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BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il)
Reynolds number: 50,000
Max Cl/Cd: 19.42 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b737a-il-50000-n5.txt
Download as CSV file: xf-b737a-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7059   0.10545   0.09660   0.0039   1.0000   0.1675
 -12.500  -0.6884   0.10497   0.09609   0.0049   1.0000   0.1726
 -12.250  -0.7164   0.09618   0.08727  -0.0004   1.0000   0.1764
 -12.000  -0.7088   0.09375   0.08482  -0.0008   1.0000   0.1797
 -11.750  -0.6973   0.09202   0.08308  -0.0007   1.0000   0.1835
 -11.500  -0.7410   0.07995   0.07095  -0.0086   1.0000   0.1863
 -11.250  -0.8631   0.05980   0.05053  -0.0210   1.0000   0.1849
 -11.000  -0.8949   0.05434   0.04481  -0.0210   1.0000   0.1864
 -10.750  -0.9107   0.05018   0.04029  -0.0205   1.0000   0.1888
 -10.500  -0.9010   0.04848   0.03848  -0.0196   1.0000   0.1917
 -10.250  -0.8789   0.04817   0.03822  -0.0187   1.0000   0.1954
 -10.000  -0.8686   0.04650   0.03640  -0.0178   1.0000   0.1991
  -9.750  -0.8632   0.04414   0.03373  -0.0169   1.0000   0.2026
  -9.500  -0.8501   0.04241   0.03182  -0.0160   1.0000   0.2055
  -9.250  -0.8285   0.04149   0.03092  -0.0153   1.0000   0.2078
  -9.000  -0.8095   0.04022   0.02958  -0.0145   1.0000   0.2099
  -8.750  -0.7912   0.03879   0.02802  -0.0137   1.0000   0.2120
  -8.500  -0.7728   0.03734   0.02642  -0.0130   1.0000   0.2143
  -8.250  -0.7543   0.03590   0.02479  -0.0122   1.0000   0.2169
  -8.000  -0.7358   0.03445   0.02311  -0.0114   1.0000   0.2199
  -7.750  -0.7133   0.03345   0.02213  -0.0106   1.0000   0.2222
  -7.500  -0.6907   0.03256   0.02128  -0.0098   1.0000   0.2249
  -7.250  -0.6687   0.03164   0.02035  -0.0090   1.0000   0.2282
  -7.000  -0.6473   0.03069   0.01933  -0.0081   1.0000   0.2325
  -6.750  -0.6267   0.02970   0.01817  -0.0072   1.0000   0.2377
  -6.500  -0.6043   0.02899   0.01762  -0.0063   1.0000   0.2417
  -6.250  -0.5832   0.02830   0.01698  -0.0052   1.0000   0.2471
  -6.000  -0.5632   0.02761   0.01622  -0.0040   1.0000   0.2540
  -5.750  -0.5433   0.02700   0.01571  -0.0028   1.0000   0.2600
  -5.500  -0.5245   0.02649   0.01529  -0.0015   1.0000   0.2668
  -5.250  -0.5069   0.02602   0.01475  -0.0001   1.0000   0.2748
  -5.000  -0.4900   0.02561   0.01448   0.0014   1.0000   0.2814
  -4.750  -0.4739   0.02527   0.01419   0.0030   1.0000   0.2892
  -4.500  -0.4575   0.02498   0.01387   0.0044   1.0000   0.2973
  -4.250  -0.4316   0.02467   0.01370   0.0041   0.9951   0.3059
  -4.000  -0.3900   0.02439   0.01342   0.0011   0.9820   0.3187
  -3.750  -0.3421   0.02403   0.01322  -0.0029   0.9650   0.3337
  -3.500  -0.2889   0.02355   0.01290  -0.0073   0.9395   0.3492
  -3.250  -0.2357   0.02299   0.01245  -0.0111   0.9079   0.3661
  -2.750  -0.1557   0.02211   0.01178  -0.0136   0.8509   0.3991
  -2.500  -0.1262   0.02180   0.01161  -0.0131   0.8262   0.4190
  -2.250  -0.0998   0.02153   0.01150  -0.0119   0.8007   0.4440
  -2.000  -0.0757   0.02129   0.01147  -0.0101   0.7743   0.4756
  -1.750  -0.0539   0.02112   0.01155  -0.0078   0.7460   0.5155
  -1.500  -0.0328   0.02105   0.01173  -0.0051   0.7144   0.5609
  -1.250  -0.0117   0.02106   0.01183  -0.0023   0.6795   0.6068
  -1.000   0.0087   0.02110   0.01187   0.0004   0.6376   0.6486
  -0.750   0.0290   0.02118   0.01189   0.0034   0.5859   0.6824
  -0.500   0.0488   0.02134   0.01178   0.0062   0.5233   0.7130
  -0.250   0.0685   0.02162   0.01172   0.0089   0.4607   0.7389
   0.000   0.0889   0.02202   0.01176   0.0112   0.4155   0.7616
   0.250   0.1104   0.02244   0.01190   0.0130   0.3847   0.7825
   0.500   0.1331   0.02284   0.01210   0.0146   0.3623   0.8025
   1.000   0.1846   0.02362   0.01265   0.0166   0.3303   0.8395
   1.250   0.2132   0.02404   0.01297   0.0171   0.3181   0.8576
   1.500   0.2447   0.02448   0.01336   0.0172   0.3067   0.8786
   1.750   0.2810   0.02502   0.01383   0.0164   0.2966   0.9020
   2.000   0.3230   0.02560   0.01437   0.0144   0.2858   0.9268
   2.250   0.3737   0.02631   0.01498   0.0107   0.2764   0.9488
   2.500   0.4271   0.02695   0.01563   0.0060   0.2661   0.9673
   2.750   0.4746   0.02763   0.01609   0.0022   0.2586   0.9826
   3.000   0.5168   0.02824   0.01687  -0.0010   0.2504   0.9958
   3.250   0.5412   0.02876   0.01738  -0.0012   0.2445   1.0000
   3.500   0.5575   0.02930   0.01779   0.0003   0.2404   1.0000
   3.750   0.5722   0.02994   0.01849   0.0018   0.2360   1.0000
   4.000   0.5860   0.03061   0.01927   0.0036   0.2311   1.0000
   4.250   0.6013   0.03129   0.01997   0.0051   0.2267   1.0000
   4.500   0.6187   0.03198   0.02058   0.0064   0.2229   1.0000
   4.750   0.6377   0.03284   0.02134   0.0075   0.2193   1.0000
   5.000   0.6545   0.03395   0.02266   0.0086   0.2148   1.0000
   5.250   0.6735   0.03504   0.02386   0.0094   0.2106   1.0000
   5.500   0.6942   0.03605   0.02486   0.0101   0.2069   1.0000
   5.750   0.7166   0.03701   0.02573   0.0106   0.2039   1.0000
   6.000   0.7351   0.03846   0.02732   0.0112   0.2007   1.0000
   6.250   0.7500   0.04028   0.02942   0.0120   0.1972   1.0000
   6.500   0.7662   0.04197   0.03127   0.0126   0.1939   1.0000
   6.750   0.7838   0.04348   0.03287   0.0132   0.1910   1.0000
   7.000   0.8033   0.04482   0.03422   0.0137   0.1885   1.0000
   7.250   0.8249   0.04610   0.03544   0.0140   0.1864   1.0000
   7.500   0.8257   0.04936   0.03912   0.0148   0.1840   1.0000
   7.750   0.8215   0.05308   0.04320   0.0154   0.1817   1.0000
   8.000   0.8120   0.05719   0.04760   0.0157   0.1794   1.0000
   8.250   0.7948   0.06192   0.05254   0.0154   0.1774   1.0000
   8.500   0.7610   0.06813   0.05893   0.0140   0.1756   1.0000
   8.750   0.7225   0.07663   0.06754   0.0092   0.1737   1.0000
   9.000   0.7191   0.08119   0.07211   0.0071   0.1722   1.0000
   9.250   0.6852   0.09196   0.08293   0.0002   0.1708   1.0000
   9.500   0.6479   0.10306   0.09407  -0.0070   0.1696   1.0000
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