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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 500,000
Max Cl/Cd: 67.79 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg14a147-il-500000-n5.txt
Download as CSV file: xf-rg14a147-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5272   0.08306   0.08084  -0.0150   1.0000   0.0053
  -8.250  -0.5317   0.07855   0.07637  -0.0174   1.0000   0.0051
  -8.000  -0.5510   0.07121   0.06909  -0.0226   1.0000   0.0044
  -7.750  -0.5433   0.06968   0.06755  -0.0240   1.0000   0.0053
  -7.500  -0.5417   0.06519   0.06304  -0.0272   1.0000   0.0057
  -7.250  -0.5412   0.05957   0.05735  -0.0301   1.0000   0.0055
  -7.000  -0.5359   0.05501   0.05270  -0.0316   1.0000   0.0060
  -6.750  -0.5299   0.05009   0.04765  -0.0324   1.0000   0.0062
  -6.500  -0.5232   0.04489   0.04226  -0.0324   1.0000   0.0060
  -6.250  -0.5147   0.03984   0.03697  -0.0317   1.0000   0.0059
  -6.000  -0.5055   0.03439   0.03120  -0.0303   1.0000   0.0055
  -5.750  -0.4956   0.02816   0.02449  -0.0280   1.0000   0.0051
  -5.500  -0.4797   0.02174   0.01735  -0.0261   0.9994   0.0046
  -5.250  -0.4498   0.01803   0.01305  -0.0267   0.9970   0.0044
  -5.000  -0.4184   0.01585   0.01043  -0.0275   0.9947   0.0044
  -4.750  -0.3878   0.01415   0.00844  -0.0281   0.9921   0.0045
  -4.500  -0.3571   0.01287   0.00697  -0.0288   0.9889   0.0046
  -4.250  -0.3253   0.01185   0.00581  -0.0297   0.9857   0.0049
  -4.000  -0.2921   0.01102   0.00487  -0.0309   0.9829   0.0054
  -3.750  -0.2614   0.01037   0.00413  -0.0315   0.9786   0.0065
  -3.500  -0.2301   0.00989   0.00357  -0.0322   0.9736   0.0080
  -3.250  -0.1965   0.00938   0.00302  -0.0335   0.9697   0.0115
  -3.000  -0.1664   0.00903   0.00256  -0.0339   0.9628   0.0150
  -2.750  -0.1336   0.00859   0.00219  -0.0351   0.9567   0.0349
  -2.500  -0.1027   0.00822   0.00194  -0.0358   0.9482   0.0702
  -2.250  -0.0699   0.00782   0.00172  -0.0370   0.9395   0.1266
  -2.000  -0.0381   0.00725   0.00152  -0.0382   0.9284   0.2364
  -1.750  -0.0079   0.00675   0.00136  -0.0389   0.9139   0.3467
  -1.500   0.0210   0.00642   0.00120  -0.0393   0.8964   0.4277
  -1.250   0.0474   0.00597   0.00108  -0.0390   0.8764   0.5476
  -1.000   0.0697   0.00541   0.00105  -0.0378   0.8538   0.7150
  -0.750   0.0929   0.00527   0.00108  -0.0364   0.8298   0.8036
  -0.500   0.1175   0.00528   0.00107  -0.0354   0.8036   0.8386
  -0.250   0.1423   0.00533   0.00104  -0.0344   0.7771   0.8622
   0.000   0.1668   0.00540   0.00104  -0.0334   0.7548   0.8837
   0.250   0.1917   0.00547   0.00105  -0.0325   0.7349   0.9019
   0.500   0.2168   0.00554   0.00107  -0.0317   0.7126   0.9189
   0.750   0.2428   0.00562   0.00108  -0.0310   0.6818   0.9353
   1.000   0.2703   0.00575   0.00109  -0.0308   0.6488   0.9502
   1.250   0.3011   0.00590   0.00112  -0.0314   0.6176   0.9640
   1.500   0.3344   0.00607   0.00116  -0.0326   0.5832   0.9755
   1.750   0.3679   0.00626   0.00122  -0.0339   0.5461   0.9846
   2.000   0.4016   0.00648   0.00129  -0.0353   0.5059   0.9915
   2.250   0.4344   0.00671   0.00136  -0.0366   0.4656   0.9973
   2.500   0.4616   0.00695   0.00146  -0.0367   0.4270   1.0000
   2.750   0.4840   0.00720   0.00160  -0.0357   0.3896   1.0000
   3.000   0.5066   0.00750   0.00174  -0.0347   0.3480   1.0000
   3.250   0.5297   0.00782   0.00190  -0.0339   0.3049   1.0000
   3.500   0.5532   0.00816   0.00208  -0.0332   0.2628   1.0000
   3.750   0.5757   0.00868   0.00232  -0.0324   0.1982   1.0000
   4.250   0.6222   0.00970   0.00292  -0.0311   0.0982   1.0000
   4.500   0.6464   0.01011   0.00322  -0.0306   0.0706   1.0000
   4.750   0.6707   0.01054   0.00355  -0.0301   0.0468   1.0000
   5.000   0.6951   0.01098   0.00392  -0.0296   0.0281   1.0000
   5.250   0.7199   0.01139   0.00432  -0.0291   0.0200   1.0000
   5.500   0.7444   0.01185   0.00480  -0.0285   0.0162   1.0000
   5.750   0.7681   0.01248   0.00558  -0.0277   0.0140   1.0000
   6.000   0.7924   0.01299   0.00617  -0.0271   0.0134   1.0000
   6.250   0.8177   0.01327   0.00654  -0.0268   0.0118   1.0000
   6.500   0.8425   0.01363   0.00696  -0.0264   0.0100   1.0000
   6.750   0.8662   0.01420   0.00758  -0.0258   0.0087   1.0000
   7.000   0.8882   0.01506   0.00857  -0.0250   0.0072   1.0000
   7.250   0.9120   0.01559   0.00920  -0.0244   0.0062   1.0000
   7.500   0.9346   0.01634   0.01005  -0.0236   0.0049   1.0000
   7.750   0.9582   0.01686   0.01063  -0.0231   0.0041   1.0000
   8.000   0.9779   0.01804   0.01192  -0.0220   0.0031   1.0000
   8.250   0.9992   0.01897   0.01304  -0.0211   0.0029   1.0000
   8.500   1.0194   0.02006   0.01431  -0.0201   0.0026   1.0000
   8.750   1.0379   0.02147   0.01593  -0.0188   0.0024   1.0000
   9.000   1.0559   0.02291   0.01759  -0.0176   0.0023   1.0000
   9.250   1.0732   0.02440   0.01930  -0.0163   0.0020   1.0000
   9.500   1.0885   0.02614   0.02129  -0.0149   0.0019   1.0000
   9.750   1.1035   0.02774   0.02312  -0.0136   0.0017   1.0000
  10.000   1.1148   0.02978   0.02543  -0.0119   0.0017   1.0000
  10.250   1.1263   0.03149   0.02735  -0.0104   0.0015   1.0000
  10.500   1.1294   0.03415   0.03032  -0.0081   0.0015   1.0000
  10.750   1.1259   0.03717   0.03367  -0.0054   0.0015   1.0000
  11.000   1.1138   0.04005   0.03680  -0.0017   0.0014   1.0000
  11.250   1.0981   0.04330   0.04030   0.0009   0.0014   1.0000
  11.500   1.0772   0.04755   0.04477   0.0017   0.0014   1.0000
  11.750   1.0589   0.05251   0.04993   0.0002   0.0014   1.0000
  12.000   1.0377   0.05929   0.05691  -0.0040   0.0014   1.0000
  12.250   1.0176   0.06793   0.06571  -0.0107   0.0014   1.0000
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