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BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BOEING 103 AIRFOIL (boe103-il)
Reynolds number: 100,000
Max Cl/Cd: 53.11 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-boe103-il-100000.txt
Download as CSV file: xf-boe103-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 103 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3449   0.10209   0.09707  -0.0363   1.0000   0.1293
  -9.000  -0.3721   0.10028   0.09541  -0.0385   1.0000   0.1336
  -8.750  -0.4203   0.09939   0.09475  -0.0393   1.0000   0.1345
  -8.500  -0.3928   0.09409   0.08943  -0.0367   1.0000   0.1367
  -8.250  -0.3773   0.09146   0.08681  -0.0338   1.0000   0.1397
  -8.000  -0.3852   0.08962   0.08505  -0.0313   1.0000   0.1429
  -7.750  -0.4085   0.08821   0.08376  -0.0284   1.0000   0.1453
  -7.500  -0.4401   0.08677   0.08245  -0.0259   1.0000   0.1471
  -7.250  -0.5107   0.08453   0.08015  -0.0314   1.0000   0.1504
  -7.000  -0.5022   0.08025   0.07601  -0.0282   1.0000   0.1520
  -6.750  -0.4899   0.07841   0.07426  -0.0234   1.0000   0.1545
  -6.500  -0.4906   0.07649   0.07238  -0.0209   1.0000   0.1586
  -6.250  -0.5188   0.07203   0.06766  -0.0265   1.0000   0.1678
  -6.000  -0.5087   0.06966   0.06547  -0.0225   1.0000   0.1703
  -5.750  -0.4863   0.06498   0.06051  -0.0299   0.9942   0.1849
  -5.500  -0.4545   0.04657   0.04055  -0.0417   0.9881   0.1068
  -5.250  -0.4163   0.03977   0.03252  -0.0453   0.9835   0.0917
  -5.000  -0.3829   0.03662   0.02900  -0.0474   0.9772   0.0910
  -4.750  -0.3434   0.03365   0.02564  -0.0504   0.9723   0.0901
  -4.500  -0.3078   0.03149   0.02306  -0.0522   0.9657   0.0901
  -4.250  -0.2671   0.02983   0.02096  -0.0548   0.9599   0.0920
  -4.000  -0.2313   0.02839   0.01946  -0.0568   0.9533   0.0950
  -3.750  -0.1918   0.02725   0.01819  -0.0590   0.9468   0.0976
  -3.500  -0.1531   0.02630   0.01710  -0.0610   0.9405   0.1014
  -3.250  -0.1168   0.02541   0.01614  -0.0626   0.9331   0.1070
  -3.000  -0.0738   0.02472   0.01550  -0.0654   0.9279   0.1178
  -2.750  -0.0444   0.02403   0.01494  -0.0658   0.9187   0.1308
  -2.500  -0.0016   0.02269   0.01404  -0.0687   0.9142   0.1959
  -2.250   0.0245   0.02170   0.01371  -0.0689   0.9049   0.3064
  -2.000   0.0585   0.02035   0.01375  -0.0698   0.8997   0.6063
  -1.750   0.0770   0.02004   0.01410  -0.0661   0.8911   0.8059
  -1.500   0.2093   0.01982   0.01380  -0.0835   0.8980   1.0000
  -1.250   0.2300   0.01984   0.01364  -0.0827   0.8853   1.0000
  -1.000   0.2659   0.01967   0.01327  -0.0842   0.8749   1.0000
  -0.750   0.3162   0.01917   0.01258  -0.0879   0.8673   1.0000
  -0.500   0.3430   0.01906   0.01233  -0.0875   0.8550   1.0000
  -0.250   0.3900   0.01861   0.01173  -0.0904   0.8493   1.0000
   0.000   0.4087   0.01874   0.01176  -0.0887   0.8366   1.0000
   0.250   0.4351   0.01873   0.01165  -0.0882   0.8262   1.0000
   0.500   0.4714   0.01845   0.01127  -0.0892   0.8183   1.0000
   0.750   0.4925   0.01857   0.01131  -0.0877   0.8062   1.0000
   1.000   0.5260   0.01835   0.01100  -0.0881   0.7978   1.0000
   1.250   0.5522   0.01831   0.01090  -0.0873   0.7868   1.0000
   1.500   0.5755   0.01837   0.01091  -0.0861   0.7748   1.0000
   1.750   0.6072   0.01818   0.01064  -0.0862   0.7653   1.0000
   2.000   0.6346   0.01810   0.01050  -0.0855   0.7537   1.0000
   2.250   0.6580   0.01815   0.01052  -0.0842   0.7406   1.0000
   2.500   0.6842   0.01813   0.01045  -0.0834   0.7281   1.0000
   2.750   0.7131   0.01801   0.01027  -0.0829   0.7159   1.0000
   3.000   0.7435   0.01785   0.01003  -0.0826   0.7035   1.0000
   3.250   0.7681   0.01788   0.01002  -0.0815   0.6884   1.0000
   3.500   0.7935   0.01788   0.00997  -0.0805   0.6726   1.0000
   3.750   0.8199   0.01783   0.00985  -0.0795   0.6557   1.0000
   4.000   0.8436   0.01785   0.00980  -0.0781   0.6366   1.0000
   4.250   0.8658   0.01789   0.00978  -0.0765   0.6153   1.0000
   4.500   0.8897   0.01787   0.00965  -0.0751   0.5936   1.0000
   4.750   0.9122   0.01793   0.00960  -0.0736   0.5714   1.0000
   5.000   0.9328   0.01809   0.00971  -0.0719   0.5489   1.0000
   5.250   0.9552   0.01830   0.00985  -0.0706   0.5288   1.0000
   5.500   0.9779   0.01856   0.01001  -0.0694   0.5098   1.0000
   5.750   0.9981   0.01888   0.01030  -0.0678   0.4894   1.0000
   6.000   1.0185   0.01921   0.01060  -0.0663   0.4692   1.0000
   6.250   1.0389   0.01956   0.01088  -0.0649   0.4494   1.0000
   6.500   1.0592   0.01995   0.01116  -0.0634   0.4300   1.0000
   6.750   1.0774   0.02041   0.01159  -0.0617   0.4091   1.0000
   7.000   1.0955   0.02091   0.01204  -0.0600   0.3884   1.0000
   7.250   1.1135   0.02149   0.01249  -0.0583   0.3679   1.0000
   7.500   1.1296   0.02215   0.01309  -0.0563   0.3457   1.0000
   7.750   1.1446   0.02291   0.01374  -0.0542   0.3224   1.0000
   8.000   1.1583   0.02379   0.01452  -0.0520   0.2983   1.0000
   8.250   1.1712   0.02473   0.01534  -0.0498   0.2749   1.0000
   8.500   1.1860   0.02577   0.01617  -0.0479   0.2552   1.0000
   8.750   1.2011   0.02677   0.01711  -0.0460   0.2388   1.0000
   9.000   1.2184   0.02775   0.01802  -0.0446   0.2259   1.0000
   9.250   1.2357   0.02875   0.01907  -0.0432   0.2152   1.0000
   9.500   1.2571   0.02987   0.02015  -0.0425   0.2071   1.0000
   9.750   1.2772   0.03091   0.02122  -0.0416   0.1997   1.0000
  10.000   1.2992   0.03208   0.02238  -0.0411   0.1932   1.0000
  10.250   1.3150   0.03309   0.02350  -0.0396   0.1865   1.0000
  10.500   1.3388   0.03425   0.02453  -0.0395   0.1801   1.0000
  10.750   1.3498   0.03535   0.02589  -0.0373   0.1748   1.0000
  11.000   1.3691   0.03642   0.02696  -0.0365   0.1695   1.0000
  11.250   1.3934   0.03792   0.02847  -0.0366   0.1650   1.0000
  11.500   1.4034   0.03929   0.03013  -0.0344   0.1613   1.0000
  11.750   1.4179   0.04065   0.03163  -0.0330   0.1575   1.0000
  12.000   1.4522   0.04229   0.03307  -0.0347   0.1522   1.0000
  12.250   1.4492   0.04369   0.03485  -0.0309   0.1495   1.0000
  12.500   1.4500   0.04518   0.03659  -0.0278   0.1459   1.0000
  12.750   1.4591   0.04639   0.03787  -0.0260   0.1418   1.0000
  13.000   1.4806   0.04804   0.03946  -0.0260   0.1373   1.0000
  13.250   1.4705   0.04992   0.04169  -0.0222   0.1350   1.0000
  13.500   1.4657   0.05191   0.04393  -0.0194   0.1324   1.0000
  13.750   1.4651   0.05376   0.04595  -0.0173   0.1295   1.0000
  14.000   1.5004   0.05482   0.04674  -0.0185   0.1244   1.0000
  14.250   1.4805   0.05742   0.04971  -0.0150   0.1232   1.0000
  14.500   1.4609   0.06051   0.05314  -0.0123   0.1218   1.0000
  14.750   1.4417   0.06400   0.05692  -0.0104   0.1203   1.0000
  15.000   1.4228   0.06783   0.06101  -0.0091   0.1188   1.0000
  15.250   1.4055   0.07181   0.06522  -0.0084   0.1173   1.0000
  15.500   1.3868   0.07623   0.06984  -0.0083   0.1160   1.0000
  15.750   1.3469   0.08349   0.07740  -0.0094   0.1159   1.0000
  16.000   1.3464   0.08631   0.08029  -0.0096   0.1137   1.0000
  16.250   1.3262   0.09191   0.08604  -0.0110   0.1127   1.0000
  16.500   1.3051   0.09814   0.09240  -0.0129   0.1117   1.0000
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