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BOEING 737 MIDSPAN AIRFOIL (b737c-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737c-il)
Reynolds number: 100,000
Max Cl/Cd: 47.07 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b737c-il-100000-n5.txt
Download as CSV file: xf-b737c-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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4221   0.08931   0.08480  -0.0204   1.0000   0.0532
  -9.000  -0.4262   0.08479   0.08031  -0.0221   1.0000   0.0535
  -8.750  -0.4317   0.08007   0.07563  -0.0241   1.0000   0.0537
  -8.500  -0.4394   0.07507   0.07067  -0.0268   1.0000   0.0537
  -8.250  -0.4519   0.06968   0.06530  -0.0305   1.0000   0.0538
  -8.000  -0.4672   0.06509   0.06071  -0.0326   1.0000   0.0538
  -7.750  -0.4807   0.06103   0.05662  -0.0328   1.0000   0.0537
  -7.500  -0.4896   0.05681   0.05233  -0.0328   1.0000   0.0536
  -7.250  -0.4956   0.05261   0.04803  -0.0322   1.0000   0.0532
  -6.750  -0.5386   0.05497   0.04928  -0.0277   1.0000   0.0327
  -6.500  -0.5321   0.05127   0.04547  -0.0264   1.0000   0.0312
  -6.250  -0.5238   0.04794   0.04192  -0.0247   1.0000   0.0302
  -6.000  -0.5133   0.04498   0.03870  -0.0228   1.0000   0.0304
  -5.750  -0.5012   0.04219   0.03558  -0.0209   1.0000   0.0308
  -5.500  -0.4881   0.03939   0.03249  -0.0189   1.0000   0.0305
  -5.250  -0.4738   0.03654   0.02934  -0.0168   1.0000   0.0293
  -5.000  -0.4577   0.03382   0.02627  -0.0148   1.0000   0.0282
  -4.750  -0.4398   0.03126   0.02333  -0.0128   1.0000   0.0273
  -4.500  -0.4175   0.02879   0.02046  -0.0115   0.9988   0.0266
  -4.250  -0.3811   0.02624   0.01747  -0.0130   0.9923   0.0261
  -4.000  -0.3435   0.02411   0.01501  -0.0147   0.9857   0.0261
  -3.750  -0.3066   0.02229   0.01297  -0.0163   0.9779   0.0265
  -3.500  -0.2697   0.02105   0.01161  -0.0182   0.9691   0.0287
  -3.250  -0.2333   0.01988   0.01035  -0.0199   0.9595   0.0314
  -3.000  -0.1996   0.01864   0.00905  -0.0209   0.9485   0.0327
  -2.750  -0.1685   0.01764   0.00799  -0.0216   0.9352   0.0349
  -2.500  -0.1389   0.01700   0.00732  -0.0221   0.9188   0.0401
  -2.250  -0.1096   0.01638   0.00654  -0.0223   0.9010   0.0444
  -2.000  -0.0799   0.01582   0.00583  -0.0225   0.8833   0.0520
  -1.750  -0.0500   0.01532   0.00521  -0.0228   0.8663   0.0708
  -1.500  -0.0301   0.01315   0.00474  -0.0222   0.8499   0.5074
  -1.250  -0.0046   0.01266   0.00456  -0.0213   0.8352   0.6267
  -1.000   0.0206   0.01231   0.00453  -0.0200   0.8224   0.7142
  -0.750   0.0492   0.01222   0.00462  -0.0190   0.8114   0.7982
  -0.500   0.0804   0.01232   0.00473  -0.0186   0.8009   0.8797
  -0.250   0.1143   0.01241   0.00472  -0.0192   0.7909   0.9143
   0.000   0.1509   0.01249   0.00468  -0.0207   0.7813   0.9401
   0.250   0.2135   0.01259   0.00467  -0.0274   0.7729   0.9770
   0.500   0.2609   0.01258   0.00454  -0.0316   0.7624   0.9903
   0.750   0.3000   0.01258   0.00443  -0.0342   0.7511   0.9988
   1.000   0.3263   0.01263   0.00439  -0.0341   0.7407   1.0000
   1.250   0.3504   0.01271   0.00439  -0.0336   0.7307   1.0000
   1.500   0.3746   0.01280   0.00444  -0.0331   0.7210   1.0000
   1.750   0.3987   0.01291   0.00449  -0.0325   0.7115   1.0000
   2.000   0.4226   0.01303   0.00458  -0.0317   0.7004   1.0000
   2.250   0.4461   0.01316   0.00467  -0.0310   0.6874   1.0000
   2.500   0.4694   0.01329   0.00478  -0.0301   0.6739   1.0000
   2.750   0.4928   0.01343   0.00491  -0.0293   0.6605   1.0000
   3.000   0.5162   0.01358   0.00510  -0.0285   0.6472   1.0000
   3.250   0.5396   0.01373   0.00526  -0.0276   0.6339   1.0000
   3.500   0.5630   0.01388   0.00544  -0.0267   0.6198   1.0000
   3.750   0.5862   0.01404   0.00563  -0.0258   0.6049   1.0000
   4.000   0.6092   0.01420   0.00585  -0.0248   0.5884   1.0000
   4.250   0.6320   0.01439   0.00604  -0.0237   0.5695   1.0000
   4.500   0.6539   0.01453   0.00628  -0.0226   0.5428   1.0000
   4.750   0.6760   0.01458   0.00658  -0.0216   0.4902   1.0000
   5.000   0.6952   0.01477   0.00637  -0.0196   0.4490   1.0000
   5.250   0.7159   0.01521   0.00675  -0.0184   0.4065   1.0000
   5.500   0.7356   0.01576   0.00715  -0.0170   0.3590   1.0000
   5.750   0.7551   0.01639   0.00764  -0.0158   0.3177   1.0000
   6.000   0.7746   0.01706   0.00819  -0.0146   0.2767   1.0000
   6.250   0.7940   0.01777   0.00882  -0.0134   0.2389   1.0000
   6.500   0.8127   0.01857   0.00947  -0.0122   0.2034   1.0000
   6.750   0.8320   0.01935   0.01018  -0.0112   0.1712   1.0000
   7.000   0.8513   0.02017   0.01093  -0.0101   0.1420   1.0000
   7.250   0.8702   0.02105   0.01174  -0.0091   0.1152   1.0000
   7.500   0.8882   0.02206   0.01268  -0.0080   0.0921   1.0000
   7.750   0.9057   0.02314   0.01375  -0.0067   0.0743   1.0000
   8.000   0.9227   0.02427   0.01492  -0.0055   0.0606   1.0000
   8.250   0.9383   0.02555   0.01619  -0.0041   0.0519   1.0000
   8.500   0.9546   0.02680   0.01765  -0.0026   0.0461   1.0000
   8.750   0.9689   0.02824   0.01917  -0.0010   0.0421   1.0000
   9.000   0.9826   0.02997   0.02101   0.0007   0.0394   1.0000
   9.250   0.9987   0.03150   0.02278   0.0020   0.0361   1.0000
   9.500   1.0132   0.03293   0.02437   0.0033   0.0326   1.0000
   9.750   1.0256   0.03488   0.02644   0.0048   0.0305   1.0000
  10.000   1.0375   0.03723   0.02902   0.0062   0.0283   1.0000
  10.250   1.0487   0.03911   0.03124   0.0078   0.0257   1.0000
  10.500   1.0569   0.04143   0.03385   0.0094   0.0241   1.0000
  10.750   1.0609   0.04363   0.03628   0.0114   0.0227   1.0000
  11.000   1.0621   0.04573   0.03852   0.0132   0.0215   1.0000
  11.250   1.0588   0.04863   0.04155   0.0148   0.0204   1.0000
  11.500   1.0515   0.05196   0.04518   0.0161   0.0196   1.0000
  11.750   1.0431   0.05536   0.04891   0.0168   0.0191   1.0000
  12.000   1.0317   0.05940   0.05327   0.0166   0.0186   1.0000
  12.250   1.0178   0.06410   0.05825   0.0153   0.0184   1.0000
  12.500   1.0016   0.06950   0.06390   0.0131   0.0183   1.0000
  12.750   0.9834   0.07565   0.07028   0.0100   0.0183   1.0000
  13.000   0.9636   0.08256   0.07738   0.0060   0.0185   1.0000
  13.250   0.9424   0.09048   0.08545   0.0010   0.0187   1.0000
  13.500   0.9209   0.09930   0.09439  -0.0047   0.0192   1.0000
  13.750   0.8998   0.10869   0.10386  -0.0104   0.0196   1.0000
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