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=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il)
Reynolds number: 500,000
Max Cl/Cd: 71.21 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b737b-il-500000-n5.txt
Download as CSV file: xf-b737b-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -1.0059   0.12237   0.11915   0.0096   1.0000   0.0131
 -17.750  -1.0447   0.11006   0.10663   0.0024   1.0000   0.0131
 -17.500  -1.0720   0.10057   0.09696  -0.0030   1.0000   0.0131
 -17.250  -1.0943   0.09234   0.08858  -0.0077   1.0000   0.0131
 -17.000  -1.1132   0.08495   0.08104  -0.0119   1.0000   0.0131
 -16.750  -1.1294   0.07823   0.07418  -0.0157   1.0000   0.0132
 -16.500  -1.1440   0.07207   0.06788  -0.0192   1.0000   0.0132
 -16.250  -1.1561   0.06648   0.06216  -0.0222   1.0000   0.0133
 -16.000  -1.1661   0.06140   0.05695  -0.0249   1.0000   0.0133
 -15.750  -1.1736   0.05677   0.05220  -0.0273   1.0000   0.0134
 -15.500  -1.1793   0.05256   0.04786  -0.0294   1.0000   0.0135
 -15.250  -1.1828   0.04875   0.04393  -0.0312   1.0000   0.0136
 -15.000  -1.1845   0.04532   0.04037  -0.0326   1.0000   0.0137
 -14.750  -1.1844   0.04221   0.03714  -0.0338   1.0000   0.0138
 -14.500  -1.1827   0.03942   0.03423  -0.0346   1.0000   0.0140
 -14.250  -1.1797   0.03691   0.03159  -0.0351   1.0000   0.0141
 -14.000  -1.1754   0.03469   0.02925  -0.0352   1.0000   0.0143
 -13.750  -1.1697   0.03275   0.02720  -0.0350   1.0000   0.0144
 -13.500  -1.1630   0.03106   0.02538  -0.0344   1.0000   0.0146
 -13.250  -1.1552   0.02958   0.02379  -0.0335   1.0000   0.0148
 -13.000  -1.1461   0.02832   0.02240  -0.0322   1.0000   0.0150
 -12.750  -1.1371   0.02712   0.02112  -0.0306   1.0000   0.0152
 -12.500  -1.1278   0.02600   0.01994  -0.0288   1.0000   0.0154
 -12.250  -1.1137   0.02506   0.01896  -0.0274   1.0000   0.0157
 -12.000  -1.0975   0.02421   0.01806  -0.0262   1.0000   0.0159
 -11.750  -1.0802   0.02341   0.01720  -0.0251   1.0000   0.0162
 -11.500  -1.0621   0.02264   0.01638  -0.0240   1.0000   0.0165
 -11.250  -1.0433   0.02190   0.01558  -0.0229   1.0000   0.0168
 -11.000  -1.0241   0.02118   0.01480  -0.0218   1.0000   0.0171
 -10.750  -1.0043   0.02048   0.01403  -0.0208   1.0000   0.0175
 -10.500  -0.9840   0.01982   0.01330  -0.0197   1.0000   0.0178
 -10.250  -0.9631   0.01922   0.01263  -0.0187   1.0000   0.0182
 -10.000  -0.9434   0.01849   0.01188  -0.0176   1.0000   0.0186
  -9.750  -0.9224   0.01791   0.01128  -0.0165   1.0000   0.0190
  -9.500  -0.9006   0.01741   0.01076  -0.0156   1.0000   0.0195
  -9.250  -0.8787   0.01694   0.01027  -0.0146   1.0000   0.0201
  -9.000  -0.8568   0.01648   0.00976  -0.0135   1.0000   0.0207
  -8.750  -0.8349   0.01603   0.00928  -0.0124   1.0000   0.0213
  -8.500  -0.8135   0.01555   0.00876  -0.0113   1.0000   0.0219
  -8.250  -0.7923   0.01504   0.00825  -0.0101   1.0000   0.0225
  -8.000  -0.7702   0.01463   0.00783  -0.0090   1.0000   0.0232
  -7.750  -0.7478   0.01424   0.00742  -0.0079   1.0000   0.0239
  -7.500  -0.7253   0.01388   0.00704  -0.0068   1.0000   0.0248
  -7.250  -0.6986   0.01352   0.00665  -0.0067   0.9987   0.0257
  -7.000  -0.6637   0.01306   0.00622  -0.0083   0.9942   0.0272
  -6.750  -0.6301   0.01270   0.00584  -0.0095   0.9883   0.0286
  -6.500  -0.5960   0.01236   0.00548  -0.0108   0.9814   0.0300
  -6.250  -0.5624   0.01197   0.00511  -0.0120   0.9720   0.0321
  -6.000  -0.5289   0.01166   0.00480  -0.0131   0.9589   0.0345
  -5.750  -0.4941   0.01131   0.00446  -0.0145   0.9394   0.0380
  -5.500  -0.4589   0.01100   0.00413  -0.0158   0.9077   0.0429
  -5.250  -0.4299   0.01076   0.00381  -0.0158   0.8673   0.0507
  -5.000  -0.4045   0.01052   0.00352  -0.0151   0.8336   0.0655
  -4.750  -0.3802   0.01010   0.00320  -0.0144   0.8068   0.1051
  -4.500  -0.3556   0.00970   0.00293  -0.0138   0.7850   0.1534
  -4.250  -0.3299   0.00942   0.00274  -0.0133   0.7662   0.1908
  -4.000  -0.3037   0.00920   0.00258  -0.0129   0.7488   0.2249
  -3.750  -0.2772   0.00900   0.00244  -0.0125   0.7328   0.2561
  -3.500  -0.2508   0.00882   0.00231  -0.0121   0.7133   0.2866
  -3.250  -0.2247   0.00869   0.00218  -0.0117   0.6881   0.3151
  -3.000  -0.1989   0.00847   0.00205  -0.0112   0.6637   0.3604
  -2.750  -0.1729   0.00821   0.00195  -0.0108   0.6469   0.4136
  -2.500  -0.1460   0.00808   0.00189  -0.0104   0.6318   0.4481
  -2.250  -0.1186   0.00801   0.00183  -0.0102   0.6170   0.4734
  -1.750  -0.0633   0.00795   0.00175  -0.0097   0.5876   0.5124
  -1.500  -0.0356   0.00792   0.00172  -0.0094   0.5731   0.5302
  -1.250  -0.0079   0.00791   0.00170  -0.0092   0.5589   0.5483
  -1.000   0.0199   0.00790   0.00169  -0.0090   0.5439   0.5664
  -0.750   0.0476   0.00791   0.00169  -0.0088   0.5273   0.5829
  -0.500   0.0754   0.00794   0.00169  -0.0086   0.5088   0.5971
  -0.250   0.1031   0.00799   0.00169  -0.0083   0.4874   0.6102
   0.000   0.1306   0.00807   0.00170  -0.0081   0.4635   0.6233
   0.250   0.1580   0.00815   0.00173  -0.0079   0.4384   0.6352
   0.500   0.1853   0.00825   0.00176  -0.0076   0.4109   0.6473
   1.000   0.2396   0.00854   0.00187  -0.0071   0.3489   0.6726
   1.250   0.2666   0.00869   0.00195  -0.0069   0.3229   0.6858
   1.500   0.2937   0.00883   0.00205  -0.0067   0.2992   0.7001
   1.750   0.3206   0.00896   0.00215  -0.0064   0.2790   0.7179
   2.000   0.3472   0.00904   0.00226  -0.0060   0.2634   0.7427
   2.500   0.4000   0.00921   0.00251  -0.0051   0.2363   0.7935
   3.000   0.4528   0.00942   0.00279  -0.0042   0.2134   0.8398
   3.250   0.4787   0.00953   0.00294  -0.0036   0.2035   0.8647
   3.500   0.5047   0.00967   0.00309  -0.0030   0.1927   0.8898
   3.750   0.5316   0.00980   0.00325  -0.0026   0.1837   0.9135
   4.000   0.5603   0.00999   0.00342  -0.0027   0.1745   0.9350
   4.250   0.5920   0.01017   0.00359  -0.0034   0.1653   0.9530
   4.500   0.6249   0.01039   0.00378  -0.0045   0.1570   0.9670
   4.750   0.6584   0.01062   0.00397  -0.0057   0.1489   0.9786
   5.000   0.6923   0.01085   0.00418  -0.0071   0.1418   0.9886
   5.250   0.7262   0.01110   0.00440  -0.0085   0.1349   0.9966
   5.500   0.7552   0.01135   0.00461  -0.0088   0.1296   1.0000
   5.750   0.7796   0.01157   0.00483  -0.0082   0.1247   1.0000
   6.000   0.8038   0.01184   0.00506  -0.0075   0.1199   1.0000
   6.250   0.8285   0.01208   0.00531  -0.0070   0.1161   1.0000
   6.500   0.8535   0.01232   0.00556  -0.0065   0.1120   1.0000
   6.750   0.8782   0.01262   0.00583  -0.0060   0.1075   1.0000
   7.000   0.9032   0.01290   0.00610  -0.0055   0.1034   1.0000
   7.250   0.9283   0.01317   0.00638  -0.0051   0.0993   1.0000
   7.500   0.9530   0.01350   0.00669  -0.0046   0.0954   1.0000
   7.750   0.9779   0.01380   0.00701  -0.0042   0.0922   1.0000
   8.000   1.0030   0.01409   0.00732  -0.0038   0.0889   1.0000
   8.250   1.0276   0.01443   0.00766  -0.0034   0.0856   1.0000
   8.500   1.0519   0.01481   0.00803  -0.0030   0.0823   1.0000
   8.750   1.0767   0.01512   0.00838  -0.0026   0.0792   1.0000
   9.000   1.1009   0.01549   0.00876  -0.0022   0.0758   1.0000
   9.250   1.1246   0.01591   0.00918  -0.0017   0.0728   1.0000
   9.500   1.1487   0.01628   0.00959  -0.0013   0.0699   1.0000
   9.750   1.1721   0.01670   0.01003  -0.0008   0.0666   1.0000
  10.000   1.1951   0.01717   0.01050  -0.0002   0.0636   1.0000
  10.250   1.2181   0.01761   0.01097   0.0003   0.0605   1.0000
  10.500   1.2400   0.01813   0.01151   0.0009   0.0576   1.0000
  10.750   1.2620   0.01863   0.01205   0.0015   0.0551   1.0000
  11.000   1.2834   0.01917   0.01262   0.0021   0.0523   1.0000
  11.250   1.3035   0.01980   0.01326   0.0029   0.0497   1.0000
  11.500   1.3240   0.02036   0.01388   0.0036   0.0474   1.0000
  11.750   1.3430   0.02101   0.01457   0.0045   0.0452   1.0000
  12.000   1.3606   0.02175   0.01533   0.0055   0.0433   1.0000
  12.250   1.3784   0.02242   0.01608   0.0064   0.0417   1.0000
  12.500   1.3936   0.02318   0.01689   0.0077   0.0400   1.0000
  12.750   1.4058   0.02406   0.01780   0.0093   0.0385   1.0000
  13.000   1.4172   0.02500   0.01881   0.0108   0.0374   1.0000
  13.250   1.4285   0.02598   0.01987   0.0121   0.0363   1.0000
  13.500   1.4381   0.02713   0.02111   0.0133   0.0353   1.0000
  13.750   1.4461   0.02851   0.02256   0.0142   0.0344   1.0000
  14.000   1.4523   0.03017   0.02429   0.0148   0.0336   1.0000
  14.250   1.4560   0.03223   0.02643   0.0150   0.0328   1.0000
  14.500   1.4618   0.03422   0.02853   0.0150   0.0321   1.0000
  14.750   1.4660   0.03651   0.03094   0.0146   0.0315   1.0000
  15.000   1.4681   0.03916   0.03370   0.0139   0.0309   1.0000
  15.250   1.4678   0.04220   0.03685   0.0130   0.0303   1.0000
  15.500   1.4648   0.04567   0.04043   0.0117   0.0299   1.0000
  15.750   1.4589   0.04963   0.04450   0.0102   0.0295   1.0000
  16.000   1.4495   0.05414   0.04913   0.0083   0.0291   1.0000
  16.250   1.4363   0.05930   0.05441   0.0060   0.0288   1.0000
  16.500   1.4192   0.06515   0.06039   0.0034   0.0285   1.0000
  16.750   1.3987   0.07164   0.06702   0.0004   0.0283   1.0000
  17.000   1.3763   0.07866   0.07418  -0.0030   0.0281   1.0000
  17.250   1.3558   0.08560   0.08126  -0.0063   0.0280   1.0000
  17.500   1.3339   0.09287   0.08866  -0.0098   0.0278   1.0000
  17.750   1.3124   0.10018   0.09611  -0.0133   0.0277   1.0000
<< Back to BOEING 737 MIDSPAN AIRFOIL (b737b-il)

Polar data table (+)

Polar graphs


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