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BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il)
Reynolds number: 100,000
Max Cl/Cd: 23.89 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b737a-il-100000.txt
Download as CSV file: xf-b737a-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -1.0633   0.08145   0.07486  -0.0232   1.0000   0.0963
 -15.750  -1.1248   0.06922   0.06225  -0.0312   1.0000   0.0962
 -15.500  -1.1362   0.06474   0.05768  -0.0330   1.0000   0.0980
 -15.250  -1.1431   0.06103   0.05389  -0.0341   1.0000   0.1004
 -15.000  -1.1708   0.05535   0.04791  -0.0363   1.0000   0.1022
 -14.750  -1.2028   0.05013   0.04225  -0.0375   1.0000   0.1039
 -14.500  -1.1837   0.04906   0.04140  -0.0365   1.0000   0.1085
 -14.250  -1.2089   0.04511   0.03703  -0.0360   1.0000   0.1115
 -14.000  -1.1937   0.04380   0.03593  -0.0351   1.0000   0.1175
 -13.750  -1.1890   0.04211   0.03431  -0.0338   1.0000   0.1235
 -13.500  -1.1932   0.04018   0.03226  -0.0317   1.0000   0.1294
 -13.250  -1.1867   0.03914   0.03122  -0.0300   1.0000   0.1362
 -13.000  -1.1670   0.03929   0.03160  -0.0287   1.0000   0.1431
 -12.750  -1.1506   0.03932   0.03169  -0.0273   1.0000   0.1494
 -12.500  -1.1444   0.03838   0.03049  -0.0256   1.0000   0.1556
 -12.250  -1.1101   0.04033   0.03279  -0.0248   1.0000   0.1620
 -12.000  -1.1030   0.03909   0.03126  -0.0232   1.0000   0.1669
 -11.750  -1.0675   0.04095   0.03340  -0.0225   1.0000   0.1725
 -11.500  -1.0614   0.03927   0.03136  -0.0210   1.0000   0.1766
 -11.250  -1.0327   0.03982   0.03207  -0.0203   1.0000   0.1805
 -11.000  -1.0073   0.04008   0.03237  -0.0195   1.0000   0.1847
 -10.750  -0.9960   0.03864   0.03064  -0.0183   1.0000   0.1884
 -10.500  -0.9798   0.03743   0.02924  -0.0172   1.0000   0.1912
 -10.250  -0.9520   0.03750   0.02945  -0.0167   1.0000   0.1942
 -10.000  -0.9287   0.03707   0.02902  -0.0159   1.0000   0.1973
  -9.750  -0.9106   0.03604   0.02783  -0.0150   1.0000   0.2006
  -9.500  -0.8955   0.03467   0.02615  -0.0138   1.0000   0.2034
  -9.250  -0.8747   0.03357   0.02497  -0.0130   1.0000   0.2058
  -9.000  -0.8503   0.03294   0.02441  -0.0124   1.0000   0.2081
  -8.750  -0.8274   0.03220   0.02366  -0.0117   1.0000   0.2104
  -8.500  -0.8052   0.03140   0.02280  -0.0108   1.0000   0.2130
  -8.250  -0.7843   0.03046   0.02173  -0.0099   1.0000   0.2157
  -8.000  -0.7642   0.02949   0.02057  -0.0089   1.0000   0.2185
  -7.750  -0.7437   0.02851   0.01944  -0.0079   1.0000   0.2210
  -7.500  -0.7200   0.02771   0.01876  -0.0072   1.0000   0.2237
  -7.250  -0.6975   0.02703   0.01811  -0.0062   1.0000   0.2263
  -7.000  -0.6758   0.02627   0.01732  -0.0052   1.0000   0.2288
  -6.750  -0.6546   0.02544   0.01643  -0.0042   1.0000   0.2312
  -6.500  -0.6340   0.02461   0.01553  -0.0030   1.0000   0.2335
  -6.250  -0.6149   0.02387   0.01468  -0.0017   1.0000   0.2362
  -6.000  -0.5970   0.02311   0.01390  -0.0003   1.0000   0.2390
  -5.750  -0.5801   0.02249   0.01342   0.0012   1.0000   0.2422
  -5.500  -0.5640   0.02203   0.01302   0.0028   1.0000   0.2463
  -5.250  -0.5473   0.02159   0.01255   0.0042   1.0000   0.2522
  -5.000  -0.5293   0.02105   0.01202   0.0052   1.0000   0.2591
  -4.750  -0.5106   0.02066   0.01177   0.0062   1.0000   0.2675
  -4.500  -0.4824   0.02021   0.01137   0.0054   0.9971   0.2801
  -4.250  -0.4157   0.01966   0.01098  -0.0019   0.9804   0.3008
  -4.000  -0.3562   0.01919   0.01059  -0.0076   0.9643   0.3193
  -3.750  -0.3009   0.01865   0.01021  -0.0123   0.9478   0.3354
  -3.500  -0.2533   0.01811   0.00983  -0.0153   0.9313   0.3488
  -3.250  -0.2108   0.01770   0.00948  -0.0174   0.9148   0.3632
  -3.000  -0.1732   0.01728   0.00920  -0.0183   0.8964   0.3757
  -2.750  -0.1404   0.01692   0.00894  -0.0182   0.8764   0.3885
  -2.500  -0.1117   0.01667   0.00874  -0.0173   0.8546   0.4027
  -2.250  -0.0862   0.01639   0.00860  -0.0158   0.8313   0.4178
  -2.000  -0.0624   0.01613   0.00848  -0.0140   0.8065   0.4373
  -1.750  -0.0400   0.01583   0.00835  -0.0118   0.7798   0.4655
  -1.500  -0.0190   0.01548   0.00826  -0.0092   0.7510   0.5096
  -1.250   0.0002   0.01523   0.00835  -0.0061   0.7139   0.5759
  -1.000   0.0192   0.01517   0.00840  -0.0026   0.6639   0.6390
  -0.750   0.0371   0.01529   0.00832   0.0012   0.5757   0.6838
  -0.500   0.0544   0.01587   0.00829   0.0046   0.4662   0.7182
  -0.250   0.0740   0.01655   0.00856   0.0072   0.4137   0.7453
   0.000   0.0955   0.01712   0.00889   0.0094   0.3854   0.7697
   0.250   0.1179   0.01762   0.00921   0.0114   0.3659   0.7913
   0.500   0.1409   0.01800   0.00952   0.0133   0.3503   0.8116
   0.750   0.1642   0.01843   0.00986   0.0151   0.3383   0.8310
   1.000   0.1880   0.01882   0.01016   0.0168   0.3275   0.8499
   1.250   0.2126   0.01928   0.01056   0.0183   0.3182   0.8689
   1.500   0.2386   0.01966   0.01093   0.0195   0.3090   0.8879
   1.750   0.2694   0.02037   0.01147   0.0199   0.3007   0.9058
   2.000   0.3065   0.02082   0.01202   0.0190   0.2916   0.9226
   2.250   0.3507   0.02155   0.01260   0.0166   0.2825   0.9391
   2.500   0.4008   0.02235   0.01344   0.0128   0.2734   0.9540
   2.750   0.4515   0.02299   0.01403   0.0086   0.2643   0.9664
   3.000   0.4997   0.02395   0.01490   0.0046   0.2568   0.9784
   3.250   0.5529   0.02457   0.01567  -0.0005   0.2484   0.9894
   3.500   0.6056   0.02535   0.01633  -0.0056   0.2414   1.0000
   3.750   0.6228   0.02624   0.01726  -0.0045   0.2374   1.0000
   4.000   0.6377   0.02684   0.01807  -0.0030   0.2330   1.0000
   4.250   0.6519   0.02749   0.01880  -0.0014   0.2289   1.0000
   4.500   0.6650   0.02813   0.01944   0.0004   0.2255   1.0000
   4.750   0.6772   0.02890   0.02018   0.0024   0.2226   1.0000
   5.000   0.6893   0.03027   0.02150   0.0042   0.2200   1.0000
   5.250   0.6999   0.03132   0.02283   0.0064   0.2171   1.0000
   5.500   0.7153   0.03266   0.02438   0.0077   0.2137   1.0000
   5.750   0.7337   0.03400   0.02583   0.0085   0.2105   1.0000
   6.000   0.7545   0.03523   0.02710   0.0091   0.2076   1.0000
   6.250   0.7772   0.03648   0.02831   0.0095   0.2053   1.0000
   6.500   0.7982   0.03833   0.03013   0.0099   0.2033   1.0000
   6.750   0.8117   0.04091   0.03295   0.0106   0.2018   1.0000
   7.000   0.8197   0.04383   0.03624   0.0115   0.2006   1.0000
   7.250   0.8232   0.04735   0.04012   0.0122   0.1995   1.0000
   7.500   0.8194   0.05170   0.04481   0.0127   0.1986   1.0000
   7.750   0.8019   0.05762   0.05107   0.0125   0.1989   1.0000
   8.000   0.7823   0.06410   0.05775   0.0114   0.2004   1.0000
   8.250   0.7782   0.06929   0.06301   0.0104   0.2017   1.0000
   8.500   0.7860   0.07355   0.06728   0.0099   0.2024   1.0000
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