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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 50,000
Max Cl/Cd: 34.13 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg14a147-il-50000-n5.txt
Download as CSV file: xf-rg14a147-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14A-1.4/7.0 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5234   0.09122   0.08444  -0.0165   1.0000   0.0474
  -8.000  -0.5234   0.08723   0.08052  -0.0181   1.0000   0.0455
  -7.750  -0.5256   0.08281   0.07618  -0.0208   1.0000   0.0437
  -7.500  -0.5264   0.07784   0.07123  -0.0242   1.0000   0.0418
  -7.000  -0.5234   0.06713   0.06023  -0.0311   1.0000   0.0372
  -6.750  -0.5172   0.06307   0.05611  -0.0314   1.0000   0.0365
  -6.500  -0.5101   0.05892   0.05182  -0.0319   1.0000   0.0360
  -6.250  -0.5013   0.05478   0.04748  -0.0322   1.0000   0.0355
  -6.000  -0.4906   0.05067   0.04297  -0.0323   1.0000   0.0350
  -5.750  -0.4778   0.04666   0.03861  -0.0321   1.0000   0.0347
  -5.500  -0.4628   0.04287   0.03442  -0.0315   1.0000   0.0345
  -5.250  -0.4456   0.03929   0.03037  -0.0308   1.0000   0.0345
  -5.000  -0.4264   0.03597   0.02654  -0.0298   1.0000   0.0348
  -4.750  -0.4050   0.03297   0.02298  -0.0287   1.0000   0.0360
  -4.500  -0.3834   0.03045   0.02001  -0.0277   1.0000   0.0394
  -4.250  -0.3616   0.02856   0.01792  -0.0269   1.0000   0.0447
  -4.000  -0.3371   0.02642   0.01538  -0.0255   1.0000   0.0476
  -3.750  -0.3127   0.02449   0.01314  -0.0240   1.0000   0.0511
  -3.500  -0.2898   0.02290   0.01146  -0.0227   1.0000   0.0573
  -3.250  -0.2662   0.02166   0.01007  -0.0216   1.0000   0.0751
  -3.000  -0.2433   0.02018   0.00865  -0.0206   1.0000   0.1039
  -2.750  -0.2238   0.01805   0.00757  -0.0198   1.0000   0.2530
  -2.500  -0.2161   0.01583   0.00720  -0.0152   1.0000   0.6327
  -2.250  -0.1171   0.01544   0.00659  -0.0251   1.0000   1.0000
  -2.000  -0.1029   0.01532   0.00617  -0.0230   1.0000   1.0000
  -1.750  -0.0882   0.01524   0.00582  -0.0210   1.0000   1.0000
  -1.500  -0.0726   0.01519   0.00553  -0.0191   1.0000   1.0000
  -1.250  -0.0562   0.01518   0.00530  -0.0174   1.0000   1.0000
  -1.000  -0.0390   0.01521   0.00505  -0.0158   1.0000   1.0000
  -0.750  -0.0212   0.01526   0.00494  -0.0144   1.0000   1.0000
  -0.500  -0.0030   0.01535   0.00487  -0.0131   1.0000   1.0000
  -0.250   0.0154   0.01547   0.00486  -0.0119   1.0000   1.0000
   0.000   0.0340   0.01563   0.00490  -0.0107   1.0000   1.0000
   0.250   0.0527   0.01582   0.00496  -0.0097   1.0000   1.0000
   0.500   0.0712   0.01605   0.00512  -0.0087   1.0000   1.0000
   0.750   0.1044   0.01638   0.00540  -0.0107   0.9920   1.0000
   1.000   0.1497   0.01672   0.00573  -0.0149   0.9761   1.0000
   1.250   0.1942   0.01700   0.00605  -0.0188   0.9594   1.0000
   1.500   0.2396   0.01723   0.00632  -0.0226   0.9427   1.0000
   1.750   0.2817   0.01737   0.00656  -0.0256   0.9237   1.0000
   2.000   0.3266   0.01746   0.00677  -0.0289   0.9049   1.0000
   2.250   0.3680   0.01749   0.00700  -0.0313   0.8837   1.0000
   2.500   0.4090   0.01748   0.00715  -0.0333   0.8611   1.0000
   2.750   0.4455   0.01747   0.00730  -0.0343   0.8347   1.0000
   3.000   0.4782   0.01749   0.00755  -0.0345   0.8046   1.0000
   3.250   0.5097   0.01751   0.00771  -0.0342   0.7716   1.0000
   3.500   0.5396   0.01758   0.00788  -0.0335   0.7360   1.0000
   3.750   0.5651   0.01776   0.00816  -0.0321   0.6947   1.0000
   4.000   0.5897   0.01796   0.00840  -0.0304   0.6500   1.0000
   4.250   0.6126   0.01825   0.00881  -0.0285   0.6006   1.0000
   4.500   0.6340   0.01864   0.00916  -0.0265   0.5457   1.0000
   4.750   0.6543   0.01917   0.00959  -0.0244   0.4851   1.0000
   5.000   0.6735   0.01985   0.01012  -0.0225   0.4162   1.0000
   5.250   0.6912   0.02075   0.01076  -0.0206   0.3372   1.0000
   5.500   0.7079   0.02197   0.01162  -0.0189   0.2482   1.0000
   5.750   0.7243   0.02367   0.01281  -0.0177   0.1635   1.0000
   6.000   0.7418   0.02559   0.01434  -0.0166   0.1063   1.0000
   6.250   0.7602   0.02752   0.01618  -0.0153   0.0818   1.0000
   6.500   0.7799   0.02948   0.01823  -0.0139   0.0694   1.0000
   6.750   0.7996   0.03127   0.02027  -0.0128   0.0575   1.0000
   7.000   0.8220   0.03327   0.02264  -0.0116   0.0501   1.0000
   7.250   0.8431   0.03584   0.02531  -0.0106   0.0464   1.0000
   7.500   0.8654   0.03898   0.02894  -0.0094   0.0441   1.0000
   7.750   0.8838   0.04254   0.03310  -0.0080   0.0423   1.0000
   8.000   0.8972   0.04645   0.03760  -0.0065   0.0408   1.0000
   8.250   0.9074   0.04961   0.04113  -0.0052   0.0375   1.0000
   8.500   0.9145   0.05292   0.04446  -0.0044   0.0342   1.0000
   8.750   0.9134   0.05695   0.04917  -0.0028   0.0329   1.0000
   9.000   0.9090   0.06130   0.05394  -0.0016   0.0325   1.0000
   9.250   0.8999   0.06574   0.05871  -0.0007   0.0324   1.0000
   9.500   0.8868   0.06994   0.06313  -0.0001   0.0324   1.0000
   9.750   0.8702   0.07427   0.06760  -0.0003   0.0326   1.0000
  10.000   0.8535   0.07925   0.07269  -0.0023   0.0328   1.0000
  10.250   0.8388   0.08491   0.07841  -0.0058   0.0331   1.0000
  10.500   0.8248   0.09161   0.08513  -0.0106   0.0334   1.0000
  10.750   0.8148   0.09849   0.09201  -0.0152   0.0337   1.0000
  11.000   0.8069   0.10557   0.09906  -0.0195   0.0339   1.0000
  11.250   0.8016   0.11226   0.10572  -0.0231   0.0341   1.0000
  11.500   0.7983   0.11856   0.11198  -0.0262   0.0343   1.0000
  12.000   0.6678   0.12935   0.12315  -0.0267   0.0448   1.0000
  12.250   0.6627   0.13428   0.12807  -0.0291   0.0446   1.0000
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