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BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il)
Reynolds number: 50,000
Max Cl/Cd: 26.73 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b737b-il-50000-n5.txt
Download as CSV file: xf-b737b-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6950   0.09454   0.08672  -0.0132   1.0000   0.0587
 -11.750  -0.7367   0.08218   0.07424  -0.0226   1.0000   0.0575
 -11.500  -0.7763   0.07304   0.06486  -0.0294   1.0000   0.0567
 -11.250  -0.8047   0.06707   0.05865  -0.0322   1.0000   0.0563
 -11.000  -0.8240   0.06278   0.05411  -0.0322   1.0000   0.0563
 -10.750  -0.8337   0.05915   0.05022  -0.0315   1.0000   0.0566
 -10.500  -0.8360   0.05587   0.04669  -0.0306   1.0000   0.0573
 -10.250  -0.8344   0.05281   0.04333  -0.0296   1.0000   0.0584
 -10.000  -0.8301   0.04984   0.04001  -0.0285   1.0000   0.0598
  -9.750  -0.8227   0.04698   0.03671  -0.0272   1.0000   0.0612
  -9.500  -0.8097   0.04442   0.03386  -0.0262   1.0000   0.0625
  -9.250  -0.7916   0.04230   0.03167  -0.0253   1.0000   0.0640
  -9.000  -0.7732   0.04033   0.02957  -0.0244   1.0000   0.0658
  -8.750  -0.7545   0.03850   0.02753  -0.0234   1.0000   0.0685
  -8.500  -0.7345   0.03674   0.02552  -0.0223   1.0000   0.0715
  -8.250  -0.7141   0.03517   0.02403  -0.0214   1.0000   0.0745
  -8.000  -0.6934   0.03371   0.02248  -0.0203   1.0000   0.0778
  -7.750  -0.6729   0.03234   0.02098  -0.0191   1.0000   0.0822
  -7.500  -0.6545   0.03102   0.01973  -0.0178   1.0000   0.0873
  -7.250  -0.6352   0.02978   0.01840  -0.0165   1.0000   0.0934
  -7.000  -0.6179   0.02850   0.01721  -0.0151   1.0000   0.1013
  -6.750  -0.6007   0.02723   0.01602  -0.0137   1.0000   0.1127
  -6.500  -0.5837   0.02592   0.01484  -0.0122   1.0000   0.1314
  -6.250  -0.5684   0.02448   0.01379  -0.0108   1.0000   0.1682
  -6.000  -0.5528   0.02327   0.01299  -0.0093   1.0000   0.2320
  -5.750  -0.5355   0.02245   0.01237  -0.0078   1.0000   0.2918
  -5.500  -0.5178   0.02181   0.01195  -0.0061   1.0000   0.3416
  -5.250  -0.5006   0.02132   0.01173  -0.0043   1.0000   0.3929
  -5.000  -0.4843   0.02104   0.01175  -0.0020   1.0000   0.4486
  -4.750  -0.4664   0.02087   0.01176   0.0003   1.0000   0.4923
  -4.500  -0.4461   0.02064   0.01157   0.0019   1.0000   0.5224
  -4.250  -0.4257   0.02041   0.01134   0.0035   1.0000   0.5492
  -4.000  -0.4058   0.02022   0.01117   0.0051   1.0000   0.5747
  -3.750  -0.3865   0.02007   0.01102   0.0068   1.0000   0.6005
  -3.500  -0.3677   0.01994   0.01091   0.0084   1.0000   0.6258
  -3.250  -0.3496   0.01987   0.01086   0.0102   1.0000   0.6497
  -3.000  -0.3278   0.01984   0.01083   0.0111   0.9974   0.6750
  -2.750  -0.2858   0.01989   0.01086   0.0085   0.9815   0.7021
  -2.500  -0.2450   0.01991   0.01086   0.0063   0.9651   0.7283
  -2.250  -0.2033   0.01994   0.01086   0.0040   0.9496   0.7531
  -2.000  -0.1626   0.01996   0.01087   0.0021   0.9336   0.7761
  -1.750  -0.1231   0.01996   0.01085   0.0004   0.9170   0.7990
  -1.500  -0.0839   0.01995   0.01081  -0.0011   0.9001   0.8218
  -1.250  -0.0424   0.01996   0.01080  -0.0029   0.8832   0.8426
  -1.000   0.0002   0.01995   0.01075  -0.0047   0.8648   0.8634
  -0.750   0.0436   0.01992   0.01067  -0.0067   0.8439   0.8838
  -0.500   0.0874   0.01987   0.01053  -0.0086   0.8215   0.9032
  -0.250   0.1301   0.01982   0.01037  -0.0105   0.7980   0.9210
   0.000   0.1712   0.01979   0.01025  -0.0125   0.7729   0.9378
   0.250   0.2139   0.01974   0.01008  -0.0148   0.7485   0.9532
   0.500   0.2558   0.01969   0.00994  -0.0173   0.7231   0.9688
   0.750   0.2974   0.01963   0.00980  -0.0198   0.6967   0.9844
   1.000   0.3396   0.01956   0.00963  -0.0226   0.6695   0.9997
   1.250   0.3573   0.01959   0.00958  -0.0211   0.6454   1.0000
   1.500   0.3751   0.01964   0.00952  -0.0193   0.6218   1.0000
   1.750   0.3930   0.01974   0.00953  -0.0176   0.5966   1.0000
   2.000   0.4115   0.01986   0.00955  -0.0159   0.5708   1.0000
   2.250   0.4305   0.02002   0.00959  -0.0142   0.5440   1.0000
   2.500   0.4497   0.02022   0.00967  -0.0126   0.5158   1.0000
   2.750   0.4697   0.02046   0.00979  -0.0111   0.4864   1.0000
   3.000   0.4900   0.02075   0.00992  -0.0096   0.4581   1.0000
   3.250   0.5105   0.02110   0.01012  -0.0083   0.4297   1.0000
   3.500   0.5314   0.02151   0.01038  -0.0070   0.4025   1.0000
   3.750   0.5526   0.02197   0.01070  -0.0059   0.3782   1.0000
   4.000   0.5741   0.02249   0.01106  -0.0048   0.3562   1.0000
   4.250   0.5959   0.02306   0.01153  -0.0039   0.3359   1.0000
   4.500   0.6179   0.02368   0.01206  -0.0030   0.3180   1.0000
   4.750   0.6400   0.02434   0.01262  -0.0021   0.3018   1.0000
   5.000   0.6624   0.02504   0.01323  -0.0013   0.2876   1.0000
   5.250   0.6850   0.02577   0.01389  -0.0005   0.2743   1.0000
   5.500   0.7075   0.02654   0.01471   0.0002   0.2614   1.0000
   5.750   0.7303   0.02736   0.01551   0.0009   0.2505   1.0000
   6.000   0.7531   0.02817   0.01625   0.0015   0.2407   1.0000
   6.250   0.7753   0.02908   0.01730   0.0022   0.2304   1.0000
   6.500   0.7984   0.02995   0.01807   0.0028   0.2225   1.0000
   6.750   0.8199   0.03098   0.01930   0.0035   0.2134   1.0000
   7.000   0.8428   0.03188   0.02011   0.0041   0.2063   1.0000
   7.250   0.8631   0.03309   0.02158   0.0048   0.1983   1.0000
   7.500   0.8854   0.03404   0.02250   0.0054   0.1919   1.0000
   7.750   0.9045   0.03540   0.02411   0.0061   0.1849   1.0000
   8.000   0.9247   0.03657   0.02536   0.0068   0.1787   1.0000
   8.250   0.9448   0.03783   0.02668   0.0075   0.1732   1.0000
   8.500   0.9605   0.03945   0.02859   0.0084   0.1668   1.0000
   8.750   0.9806   0.04059   0.02975   0.0090   0.1618   1.0000
   9.000   0.9944   0.04245   0.03186   0.0100   0.1566   1.0000
   9.250   1.0064   0.04431   0.03398   0.0110   0.1512   1.0000
   9.500   1.0256   0.04547   0.03512   0.0116   0.1468   1.0000
   9.750   1.0314   0.04793   0.03791   0.0128   0.1424   1.0000
  10.000   1.0334   0.05056   0.04086   0.0140   0.1379   1.0000
  10.250   1.0450   0.05220   0.04258   0.0149   0.1340   1.0000
  10.500   1.0552   0.05405   0.04448   0.0158   0.1305   1.0000
  10.750   1.0318   0.05849   0.04934   0.0172   0.1280   1.0000
  11.000   1.0006   0.06375   0.05489   0.0174   0.1263   1.0000
  11.250   0.9397   0.07412   0.06555   0.0124   0.1261   1.0000
  11.500   0.8075   0.10323   0.09474  -0.0072   0.1251   1.0000
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