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B-29 TIP AIRFOIL (b29tip-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: B-29 TIP AIRFOIL (b29tip-il)
Reynolds number: 200,000
Max Cl/Cd: 68.77 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b29tip-il-200000.txt
Download as CSV file: xf-b29tip-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: B-29 TIP AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4255   0.09774   0.09460  -0.0022   1.0000   0.0459
  -9.250  -0.4226   0.09391   0.09078  -0.0033   1.0000   0.0470
  -9.000  -0.5165   0.09550   0.09216  -0.0056   1.0000   0.0445
  -8.750  -0.5104   0.09224   0.08892  -0.0060   1.0000   0.0455
  -8.500  -0.5078   0.08876   0.08546  -0.0074   1.0000   0.0464
  -8.250  -0.5074   0.08512   0.08187  -0.0094   1.0000   0.0476
  -8.000  -0.5109   0.08127   0.07807  -0.0122   1.0000   0.0485
  -7.750  -0.5154   0.07742   0.07424  -0.0146   1.0000   0.0495
  -7.500  -0.5154   0.07311   0.06991  -0.0177   1.0000   0.0510
  -7.250  -0.5149   0.06834   0.06495  -0.0231   1.0000   0.0538
  -7.000  -0.5128   0.06539   0.06163  -0.0246   1.0000   0.0546
  -6.750  -0.5099   0.05812   0.05441  -0.0252   1.0000   0.0558
  -6.500  -0.4966   0.05494   0.05132  -0.0248   1.0000   0.0571
  -6.250  -0.4834   0.05222   0.04857  -0.0244   1.0000   0.0589
  -6.000  -0.4700   0.04931   0.04558  -0.0243   1.0000   0.0617
  -5.750  -0.4571   0.04920   0.04471  -0.0228   1.0000   0.0679
  -5.500  -0.4430   0.04199   0.03769  -0.0247   0.9879   0.0703
  -5.250  -0.4077   0.03925   0.03495  -0.0281   0.9686   0.0757
  -5.000  -0.3535   0.01985   0.01541  -0.0310   0.9011   0.0853
  -4.750  -0.3381   0.01794   0.01334  -0.0293   0.8845   0.0891
  -4.500  -0.3238   0.01565   0.01062  -0.0274   0.8687   0.0987
  -4.250  -0.3055   0.01396   0.00884  -0.0262   0.8555   0.1028
  -4.000  -0.2774   0.02168   0.01438  -0.0238   0.8751   0.0429
  -3.750  -0.2536   0.02048   0.01289  -0.0225   0.8604   0.0426
  -3.500  -0.2297   0.01837   0.01050  -0.0214   0.8471   0.0433
  -3.250  -0.2053   0.01701   0.00902  -0.0205   0.8344   0.0457
  -3.000  -0.1802   0.01606   0.00796  -0.0196   0.8225   0.0469
  -2.750  -0.1554   0.01524   0.00703  -0.0186   0.8114   0.0487
  -2.500  -0.1307   0.01454   0.00626  -0.0176   0.7996   0.0516
  -2.250  -0.1065   0.01389   0.00554  -0.0166   0.7885   0.0556
  -2.000  -0.0828   0.01334   0.00496  -0.0155   0.7782   0.0675
  -1.750  -0.0622   0.01227   0.00419  -0.0140   0.7689   0.1343
  -1.500  -0.0208   0.00944   0.00427  -0.0163   0.7596   0.8966
  -1.250   0.1227   0.01011   0.00451  -0.0385   0.7507   0.9983
  -1.000   0.1507   0.01009   0.00430  -0.0386   0.7406   1.0000
  -0.750   0.1741   0.01009   0.00418  -0.0379   0.7304   1.0000
  -0.500   0.1974   0.01010   0.00406  -0.0371   0.7211   1.0000
  -0.250   0.2209   0.01013   0.00396  -0.0363   0.7121   1.0000
   0.000   0.2449   0.01016   0.00392  -0.0356   0.7029   1.0000
   0.250   0.2686   0.01021   0.00384  -0.0348   0.6951   1.0000
   0.500   0.2928   0.01024   0.00383  -0.0342   0.6858   1.0000
   0.750   0.3170   0.01030   0.00381  -0.0335   0.6781   1.0000
   1.000   0.3414   0.01035   0.00381  -0.0328   0.6699   1.0000
   1.250   0.3658   0.01043   0.00384  -0.0322   0.6622   1.0000
   1.500   0.3903   0.01050   0.00386  -0.0315   0.6545   1.0000
   1.750   0.4149   0.01059   0.00394  -0.0310   0.6468   1.0000
   2.000   0.4394   0.01068   0.00400  -0.0303   0.6396   1.0000
   2.250   0.4640   0.01079   0.00411  -0.0297   0.6319   1.0000
   2.500   0.4886   0.01089   0.00419  -0.0291   0.6250   1.0000
   2.750   0.5133   0.01102   0.00435  -0.0285   0.6173   1.0000
   3.000   0.5380   0.01114   0.00447  -0.0279   0.6104   1.0000
   3.250   0.5626   0.01129   0.00467  -0.0273   0.6028   1.0000
   3.500   0.5873   0.01143   0.00481  -0.0267   0.5959   1.0000
   3.750   0.6120   0.01159   0.00504  -0.0261   0.5880   1.0000
   4.000   0.6364   0.01169   0.00513  -0.0253   0.5798   1.0000
   4.250   0.6600   0.01167   0.00511  -0.0242   0.5654   1.0000
   4.500   0.6830   0.01160   0.00508  -0.0231   0.5473   1.0000
   4.750   0.7067   0.01162   0.00513  -0.0221   0.5326   1.0000
   5.000   0.7306   0.01170   0.00527  -0.0212   0.5200   1.0000
   5.250   0.7545   0.01178   0.00542  -0.0204   0.5068   1.0000
   5.500   0.7777   0.01179   0.00552  -0.0193   0.4857   1.0000
   5.750   0.7996   0.01178   0.00548  -0.0180   0.4513   1.0000
   6.000   0.8211   0.01194   0.00561  -0.0168   0.4052   1.0000
   6.250   0.8392   0.01254   0.00589  -0.0152   0.3179   1.0000
   6.500   0.8452   0.01474   0.00704  -0.0129   0.1389   1.0000
   6.750   0.8524   0.01693   0.00866  -0.0103   0.0614   1.0000
   7.000   0.8653   0.01833   0.01007  -0.0080   0.0453   1.0000
   7.250   0.8770   0.01973   0.01144  -0.0058   0.0388   1.0000
   7.500   0.8929   0.02068   0.01251  -0.0040   0.0354   1.0000
   7.750   0.9070   0.02183   0.01370  -0.0019   0.0329   1.0000
   8.000   0.9196   0.02327   0.01513   0.0002   0.0311   1.0000
   8.250   0.9335   0.02563   0.01748   0.0023   0.0298   1.0000
   8.500   0.9526   0.02689   0.01889   0.0037   0.0290   1.0000
   8.750   0.9715   0.02824   0.02039   0.0051   0.0279   1.0000
   9.000   0.9898   0.02980   0.02214   0.0065   0.0264   1.0000
   9.250   1.0082   0.03197   0.02453   0.0078   0.0260   1.0000
   9.500   1.0246   0.03459   0.02744   0.0094   0.0260   1.0000
   9.750   1.0370   0.03769   0.03090   0.0112   0.0263   1.0000
  10.000   1.0444   0.04128   0.03488   0.0134   0.0270   1.0000
  10.250   1.0470   0.04521   0.03915   0.0156   0.0280   1.0000
  10.500   1.0452   0.04965   0.04386   0.0177   0.0290   1.0000
  11.750   0.8670   0.06225   0.05809   0.0291   0.0372   1.0000
  12.000   0.8422   0.06813   0.06411   0.0277   0.0376   1.0000
  12.250   0.8160   0.07431   0.07042   0.0253   0.0376   1.0000
  12.500   0.7874   0.08119   0.07744   0.0219   0.0373   1.0000
  12.750   0.7561   0.08928   0.08566   0.0173   0.0369   1.0000
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