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BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il)
Reynolds number: 500,000
Max Cl/Cd: 68.25 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b737a-il-500000-n5.txt
Download as CSV file: xf-b737a-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 737 ROOT 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
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -1.1900   0.08508   0.08016  -0.0070   1.0000   0.0284
 -17.250  -1.2183   0.07709   0.07204  -0.0110   1.0000   0.0285
 -17.000  -1.2483   0.06875   0.06353  -0.0153   1.0000   0.0285
 -16.750  -1.2745   0.06093   0.05554  -0.0195   1.0000   0.0286
 -16.500  -1.2941   0.05430   0.04874  -0.0230   1.0000   0.0287
 -16.250  -1.3074   0.04894   0.04324  -0.0258   1.0000   0.0289
 -16.000  -1.3152   0.04462   0.03879  -0.0277   1.0000   0.0291
 -15.750  -1.3188   0.04107   0.03513  -0.0290   1.0000   0.0294
 -15.500  -1.3189   0.03812   0.03207  -0.0298   1.0000   0.0297
 -15.250  -1.3162   0.03559   0.02944  -0.0303   1.0000   0.0300
 -15.000  -1.3136   0.03318   0.02695  -0.0305   1.0000   0.0304
 -14.750  -1.3087   0.03109   0.02479  -0.0305   1.0000   0.0308
 -14.500  -1.3013   0.02934   0.02297  -0.0303   1.0000   0.0312
 -14.250  -1.2921   0.02785   0.02142  -0.0298   1.0000   0.0317
 -14.000  -1.2814   0.02656   0.02007  -0.0291   1.0000   0.0323
 -13.750  -1.2698   0.02546   0.01890  -0.0282   1.0000   0.0329
 -13.500  -1.2568   0.02454   0.01792  -0.0270   1.0000   0.0335
 -13.250  -1.2447   0.02362   0.01695  -0.0255   1.0000   0.0341
 -13.000  -1.2308   0.02280   0.01610  -0.0240   1.0000   0.0348
 -12.750  -1.2135   0.02207   0.01533  -0.0228   1.0000   0.0355
 -12.500  -1.1947   0.02142   0.01464  -0.0217   1.0000   0.0363
 -12.250  -1.1747   0.02083   0.01401  -0.0207   1.0000   0.0371
 -12.000  -1.1548   0.02021   0.01336  -0.0197   1.0000   0.0380
 -11.750  -1.1344   0.01959   0.01273  -0.0187   1.0000   0.0389
 -11.500  -1.1129   0.01906   0.01217  -0.0178   1.0000   0.0400
 -11.250  -1.0905   0.01859   0.01166  -0.0169   1.0000   0.0411
 -11.000  -1.0685   0.01807   0.01112  -0.0160   1.0000   0.0422
 -10.750  -1.0462   0.01756   0.01059  -0.0150   1.0000   0.0436
 -10.500  -1.0233   0.01712   0.01012  -0.0142   1.0000   0.0452
 -10.250  -1.0009   0.01661   0.00960  -0.0132   1.0000   0.0470
 -10.000  -0.9784   0.01612   0.00910  -0.0122   1.0000   0.0494
  -9.750  -0.9570   0.01552   0.00850  -0.0111   1.0000   0.0533
  -9.500  -0.9344   0.01505   0.00829  -0.0102   1.0000   0.0845
  -9.250  -0.9085   0.01494   0.00815  -0.0095   1.0000   0.0895
  -9.000  -0.8833   0.01479   0.00801  -0.0087   1.0000   0.0923
  -8.750  -0.8581   0.01465   0.00786  -0.0079   1.0000   0.0946
  -8.500  -0.8293   0.01453   0.00771  -0.0078   0.9978   0.0963
  -8.250  -0.7939   0.01423   0.00743  -0.0093   0.9860   0.0979
  -8.000  -0.7566   0.01396   0.00718  -0.0110   0.9609   0.0995
  -7.750  -0.7119   0.01373   0.00690  -0.0142   0.9132   0.1011
  -7.500  -0.6804   0.01361   0.00664  -0.0144   0.8677   0.1022
  -7.000  -0.6280   0.01351   0.00627  -0.0130   0.8133   0.1037
  -6.750  -0.6022   0.01334   0.00601  -0.0123   0.7913   0.1045
  -6.500  -0.5763   0.01312   0.00574  -0.0117   0.7721   0.1055
  -6.250  -0.5496   0.01292   0.00551  -0.0112   0.7561   0.1062
  -6.000  -0.5226   0.01275   0.00529  -0.0107   0.7428   0.1069
  -5.750  -0.4955   0.01259   0.00509  -0.0103   0.7292   0.1075
  -5.500  -0.4681   0.01243   0.00490  -0.0099   0.7157   0.1081
  -5.250  -0.4408   0.01230   0.00471  -0.0094   0.6989   0.1088
  -5.000  -0.4136   0.01218   0.00453  -0.0090   0.6801   0.1096
  -4.750  -0.3862   0.01207   0.00436  -0.0086   0.6603   0.1104
  -4.500  -0.3587   0.01198   0.00419  -0.0081   0.6378   0.1110
  -4.250  -0.3313   0.01190   0.00403  -0.0077   0.6131   0.1115
  -4.000  -0.3040   0.01182   0.00388  -0.0073   0.5877   0.1116
  -3.750  -0.2768   0.01175   0.00372  -0.0069   0.5564   0.1120
  -3.500  -0.2500   0.01175   0.00357  -0.0064   0.5129   0.1123
  -3.250  -0.2242   0.01189   0.00345  -0.0058   0.4366   0.1127
  -3.000  -0.1984   0.01211   0.00338  -0.0053   0.3568   0.1132
  -2.750  -0.1716   0.01222   0.00332  -0.0049   0.3104   0.1137
  -2.500  -0.1443   0.01226   0.00327  -0.0046   0.2845   0.1143
  -2.250  -0.1166   0.01227   0.00322  -0.0043   0.2663   0.1149
  -2.000  -0.0888   0.01228   0.00317  -0.0040   0.2518   0.1157
  -1.750  -0.0610   0.01230   0.00313  -0.0037   0.2390   0.1166
  -1.500  -0.0329   0.01229   0.00310  -0.0035   0.2300   0.1176
  -1.250  -0.0050   0.01231   0.00308  -0.0032   0.2217   0.1189
  -1.000   0.0231   0.01229   0.00306  -0.0029   0.2158   0.1209
  -0.750   0.0509   0.01226   0.00303  -0.0027   0.2097   0.1249
  -0.500   0.0776   0.01209   0.00299  -0.0023   0.2037   0.1574
  -0.250   0.1054   0.01202   0.00303  -0.0021   0.1994   0.1896
   0.000   0.1335   0.01203   0.00307  -0.0019   0.1952   0.1986
   0.250   0.1616   0.01208   0.00311  -0.0016   0.1904   0.2049
   0.500   0.1895   0.01212   0.00317  -0.0014   0.1854   0.2119
   0.750   0.2178   0.01215   0.00321  -0.0012   0.1810   0.2182
   1.000   0.2458   0.01219   0.00327  -0.0010   0.1767   0.2244
   1.250   0.2737   0.01224   0.00333  -0.0008   0.1730   0.2332
   1.500   0.3018   0.01230   0.00341  -0.0005   0.1700   0.2400
   1.750   0.3298   0.01232   0.00348  -0.0004   0.1674   0.2494
   2.000   0.3578   0.01236   0.00357  -0.0001   0.1645   0.2601
   2.500   0.4129   0.01241   0.00374   0.0003   0.1585   0.3033
   2.750   0.4401   0.01230   0.00382   0.0005   0.1556   0.3580
   3.000   0.4659   0.01193   0.00388   0.0008   0.1520   0.4843
   3.250   0.4919   0.01177   0.00402   0.0013   0.1482   0.5774
   3.500   0.5187   0.01183   0.00420   0.0016   0.1447   0.6249
   3.750   0.5464   0.01190   0.00436   0.0019   0.1419   0.6501
   4.000   0.5741   0.01201   0.00453   0.0022   0.1389   0.6707
   4.250   0.6014   0.01214   0.00470   0.0025   0.1359   0.6888
   4.500   0.6287   0.01229   0.00489   0.0028   0.1329   0.7049
   4.750   0.6563   0.01242   0.00506   0.0030   0.1298   0.7196
   5.000   0.6836   0.01257   0.00525   0.0033   0.1262   0.7333
   5.250   0.7106   0.01275   0.00545   0.0036   0.1231   0.7467
   5.500   0.7380   0.01291   0.00565   0.0039   0.1201   0.7596
   5.750   0.7648   0.01308   0.00585   0.0042   0.1166   0.7710
   6.000   0.7916   0.01329   0.00607   0.0045   0.1135   0.7825
   6.250   0.8183   0.01345   0.00630   0.0049   0.1105   0.7948
   6.500   0.8447   0.01365   0.00653   0.0053   0.1076   0.8074
   6.750   0.8707   0.01387   0.00678   0.0057   0.1048   0.8225
   7.000   0.8964   0.01404   0.00703   0.0062   0.1018   0.8396
   7.250   0.9215   0.01423   0.00729   0.0068   0.0991   0.8605
   7.500   0.9454   0.01441   0.00757   0.0077   0.0967   0.8936
   7.750   0.9802   0.01462   0.00789   0.0064   0.0942   0.9616
   8.000   1.0117   0.01493   0.00821   0.0055   0.0918   1.0000
   8.250   1.0368   0.01528   0.00853   0.0059   0.0897   1.0000
   8.500   1.0621   0.01560   0.00886   0.0062   0.0880   1.0000
   8.750   1.0873   0.01593   0.00920   0.0066   0.0861   1.0000
   9.000   1.1120   0.01630   0.00956   0.0070   0.0837   1.0000
   9.250   1.1363   0.01670   0.00995   0.0074   0.0817   1.0000
   9.500   1.1609   0.01705   0.01033   0.0078   0.0799   1.0000
   9.750   1.1851   0.01744   0.01073   0.0083   0.0778   1.0000
  10.000   1.2085   0.01789   0.01118   0.0087   0.0756   1.0000
  10.250   1.2322   0.01829   0.01161   0.0092   0.0735   1.0000
  10.500   1.2553   0.01873   0.01207   0.0097   0.0706   1.0000
  10.750   1.2777   0.01923   0.01257   0.0103   0.0670   1.0000
  11.000   1.2994   0.01976   0.01311   0.0109   0.0622   1.0000
  11.250   1.3150   0.02084   0.01405   0.0119   0.0444   1.0000
  11.500   1.3293   0.02194   0.01512   0.0131   0.0390   1.0000
  11.750   1.3452   0.02284   0.01604   0.0142   0.0372   1.0000
  12.000   1.3587   0.02375   0.01699   0.0155   0.0359   1.0000
  12.250   1.3716   0.02464   0.01794   0.0169   0.0352   1.0000
  12.500   1.3837   0.02561   0.01897   0.0181   0.0346   1.0000
  12.750   1.3946   0.02671   0.02014   0.0192   0.0342   1.0000
  13.000   1.4040   0.02800   0.02151   0.0200   0.0338   1.0000
  13.250   1.4120   0.02953   0.02311   0.0205   0.0334   1.0000
  13.500   1.4183   0.03132   0.02498   0.0206   0.0331   1.0000
  13.750   1.4228   0.03341   0.02717   0.0205   0.0329   1.0000
  14.000   1.4250   0.03585   0.02971   0.0201   0.0326   1.0000
  14.250   1.4243   0.03874   0.03271   0.0193   0.0324   1.0000
  14.500   1.4201   0.04220   0.03629   0.0181   0.0323   1.0000
  14.750   1.4112   0.04646   0.04068   0.0162   0.0322   1.0000
  15.000   1.3960   0.05185   0.04624   0.0135   0.0321   1.0000
  15.250   1.3705   0.05916   0.05375   0.0095   0.0320   1.0000
  15.500   1.3282   0.06975   0.06460   0.0036   0.0321   1.0000
  15.750   1.2643   0.08395   0.07911  -0.0037   0.0323   1.0000
  16.000   1.2015   0.09764   0.09304  -0.0106   0.0325   1.0000
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