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B-29 ROOT AIRFOIL (b29root-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: B-29 ROOT AIRFOIL (b29root-il)
Reynolds number: 50,000
Max Cl/Cd: 8.54 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b29root-il-50000-n5.txt
Download as CSV file: xf-b29root-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: B-29 ROOT AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.4150   0.11908   0.11048  -0.0553   1.0000   0.1240
 -14.250  -0.5667   0.08834   0.07947  -0.0709   1.0000   0.1270
 -14.000  -0.6653   0.07349   0.06422  -0.0769   1.0000   0.1273
 -13.750  -0.7102   0.06695   0.05738  -0.0779   1.0000   0.1280
 -13.500  -0.7077   0.06464   0.05508  -0.0774   1.0000   0.1297
 -13.250  -0.7017   0.06283   0.05330  -0.0768   1.0000   0.1318
 -13.000  -0.7071   0.06033   0.05074  -0.0759   1.0000   0.1338
 -12.750  -0.7168   0.05777   0.04807  -0.0747   1.0000   0.1358
 -12.500  -0.7291   0.05536   0.04554  -0.0729   1.0000   0.1378
 -12.250  -0.7437   0.05326   0.04330  -0.0704   1.0000   0.1397
 -12.000  -0.7562   0.05183   0.04180  -0.0672   1.0000   0.1415
 -11.750  -0.7576   0.05147   0.04160  -0.0640   1.0000   0.1434
 -11.500  -0.7373   0.05016   0.04029  -0.0649   0.9875   0.1471
 -11.250  -0.7133   0.04821   0.03814  -0.0673   0.9734   0.1521
 -11.000  -0.6800   0.04668   0.03656  -0.0701   0.9626   0.1578
 -10.750  -0.6476   0.04528   0.03512  -0.0726   0.9515   0.1641
 -10.500  -0.6164   0.04376   0.03349  -0.0752   0.9414   0.1714
 -10.250  -0.5823   0.04243   0.03217  -0.0779   0.9323   0.1797
 -10.000  -0.5543   0.04115   0.03086  -0.0797   0.9210   0.1884
  -9.750  -0.5255   0.03972   0.02933  -0.0820   0.9121   0.1999
  -9.500  -0.5045   0.03868   0.02842  -0.0825   0.8998   0.2105
  -9.250  -0.4832   0.03754   0.02731  -0.0832   0.8896   0.2234
  -9.000  -0.4677   0.03654   0.02635  -0.0828   0.8779   0.2380
  -8.750  -0.4553   0.03567   0.02552  -0.0817   0.8669   0.2541
  -8.500  -0.4439   0.03488   0.02479  -0.0803   0.8565   0.2726
  -8.250  -0.4367   0.03430   0.02427  -0.0780   0.8457   0.2916
  -8.000  -0.4280   0.03377   0.02377  -0.0757   0.8359   0.3130
  -7.750  -0.4231   0.03342   0.02344  -0.0726   0.8257   0.3332
  -7.500  -0.4166   0.03310   0.02312  -0.0695   0.8165   0.3541
  -7.250  -0.4106   0.03289   0.02290  -0.0662   0.8078   0.3739
  -7.000  -0.4065   0.03279   0.02280  -0.0625   0.7982   0.3920
  -6.750  -0.3953   0.03262   0.02257  -0.0597   0.7915   0.4113
  -6.500  -0.3973   0.03272   0.02266  -0.0550   0.7815   0.4264
  -6.250  -0.3916   0.03263   0.02249  -0.0513   0.7740   0.4435
  -6.000  -0.3777   0.03263   0.02245  -0.0488   0.7675   0.4606
  -5.750  -0.3658   0.03290   0.02276  -0.0460   0.7585   0.4754
  -5.500  -0.3479   0.03290   0.02272  -0.0440   0.7522   0.4919
  -5.250  -0.3352   0.03292   0.02266  -0.0414   0.7460   0.5079
  -5.000  -0.3319   0.03314   0.02287  -0.0374   0.7372   0.5224
  -4.750  -0.3055   0.03332   0.02306  -0.0365   0.7314   0.5394
  -4.500  -0.2751   0.03345   0.02313  -0.0361   0.7271   0.5575
  -4.250  -0.2760   0.03393   0.02366  -0.0316   0.7175   0.5712
  -4.000  -0.2658   0.03394   0.02361  -0.0285   0.7113   0.5875
  -3.750  -0.2198   0.03414   0.02375  -0.0306   0.7072   0.6008
  -3.500  -0.2157   0.03445   0.02407  -0.0271   0.6991   0.6122
  -3.250  -0.1987   0.03463   0.02420  -0.0253   0.6923   0.6243
  -3.000  -0.1645   0.03464   0.02414  -0.0261   0.6878   0.6354
  -2.750  -0.1551   0.03451   0.02392  -0.0231   0.6828   0.6494
  -2.500  -0.1336   0.03529   0.02476  -0.0223   0.6743   0.6582
  -2.250  -0.1215   0.03524   0.02464  -0.0198   0.6688   0.6719
  -2.000  -0.0720   0.03540   0.02472  -0.0228   0.6653   0.6817
  -1.750  -0.0748   0.03595   0.02529  -0.0184   0.6575   0.6948
  -1.500  -0.0535   0.03644   0.02577  -0.0175   0.6509   0.7062
  -1.250  -0.0205   0.03655   0.02582  -0.0182   0.6466   0.7179
  -1.000   0.0107   0.03648   0.02564  -0.0183   0.6435   0.7315
  -0.750   0.0130   0.03782   0.02708  -0.0153   0.6341   0.7417
  -0.500   0.0266   0.03812   0.02735  -0.0131   0.6286   0.7563
  -0.250   0.0792   0.03837   0.02752  -0.0168   0.6252   0.7651
   0.000   0.1146   0.03827   0.02732  -0.0176   0.6225   0.7779
   0.250   0.0894   0.04017   0.02936  -0.0110   0.6113   0.7930
   0.500   0.1332   0.04059   0.02972  -0.0137   0.6073   0.8022
   0.750   0.1609   0.04058   0.02964  -0.0134   0.6041   0.8166
   1.250   0.1864   0.04326   0.03237  -0.0111   0.5896   0.8401
   1.500   0.2314   0.04358   0.03264  -0.0140   0.5863   0.8493
   1.750   0.2722   0.04357   0.03257  -0.0159   0.5837   0.8603
   2.250   0.2790   0.04683   0.03590  -0.0122   0.5680   0.8876
   2.500   0.3186   0.04693   0.03596  -0.0142   0.5653   0.8986
   2.750   0.3696   0.04683   0.03581  -0.0179   0.5633   0.9073
   3.250   0.3654   0.05087   0.03995  -0.0146   0.5465   0.9364
   3.500   0.4097   0.05071   0.03975  -0.0172   0.5445   0.9464
   4.000   0.4251   0.05532   0.04446  -0.0191   0.5280   0.9710
   4.250   0.4715   0.05519   0.04431  -0.0223   0.5258   0.9796
   5.250   0.4651   0.06305   0.05220  -0.0188   0.4984   1.0000
   5.500   0.4568   0.06430   0.05341  -0.0155   0.4929   1.0000
   5.750   0.4663   0.06462   0.05368  -0.0133   0.4895   1.0000
   6.000   0.4841   0.06457   0.05360  -0.0116   0.4871   1.0000
   6.250   0.4358   0.06847   0.05747  -0.0063   0.4768   1.0000
   6.500   0.4413   0.06934   0.05831  -0.0042   0.4727   1.0000
   6.750   0.4575   0.06960   0.05854  -0.0026   0.4697   1.0000
   7.250   0.4333   0.07393   0.06282   0.0028   0.4566   1.0000
   7.500   0.4453   0.07469   0.06357   0.0043   0.4530   1.0000
   7.750   0.4650   0.07501   0.06387   0.0055   0.4504   1.0000
   8.000   0.4394   0.07836   0.06722   0.0082   0.4415   1.0000
   8.250   0.4457   0.07967   0.06852   0.0097   0.4367   1.0000
   8.500   0.4631   0.08026   0.06910   0.0108   0.4333   1.0000
   9.000   0.4554   0.08453   0.07339   0.0139   0.4204   1.0000
   9.250   0.4708   0.08534   0.07421   0.0150   0.4163   1.0000
   9.500   0.4953   0.08547   0.07434   0.0159   0.4135   1.0000
   9.750   0.4724   0.08913   0.07802   0.0174   0.4032   1.0000
  10.000   0.4886   0.08986   0.07877   0.0184   0.3986   1.0000
  10.250   0.5150   0.08979   0.07871   0.0192   0.3955   1.0000
  10.500   0.4937   0.09350   0.08246   0.0204   0.3846   1.0000
  10.750   0.5137   0.09389   0.08287   0.0213   0.3801   1.0000
  11.250   0.5189   0.09766   0.08671   0.0230   0.3652   1.0000
  11.500   0.5440   0.09755   0.08662   0.0239   0.3614   1.0000
  11.750   0.5299   0.10105   0.09016   0.0245   0.3508   1.0000
  12.000   0.5498   0.10135   0.09051   0.0253   0.3457   1.0000
  12.250   0.5457   0.10406   0.09326   0.0258   0.3367   1.0000
  12.500   0.5590   0.10497   0.09422   0.0265   0.3301   1.0000
  12.750   0.5773   0.10537   0.09465   0.0274   0.3249   1.0000
  13.000   0.5711   0.10834   0.09767   0.0276   0.3142   1.0000
  13.250   0.5982   0.10762   0.09700   0.0286   0.3103   1.0000
  13.500   0.5846   0.11156   0.10099   0.0285   0.2981   1.0000
  13.750   0.6116   0.11072   0.10020   0.0296   0.2940   1.0000
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