Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il)
Reynolds number: 100,000
Max Cl/Cd: 37.8 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b737b-il-100000-n5.txt
Download as CSV file: xf-b737b-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 737 MIDSPAN AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7431   0.10347   0.09773  -0.0056   1.0000   0.0346
 -13.250  -0.7799   0.09068   0.08483  -0.0146   1.0000   0.0341
 -13.000  -0.8143   0.08013   0.07409  -0.0226   1.0000   0.0338
 -12.750  -0.8434   0.07195   0.06570  -0.0287   1.0000   0.0335
 -12.500  -0.8678   0.06557   0.05909  -0.0328   1.0000   0.0334
 -12.250  -0.8882   0.06051   0.05377  -0.0351   1.0000   0.0334
 -12.000  -0.9051   0.05642   0.04943  -0.0357   1.0000   0.0335
 -11.750  -0.9185   0.05304   0.04578  -0.0348   1.0000   0.0336
 -11.500  -0.9269   0.05002   0.04246  -0.0331   1.0000   0.0338
 -11.250  -0.9288   0.04707   0.03917  -0.0316   1.0000   0.0341
 -11.000  -0.9260   0.04432   0.03605  -0.0301   1.0000   0.0344
 -10.750  -0.9192   0.04178   0.03312  -0.0285   1.0000   0.0349
 -10.500  -0.9041   0.03983   0.03110  -0.0276   1.0000   0.0354
 -10.250  -0.8882   0.03821   0.02942  -0.0267   1.0000   0.0363
 -10.000  -0.8720   0.03666   0.02775  -0.0257   1.0000   0.0374
  -9.750  -0.8552   0.03504   0.02594  -0.0246   1.0000   0.0387
  -9.500  -0.8372   0.03340   0.02403  -0.0234   1.0000   0.0398
  -9.250  -0.8176   0.03183   0.02230  -0.0224   1.0000   0.0408
  -9.000  -0.7975   0.03045   0.02095  -0.0215   1.0000   0.0417
  -8.750  -0.7775   0.02924   0.01971  -0.0205   1.0000   0.0430
  -8.500  -0.7574   0.02812   0.01852  -0.0194   1.0000   0.0448
  -8.250  -0.7367   0.02708   0.01732  -0.0183   1.0000   0.0468
  -8.000  -0.7178   0.02593   0.01627  -0.0171   1.0000   0.0485
  -7.750  -0.6984   0.02493   0.01528  -0.0159   1.0000   0.0503
  -7.500  -0.6789   0.02401   0.01430  -0.0146   1.0000   0.0526
  -7.250  -0.6600   0.02309   0.01337  -0.0133   1.0000   0.0553
  -7.000  -0.6409   0.02224   0.01253  -0.0119   1.0000   0.0587
  -6.750  -0.6213   0.02145   0.01169  -0.0106   1.0000   0.0624
  -6.500  -0.6025   0.02059   0.01085  -0.0092   1.0000   0.0669
  -6.250  -0.5831   0.01979   0.01008  -0.0079   1.0000   0.0740
  -6.000  -0.5637   0.01896   0.00932  -0.0065   1.0000   0.0851
  -5.750  -0.5450   0.01800   0.00861  -0.0052   1.0000   0.1112
  -5.500  -0.5269   0.01700   0.00805  -0.0040   1.0000   0.1765
  -5.250  -0.5071   0.01634   0.00768  -0.0028   1.0000   0.2353
  -5.000  -0.4862   0.01588   0.00739  -0.0018   1.0000   0.2781
  -4.750  -0.4654   0.01547   0.00714  -0.0007   1.0000   0.3158
  -4.500  -0.4440   0.01508   0.00697   0.0002   0.9992   0.3609
  -4.250  -0.4058   0.01463   0.00694  -0.0022   0.9864   0.4344
  -4.000  -0.3670   0.01440   0.00691  -0.0044   0.9731   0.4885
  -3.750  -0.3297   0.01422   0.00677  -0.0061   0.9572   0.5201
  -3.500  -0.2934   0.01407   0.00664  -0.0075   0.9400   0.5475
  -3.250  -0.2571   0.01394   0.00652  -0.0089   0.9226   0.5733
  -3.000  -0.2216   0.01381   0.00639  -0.0100   0.9044   0.5975
  -2.750  -0.1876   0.01371   0.00627  -0.0107   0.8854   0.6204
  -2.250  -0.1236   0.01354   0.00604  -0.0112   0.8470   0.6613
  -2.000  -0.0941   0.01349   0.00595  -0.0108   0.8275   0.6798
  -1.750  -0.0660   0.01346   0.00586  -0.0102   0.8059   0.6975
  -1.500  -0.0386   0.01345   0.00577  -0.0093   0.7833   0.7149
  -1.250  -0.0120   0.01345   0.00571  -0.0084   0.7607   0.7317
  -1.000   0.0146   0.01346   0.00568  -0.0075   0.7400   0.7486
  -0.750   0.0414   0.01347   0.00566  -0.0067   0.7210   0.7659
  -0.500   0.0680   0.01350   0.00566  -0.0058   0.7027   0.7838
  -0.250   0.0943   0.01353   0.00566  -0.0049   0.6847   0.8026
   0.000   0.1206   0.01357   0.00569  -0.0040   0.6667   0.8231
   0.250   0.1477   0.01363   0.00574  -0.0031   0.6482   0.8444
   0.500   0.1758   0.01369   0.00578  -0.0025   0.6290   0.8661
   0.750   0.2055   0.01376   0.00581  -0.0023   0.6088   0.8861
   1.000   0.2370   0.01385   0.00582  -0.0025   0.5875   0.9045
   1.250   0.2701   0.01395   0.00583  -0.0032   0.5646   0.9220
   1.500   0.3048   0.01405   0.00587  -0.0043   0.5383   0.9388
   1.750   0.3407   0.01417   0.00588  -0.0058   0.5095   0.9547
   2.000   0.3775   0.01432   0.00589  -0.0075   0.4774   0.9698
   2.250   0.4158   0.01451   0.00592  -0.0097   0.4421   0.9832
   2.500   0.4556   0.01474   0.00598  -0.0124   0.4044   0.9954
   2.750   0.4828   0.01501   0.00607  -0.0126   0.3729   1.0000
   3.000   0.5032   0.01530   0.00620  -0.0115   0.3469   1.0000
   3.250   0.5238   0.01565   0.00638  -0.0103   0.3246   1.0000
   3.500   0.5449   0.01601   0.00661  -0.0093   0.3049   1.0000
   3.750   0.5662   0.01639   0.00689  -0.0082   0.2878   1.0000
   4.000   0.5878   0.01680   0.00719  -0.0072   0.2724   1.0000
   4.250   0.6099   0.01721   0.00752  -0.0063   0.2583   1.0000
   4.500   0.6325   0.01762   0.00789  -0.0055   0.2455   1.0000
   4.750   0.6550   0.01806   0.00828  -0.0046   0.2341   1.0000
   5.000   0.6774   0.01854   0.00867  -0.0038   0.2236   1.0000
   5.250   0.7007   0.01898   0.00913  -0.0031   0.2133   1.0000
   5.500   0.7233   0.01949   0.00957  -0.0023   0.2048   1.0000
   5.750   0.7467   0.01997   0.01007  -0.0016   0.1958   1.0000
   6.000   0.7694   0.02052   0.01058  -0.0009   0.1884   1.0000
   6.250   0.7928   0.02103   0.01114  -0.0003   0.1807   1.0000
   6.500   0.8153   0.02164   0.01166   0.0004   0.1745   1.0000
   6.750   0.8387   0.02219   0.01232   0.0010   0.1675   1.0000
   7.000   0.8611   0.02279   0.01290   0.0017   0.1618   1.0000
   7.250   0.8839   0.02345   0.01361   0.0023   0.1561   1.0000
   7.500   0.9065   0.02407   0.01430   0.0029   0.1503   1.0000
   7.750   0.9283   0.02478   0.01495   0.0036   0.1458   1.0000
   8.000   0.9506   0.02550   0.01582   0.0042   0.1404   1.0000
   8.250   0.9722   0.02619   0.01656   0.0049   0.1354   1.0000
   8.500   0.9931   0.02698   0.01729   0.0056   0.1313   1.0000
   8.750   1.0140   0.02779   0.01832   0.0063   0.1262   1.0000
   9.000   1.0342   0.02856   0.01916   0.0070   0.1216   1.0000
   9.250   1.0538   0.02940   0.01994   0.0078   0.1178   1.0000
   9.500   1.0726   0.03035   0.02115   0.0086   0.1132   1.0000
   9.750   1.0907   0.03122   0.02211   0.0095   0.1089   1.0000
  10.000   1.1083   0.03210   0.02295   0.0103   0.1055   1.0000
  10.250   1.1241   0.03327   0.02438   0.0113   0.1015   1.0000
  10.500   1.1391   0.03434   0.02558   0.0124   0.0977   1.0000
  10.750   1.1536   0.03531   0.02657   0.0134   0.0947   1.0000
  11.000   1.1657   0.03665   0.02805   0.0146   0.0917   1.0000
  11.250   1.1749   0.03808   0.02972   0.0159   0.0884   1.0000
  11.500   1.1824   0.03936   0.03110   0.0175   0.0857   1.0000
  11.750   1.1904   0.04061   0.03235   0.0188   0.0836   1.0000
  12.000   1.1937   0.04249   0.03442   0.0200   0.0814   1.0000
  12.250   1.1933   0.04477   0.03695   0.0209   0.0790   1.0000
  12.500   1.1933   0.04705   0.03941   0.0213   0.0770   1.0000
  12.750   1.1944   0.04930   0.04175   0.0214   0.0752   1.0000
  13.000   1.1975   0.05143   0.04389   0.0213   0.0737   1.0000
  13.250   1.1906   0.05499   0.04766   0.0204   0.0722   1.0000
  13.500   1.1761   0.05976   0.05272   0.0186   0.0709   1.0000
  13.750   1.1589   0.06520   0.05842   0.0161   0.0697   1.0000
  14.000   1.1371   0.07168   0.06512   0.0126   0.0688   1.0000
  14.250   1.1041   0.08045   0.07414   0.0074   0.0682   1.0000
<< Back to BOEING 737 MIDSPAN AIRFOIL (b737b-il)

Polar data table (+)

Polar graphs


<< Back to BOEING 737 MIDSPAN AIRFOIL (b737b-il)