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 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il)
Reynolds number: 100,000
Max Cl/Cd: 30.35 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b737a-il-100000-n5.txt
Download as CSV file: xf-b737a-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -1.0090   0.07700   0.07044  -0.0133   1.0000   0.0782
 -14.750  -1.0716   0.06295   0.05605  -0.0225   1.0000   0.0766
 -14.500  -1.1007   0.05529   0.04804  -0.0269   1.0000   0.0819
 -14.250  -1.1143   0.05021   0.04256  -0.0293   1.0000   0.0887
 -14.000  -1.1201   0.04657   0.03865  -0.0306   1.0000   0.0936
 -13.750  -1.1221   0.04361   0.03542  -0.0313   1.0000   0.0978
 -13.500  -1.1214   0.04123   0.03287  -0.0315   1.0000   0.1013
 -13.250  -1.1188   0.03914   0.03057  -0.0313   1.0000   0.1048
 -13.000  -1.1148   0.03743   0.02877  -0.0307   1.0000   0.1083
 -12.750  -1.1095   0.03588   0.02701  -0.0297   1.0000   0.1120
 -12.500  -1.1016   0.03468   0.02581  -0.0283   1.0000   0.1150
 -12.250  -1.0918   0.03358   0.02457  -0.0269   1.0000   0.1182
 -12.000  -1.0789   0.03255   0.02346  -0.0256   1.0000   0.1211
 -11.750  -1.0647   0.03163   0.02251  -0.0245   1.0000   0.1245
 -11.500  -1.0487   0.03072   0.02145  -0.0234   1.0000   0.1279
 -11.250  -1.0318   0.02993   0.02069  -0.0223   1.0000   0.1306
 -11.000  -1.0136   0.02919   0.01992  -0.0212   1.0000   0.1334
 -10.750  -0.9942   0.02845   0.01907  -0.0203   1.0000   0.1363
 -10.500  -0.9746   0.02779   0.01841  -0.0193   1.0000   0.1387
 -10.250  -0.9544   0.02720   0.01782  -0.0184   1.0000   0.1415
 -10.000  -0.9333   0.02660   0.01715  -0.0175   1.0000   0.1445
  -9.750  -0.9118   0.02602   0.01654  -0.0166   1.0000   0.1470
  -9.500  -0.8901   0.02551   0.01605  -0.0157   1.0000   0.1492
  -9.250  -0.8678   0.02501   0.01551  -0.0149   1.0000   0.1516
  -9.000  -0.8452   0.02449   0.01495  -0.0140   1.0000   0.1542
  -8.750  -0.8225   0.02400   0.01444  -0.0132   1.0000   0.1568
  -8.500  -0.7999   0.02358   0.01405  -0.0123   1.0000   0.1594
  -8.250  -0.7770   0.02315   0.01361  -0.0115   1.0000   0.1625
  -8.000  -0.7538   0.02270   0.01311  -0.0106   1.0000   0.1659
  -7.750  -0.7313   0.02233   0.01279  -0.0097   1.0000   0.1689
  -7.500  -0.7085   0.02194   0.01242  -0.0087   1.0000   0.1722
  -7.250  -0.6859   0.02152   0.01199  -0.0077   1.0000   0.1755
  -7.000  -0.6636   0.02110   0.01159  -0.0067   1.0000   0.1784
  -6.750  -0.6421   0.02071   0.01126  -0.0056   1.0000   0.1810
  -6.500  -0.6210   0.02035   0.01093  -0.0044   1.0000   0.1842
  -6.250  -0.6006   0.02000   0.01060  -0.0031   1.0000   0.1884
  -6.000  -0.5815   0.01971   0.01036  -0.0018   0.9996   0.1924
  -5.750  -0.5415   0.01937   0.01006  -0.0043   0.9858   0.1990
  -5.500  -0.5026   0.01905   0.00976  -0.0065   0.9713   0.2066
  -5.250  -0.4645   0.01875   0.00950  -0.0085   0.9552   0.2146
  -5.000  -0.4233   0.01845   0.00920  -0.0108   0.9345   0.2232
  -4.750  -0.3832   0.01815   0.00890  -0.0127   0.9074   0.2320
  -4.500  -0.3446   0.01789   0.00859  -0.0141   0.8803   0.2403
  -4.250  -0.3124   0.01768   0.00835  -0.0144   0.8567   0.2479
  -4.000  -0.2837   0.01758   0.00814  -0.0139   0.8327   0.2555
  -3.750  -0.2578   0.01741   0.00798  -0.0129   0.8075   0.2629
  -3.500  -0.2319   0.01729   0.00781  -0.0119   0.7837   0.2696
  -3.250  -0.2056   0.01720   0.00765  -0.0111   0.7635   0.2762
  -3.000  -0.1802   0.01701   0.00751  -0.0102   0.7437   0.2835
  -2.750  -0.1540   0.01688   0.00736  -0.0093   0.7230   0.2909
  -2.500  -0.1280   0.01676   0.00721  -0.0085   0.7001   0.2973
  -2.250  -0.1026   0.01659   0.00706  -0.0075   0.6741   0.3045
  -2.000  -0.0771   0.01646   0.00690  -0.0066   0.6433   0.3136
  -1.750  -0.0520   0.01634   0.00674  -0.0056   0.6050   0.3234
  -1.500  -0.0275   0.01627   0.00655  -0.0044   0.5518   0.3348
  -1.250  -0.0042   0.01631   0.00636  -0.0032   0.4761   0.3490
  -1.000   0.0182   0.01651   0.00627  -0.0020   0.3985   0.3694
  -0.750   0.0410   0.01663   0.00630  -0.0010   0.3523   0.4031
  -0.500   0.0638   0.01665   0.00642   0.0000   0.3251   0.4567
  -0.250   0.0867   0.01667   0.00668   0.0012   0.3067   0.5248
   0.000   0.1105   0.01682   0.00698   0.0024   0.2930   0.5844
   0.250   0.1352   0.01708   0.00723   0.0034   0.2817   0.6257
   0.500   0.1605   0.01730   0.00749   0.0044   0.2721   0.6563
   0.750   0.1858   0.01757   0.00773   0.0053   0.2635   0.6815
   1.000   0.2110   0.01788   0.00798   0.0062   0.2565   0.7036
   1.250   0.2366   0.01812   0.00825   0.0070   0.2495   0.7242
   1.500   0.2617   0.01840   0.00851   0.0080   0.2432   0.7435
   1.750   0.2865   0.01874   0.00878   0.0089   0.2378   0.7626
   2.000   0.3115   0.01898   0.00909   0.0100   0.2321   0.7828
   2.250   0.3360   0.01923   0.00937   0.0111   0.2267   0.8031
   2.500   0.3602   0.01953   0.00963   0.0123   0.2218   0.8217
   2.750   0.3853   0.01981   0.00996   0.0133   0.2170   0.8383
   3.000   0.4110   0.02006   0.01028   0.0141   0.2117   0.8542
   3.250   0.4370   0.02033   0.01055   0.0148   0.2069   0.8707
   3.500   0.4640   0.02071   0.01085   0.0153   0.2028   0.8882
   3.750   0.4941   0.02102   0.01130   0.0151   0.1980   0.9066
   4.000   0.5279   0.02141   0.01173   0.0142   0.1931   0.9267
   4.250   0.5652   0.02184   0.01213   0.0124   0.1888   0.9476
   4.500   0.6045   0.02239   0.01265   0.0101   0.1848   0.9673
   4.750   0.6435   0.02292   0.01328   0.0077   0.1802   0.9862
   5.000   0.6766   0.02340   0.01377   0.0062   0.1762   1.0000
   5.250   0.6957   0.02382   0.01411   0.0074   0.1735   1.0000
   5.500   0.7176   0.02437   0.01452   0.0081   0.1711   1.0000
   5.750   0.7398   0.02499   0.01529   0.0088   0.1679   1.0000
   6.000   0.7628   0.02564   0.01601   0.0093   0.1650   1.0000
   6.250   0.7863   0.02627   0.01665   0.0098   0.1623   1.0000
   6.500   0.8102   0.02687   0.01722   0.0103   0.1600   1.0000
   6.750   0.8345   0.02750   0.01776   0.0106   0.1581   1.0000
   7.000   0.8569   0.02837   0.01876   0.0112   0.1555   1.0000
   7.250   0.8787   0.02925   0.01980   0.0117   0.1527   1.0000
   7.500   0.9009   0.03002   0.02064   0.0122   0.1501   1.0000
   7.750   0.9238   0.03067   0.02130   0.0127   0.1479   1.0000
   8.000   0.9474   0.03123   0.02180   0.0131   0.1460   1.0000
   8.250   0.9683   0.03215   0.02281   0.0136   0.1438   1.0000
   8.500   0.9862   0.03332   0.02422   0.0144   0.1411   1.0000
   8.750   1.0054   0.03425   0.02527   0.0151   0.1386   1.0000
   9.000   1.0259   0.03492   0.02597   0.0156   0.1365   1.0000
   9.250   1.0480   0.03541   0.02641   0.0161   0.1347   1.0000
   9.500   1.0659   0.03640   0.02749   0.0168   0.1328   1.0000
   9.750   1.0768   0.03801   0.02939   0.0179   0.1303   1.0000
  10.000   1.0899   0.03927   0.03080   0.0188   0.1281   1.0000
  10.250   1.1051   0.04022   0.03183   0.0196   0.1262   1.0000
  10.500   1.1219   0.04097   0.03260   0.0203   0.1247   1.0000
  10.750   1.1414   0.04151   0.03308   0.0209   0.1235   1.0000
  11.000   1.1371   0.04398   0.03587   0.0225   0.1218   1.0000
  11.250   1.1263   0.04678   0.03896   0.0240   0.1203   1.0000
  11.500   1.1129   0.05005   0.04247   0.0245   0.1189   1.0000
  11.750   1.0958   0.05408   0.04672   0.0236   0.1176   1.0000
  12.000   1.0701   0.05964   0.05250   0.0211   0.1165   1.0000
  12.500   1.0976   0.06168   0.05449   0.0209   0.1139   1.0000
  12.750   0.7420   0.13163   0.12524  -0.0227   0.1000   1.0000
  13.000   0.7539   0.13315   0.12677  -0.0232   0.0980   1.0000
<< Back to BOEING 737 ROOT AIRFOIL (b737a-il)

Polar data table (+)

Polar graphs


<< Back to BOEING 737 ROOT AIRFOIL (b737a-il)