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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 50,000
Max Cl/Cd: 33.93 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14a147-il-50000.txt
Download as CSV file: xf-rg14a147-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5167   0.10089   0.09417   0.0006   1.0000   0.2364
  -8.000  -0.5186   0.09788   0.09125   0.0001   1.0000   0.2477
  -7.750  -0.5191   0.09481   0.08826   0.0001   1.0000   0.2607
  -7.500  -0.5130   0.09127   0.08478   0.0010   1.0000   0.2757
  -7.250  -0.5080   0.08799   0.08156   0.0019   1.0000   0.2916
  -7.000  -0.5144   0.08561   0.07929   0.0028   1.0000   0.3111
  -6.750  -0.5022   0.08195   0.07559   0.0049   1.0000   0.3338
  -6.500  -0.4990   0.07913   0.07285   0.0074   1.0000   0.3637
  -6.250  -0.5072   0.07711   0.07095   0.0093   1.0000   0.3949
  -6.000  -0.4860   0.07330   0.06715   0.0137   1.0000   0.4338
  -5.250  -0.4663   0.04890   0.04153  -0.0296   1.0000   0.1454
  -5.000  -0.4440   0.04354   0.03531  -0.0308   1.0000   0.1209
  -4.750  -0.4241   0.03969   0.03113  -0.0302   1.0000   0.1167
  -4.500  -0.3998   0.03606   0.02656  -0.0295   1.0000   0.1080
  -4.250  -0.3768   0.03273   0.02291  -0.0286   1.0000   0.1054
  -4.000  -0.3518   0.02982   0.01952  -0.0275   1.0000   0.1045
  -3.750  -0.3257   0.02733   0.01652  -0.0262   1.0000   0.1066
  -3.500  -0.3012   0.02533   0.01434  -0.0251   1.0000   0.1195
  -3.250  -0.2751   0.02331   0.01216  -0.0237   1.0000   0.1344
  -3.000  -0.1566   0.01612   0.00842  -0.0316   1.0000   1.0000
  -2.750  -0.1443   0.01583   0.00766  -0.0294   1.0000   1.0000
  -2.500  -0.1314   0.01561   0.00706  -0.0273   1.0000   1.0000
  -2.250  -0.1177   0.01544   0.00656  -0.0251   1.0000   1.0000
  -2.000  -0.1035   0.01532   0.00614  -0.0231   1.0000   1.0000
  -1.750  -0.0888   0.01523   0.00579  -0.0210   1.0000   1.0000
  -1.500  -0.0733   0.01519   0.00550  -0.0191   1.0000   1.0000
  -1.250  -0.0569   0.01518   0.00522  -0.0174   1.0000   1.0000
  -1.000  -0.0397   0.01520   0.00505  -0.0158   1.0000   1.0000
  -0.750  -0.0219   0.01525   0.00493  -0.0144   1.0000   1.0000
  -0.500  -0.0037   0.01533   0.00486  -0.0131   1.0000   1.0000
  -0.250   0.0148   0.01545   0.00485  -0.0119   1.0000   1.0000
   0.000   0.0334   0.01560   0.00486  -0.0108   1.0000   1.0000
   0.250   0.0520   0.01579   0.00495  -0.0097   1.0000   1.0000
   0.500   0.0705   0.01602   0.00511  -0.0087   1.0000   1.0000
   0.750   0.0889   0.01629   0.00533  -0.0078   1.0000   1.0000
   1.000   0.1071   0.01661   0.00561  -0.0070   1.0000   1.0000
   1.250   0.1249   0.01698   0.00597  -0.0063   1.0000   1.0000
   1.500   0.1424   0.01741   0.00640  -0.0056   1.0000   1.0000
   1.750   0.1594   0.01790   0.00690  -0.0051   1.0000   1.0000
   2.000   0.1759   0.01847   0.00750  -0.0047   1.0000   1.0000
   2.250   0.1918   0.01913   0.00820  -0.0044   1.0000   1.0000
   2.500   0.2071   0.01988   0.00900  -0.0042   1.0000   1.0000
   2.750   0.2477   0.02103   0.01035  -0.0091   0.9870   1.0000
   3.000   0.3257   0.02232   0.01194  -0.0201   0.9558   1.0000
   3.250   0.3945   0.02297   0.01294  -0.0285   0.9204   1.0000
   3.500   0.4701   0.02305   0.01358  -0.0366   0.8828   1.0000
   3.750   0.5442   0.02243   0.01349  -0.0426   0.8418   1.0000
   4.000   0.6003   0.02154   0.01304  -0.0440   0.7960   1.0000
   4.250   0.6378   0.02086   0.01271  -0.0418   0.7445   1.0000
   4.500   0.6643   0.02052   0.01247  -0.0379   0.6857   1.0000
   4.750   0.6852   0.02042   0.01232  -0.0334   0.6176   1.0000
   5.000   0.7020   0.02069   0.01234  -0.0288   0.5349   1.0000
   5.250   0.7144   0.02146   0.01265  -0.0241   0.4317   1.0000
   5.500   0.7237   0.02307   0.01344  -0.0199   0.3101   1.0000
   5.750   0.7354   0.02550   0.01510  -0.0169   0.2059   1.0000
   6.000   0.7565   0.02820   0.01743  -0.0152   0.1516   1.0000
   6.250   0.7817   0.03093   0.02008  -0.0141   0.1264   1.0000
   6.500   0.8091   0.03417   0.02345  -0.0133   0.1149   1.0000
   6.750   0.8312   0.03733   0.02732  -0.0116   0.1078   1.0000
   7.000   0.8502   0.04048   0.03074  -0.0104   0.0988   1.0000
   7.250   0.8663   0.04446   0.03538  -0.0087   0.0968   1.0000
   7.500   0.8789   0.04893   0.04043  -0.0072   0.0972   1.0000
   7.750   0.8877   0.05376   0.04577  -0.0058   0.0987   1.0000
   8.000   0.8967   0.05894   0.05125  -0.0048   0.1007   1.0000
   8.250   0.8837   0.06481   0.05792  -0.0042   0.1069   1.0000
   8.500   0.8790   0.07066   0.06402  -0.0043   0.1118   1.0000
   8.750   0.8159   0.06787   0.06175  -0.0005   0.1151   1.0000
   9.000   0.7650   0.07347   0.06752  -0.0019   0.1176   1.0000
   9.250   0.7248   0.08152   0.07554  -0.0075   0.1220   1.0000
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