   4.250   0.6085   0.04364   0.03311  -0.0698   0.6564   1.0000
   4.500   0.6371   0.04393   0.03345  -0.0693   0.6414   1.0000
   4.750   0.6604   0.04454   0.03407  -0.0685   0.6268   1.0000
   5.000   0.6811   0.04529   0.03484  -0.0674   0.6124   1.0000
   5.250   0.6959   0.04649   0.03608  -0.0660   0.5984   1.0000
   5.500   0.7063   0.04812   0.03773  -0.0645   0.5851   1.0000
   5.750   0.7787   0.04538   0.03513  -0.0667   0.5796   1.0000
   6.000   0.7741   0.04791   0.03768  -0.0640   0.5658   1.0000
   6.250   0.7619   0.05145   0.04122  -0.0617   0.5522   1.0000
   6.750   0.7604   0.05722   0.04704  -0.0591   0.5304   1.0000
   7.000   0.7821   0.05828   0.04818  -0.0584   0.5218   1.0000
   7.250   0.7542   0.06385   0.05373  -0.0571   0.5113   1.0000
   7.500   0.8179   0.06114   0.05122  -0.0570   0.5051   1.0000
   7.750   0.7584   0.06994   0.05990  -0.0560   0.4952   1.0000
   8.000   0.7754   0.07176   0.06182  -0.0556   0.4880   1.0000
   8.250   0.7524   0.07729   0.06736  -0.0554   0.4815   1.0000
   8.500   0.7880   0.07770   0.06791  -0.0550   0.4749   1.0000
   8.750   0.7504   0.08475   0.07492  -0.0554   0.4710   1.0000
   9.000   0.7410   0.08928   0.07949  -0.0557   0.4673   1.0000
   9.250   0.7340   0.09390   0.08416  -0.0563   0.4666   1.0000
   9.500   0.7234   0.09917   0.08947  -0.0574   0.4706   1.0000
   9.750   0.7262   0.10356   0.09394  -0.0585   0.4736   1.0000
  11.000   1.2663   0.05141   0.04393  -0.0405   0.3427   1.0000
  11.250   1.2242   0.05700   0.04967  -0.0360   0.3425   1.0000
  11.500   1.2694   0.04773   0.04013  -0.0305   0.2908   1.0000
  11.750   1.2546   0.04884   0.04134  -0.0264   0.2747   1.0000
  12.000   1.2373   0.05065   0.04326  -0.0230   0.2590   1.0000
  12.250   1.2150   0.05317   0.04588  -0.0203   0.2407   1.0000
  12.500   1.1937   0.05634   0.04914  -0.0186   0.2204   1.0000
  12.750   1.1719   0.06033   0.05320  -0.0178   0.1961   1.0000
  13.000   1.1515   0.06458   0.05723  -0.0173   0.1647   1.0000
  13.250   1.1342   0.06907   0.06136  -0.0171   0.1415   1.0000
  13.500   1.1184   0.07395   0.06596  -0.0173   0.1249   1.0000
  13.750   1.1084   0.07829   0.07008  -0.0174   0.1143   1.0000
  14.000   1.1019   0.08248   0.07425  -0.0176   0.1053   1.0000
  14.250   1.1007   0.08596   0.07767  -0.0174   0.0992   1.0000
  14.500   1.1007   0.08930   0.08096  -0.0172   0.0927   1.0000
  14.750   1.1046   0.09226   0.08394  -0.0168   0.0880   1.0000
  15.000   1.1063   0.09581   0.08769  -0.0169   0.0841   1.0000
  15.250   1.1221   0.09724   0.08907  -0.0152   0.0802   1.0000
  15.500   1.1340   0.09995   0.09192  -0.0142   0.0778   1.0000
  15.750   1.1265   0.10536   0.09763  -0.0157   0.0774   1.0000
  16.000   1.1123   0.11195   0.10450  -0.0182   0.0773   1.0000
  16.250   1.0951   0.11932   0.11210  -0.0216   0.0776   1.0000
  16.500   1.0743   0.12776   0.12074  -0.0259   0.0782   1.0000
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