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RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 14 10% AIRFOIL (rg1410-il)
Reynolds number: 50,000
Max Cl/Cd: 33.59 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1410-il-50000-n5.txt
Download as CSV file: xf-rg1410-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 10% 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5384   0.09209   0.08477  -0.0338   1.0000   0.0557
  -9.750  -0.5430   0.08679   0.07952  -0.0364   1.0000   0.0554
  -9.500  -0.5513   0.08101   0.07379  -0.0399   1.0000   0.0550
  -9.250  -0.5655   0.07585   0.06867  -0.0424   1.0000   0.0546
  -9.000  -0.5823   0.07154   0.06436  -0.0430   1.0000   0.0543
  -8.750  -0.5978   0.06700   0.05975  -0.0432   1.0000   0.0541
  -8.500  -0.6095   0.06272   0.05534  -0.0428   1.0000   0.0539
  -8.250  -0.6182   0.05854   0.05096  -0.0418   1.0000   0.0539
  -8.000  -0.6239   0.05440   0.04652  -0.0405   1.0000   0.0542
  -7.750  -0.6263   0.05046   0.04216  -0.0388   1.0000   0.0549
  -7.500  -0.6246   0.04681   0.03805  -0.0370   1.0000   0.0563
  -7.000  -0.6021   0.04220   0.03314  -0.0340   1.0000   0.0605
  -6.750  -0.5901   0.03941   0.02996  -0.0323   1.0000   0.0619
  -6.500  -0.5758   0.03678   0.02691  -0.0306   1.0000   0.0637
  -6.250  -0.5592   0.03438   0.02407  -0.0290   1.0000   0.0661
  -6.000  -0.5415   0.03245   0.02183  -0.0276   1.0000   0.0699
  -5.750  -0.5231   0.03103   0.02033  -0.0262   1.0000   0.0744
  -5.500  -0.5027   0.02939   0.01840  -0.0248   1.0000   0.0789
  -5.250  -0.4820   0.02786   0.01668  -0.0234   1.0000   0.0835
  -5.000  -0.4622   0.02676   0.01552  -0.0220   1.0000   0.0920
  -4.750  -0.4422   0.02567   0.01440  -0.0207   1.0000   0.1019
  -4.500  -0.4221   0.02465   0.01335  -0.0193   1.0000   0.1154
  -4.250  -0.4021   0.02373   0.01241  -0.0180   1.0000   0.1349
  -4.000  -0.3823   0.02282   0.01159  -0.0168   1.0000   0.1615
  -3.750  -0.3622   0.02193   0.01087  -0.0158   1.0000   0.1989
  -3.500  -0.3441   0.02106   0.01026  -0.0145   1.0000   0.2476
  -3.250  -0.3268   0.02021   0.00977  -0.0130   1.0000   0.3176
  -3.000  -0.3107   0.01937   0.00944  -0.0112   1.0000   0.4148
  -2.750  -0.2970   0.01860   0.00932  -0.0083   1.0000   0.5441
  -2.500  -0.2839   0.01825   0.00968  -0.0038   1.0000   0.6989
  -2.250  -0.2644   0.01837   0.00991  -0.0007   1.0000   0.8265
  -2.000  -0.2207   0.01863   0.01000  -0.0024   1.0000   0.9160
  -1.750  -0.1304   0.01891   0.00985  -0.0138   1.0000   0.9830
  -1.500  -0.0972   0.01892   0.00963  -0.0161   1.0000   1.0000
  -1.250  -0.0900   0.01893   0.00949  -0.0137   0.9987   1.0000
  -1.000  -0.0463   0.01915   0.00949  -0.0178   0.9865   1.0000
  -0.750  -0.0046   0.01933   0.00948  -0.0214   0.9739   1.0000
  -0.500   0.0358   0.01948   0.00948  -0.0246   0.9607   1.0000
  -0.250   0.0753   0.01961   0.00948  -0.0274   0.9473   1.0000
   0.000   0.1144   0.01971   0.00948  -0.0301   0.9336   1.0000
   0.250   0.1533   0.01979   0.00948  -0.0326   0.9199   1.0000
   0.500   0.1927   0.01984   0.00948  -0.0351   0.9060   1.0000
   0.750   0.2325   0.01985   0.00946  -0.0375   0.8921   1.0000
   1.000   0.2707   0.01983   0.00943  -0.0395   0.8773   1.0000
   1.250   0.3063   0.01980   0.00940  -0.0408   0.8616   1.0000
   1.500   0.3404   0.01976   0.00938  -0.0418   0.8453   1.0000
   1.750   0.3732   0.01973   0.00937  -0.0424   0.8286   1.0000
   2.000   0.4054   0.01969   0.00936  -0.0428   0.8115   1.0000
   2.250   0.4351   0.01968   0.00937  -0.0427   0.7932   1.0000
   2.500   0.4608   0.01973   0.00945  -0.0418   0.7730   1.0000
   2.750   0.4891   0.01974   0.00950  -0.0413   0.7533   1.0000
   3.000   0.5161   0.01978   0.00957  -0.0406   0.7328   1.0000
   3.250   0.5411   0.01986   0.00968  -0.0395   0.7102   1.0000
   3.500   0.5657   0.01992   0.00975  -0.0381   0.6849   1.0000
   3.750   0.5895   0.01997   0.00978  -0.0366   0.6564   1.0000
   4.000   0.6120   0.02008   0.00985  -0.0348   0.6264   1.0000
   4.250   0.6343   0.02026   0.01003  -0.0332   0.5972   1.0000
   4.500   0.6568   0.02051   0.01027  -0.0317   0.5699   1.0000
   4.750   0.6785   0.02081   0.01054  -0.0301   0.5412   1.0000
   5.000   0.6993   0.02115   0.01088  -0.0285   0.5108   1.0000
   5.250   0.7191   0.02155   0.01125  -0.0267   0.4775   1.0000
   5.500   0.7381   0.02199   0.01166  -0.0248   0.4421   1.0000
   5.750   0.7560   0.02251   0.01209  -0.0229   0.4044   1.0000
   6.000   0.7733   0.02313   0.01260  -0.0210   0.3663   1.0000
   6.250   0.7901   0.02385   0.01322  -0.0192   0.3281   1.0000
   6.500   0.8067   0.02468   0.01395  -0.0174   0.2934   1.0000
   6.750   0.8232   0.02561   0.01475  -0.0158   0.2623   1.0000
   7.000   0.8402   0.02662   0.01568  -0.0143   0.2348   1.0000
   7.250   0.8575   0.02768   0.01671  -0.0129   0.2108   1.0000
   7.500   0.8746   0.02881   0.01777  -0.0115   0.1915   1.0000
   7.750   0.8924   0.03002   0.01900  -0.0102   0.1744   1.0000
   8.000   0.9102   0.03129   0.02030  -0.0090   0.1590   1.0000
   8.250   0.9289   0.03267   0.02168  -0.0079   0.1464   1.0000
   8.500   0.9468   0.03407   0.02312  -0.0068   0.1343   1.0000
   8.750   0.9653   0.03557   0.02485  -0.0057   0.1236   1.0000
   9.000   0.9832   0.03718   0.02662  -0.0046   0.1144   1.0000
   9.250   0.9997   0.03864   0.02810  -0.0035   0.1065   1.0000
   9.500   1.0157   0.04060   0.03044  -0.0022   0.0992   1.0000
   9.750   1.0316   0.04219   0.03195  -0.0012   0.0931   1.0000
  10.000   1.0413   0.04445   0.03471   0.0006   0.0869   1.0000
  10.250   1.0544   0.04650   0.03689   0.0018   0.0825   1.0000
  10.500   1.0629   0.04898   0.03960   0.0033   0.0784   1.0000
  10.750   1.0627   0.05173   0.04276   0.0054   0.0744   1.0000
  11.000   1.0637   0.05398   0.04522   0.0075   0.0709   1.0000
  11.250   1.0708   0.05635   0.04762   0.0088   0.0683   1.0000
  11.500   1.0588   0.05981   0.05141   0.0109   0.0668   1.0000
  11.750   1.0399   0.06380   0.05577   0.0124   0.0657   1.0000
  12.000   1.0191   0.06837   0.06062   0.0126   0.0651   1.0000
  12.250   0.9954   0.07375   0.06625   0.0114   0.0649   1.0000
  12.500   0.9686   0.08032   0.07301   0.0086   0.0652   1.0000
  12.750   0.9396   0.08827   0.08107   0.0041   0.0659   1.0000
  13.000   0.9086   0.09787   0.09076  -0.0019   0.0666   1.0000
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