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RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 14 10% AIRFOIL (rg1410-il)
Reynolds number: 100,000
Max Cl/Cd: 46.44 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1410-il-100000-n5.txt
Download as CSV file: xf-rg1410-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5395   0.08913   0.08391  -0.0307   1.0000   0.0325
 -10.000  -0.5504   0.08258   0.07743  -0.0343   1.0000   0.0322
  -9.750  -0.5669   0.07431   0.06922  -0.0398   1.0000   0.0317
  -9.500  -0.5965   0.06482   0.05971  -0.0469   1.0000   0.0310
  -9.250  -0.6262   0.05963   0.05444  -0.0471   1.0000   0.0307
  -9.000  -0.6480   0.05478   0.04939  -0.0461   1.0000   0.0305
  -8.750  -0.6636   0.05022   0.04455  -0.0443   1.0000   0.0305
  -8.500  -0.6721   0.04609   0.04009  -0.0422   1.0000   0.0307
  -8.250  -0.6748   0.04234   0.03595  -0.0399   1.0000   0.0311
  -8.000  -0.6727   0.03891   0.03209  -0.0375   1.0000   0.0317
  -7.750  -0.6660   0.03604   0.02877  -0.0353   1.0000   0.0329
  -7.500  -0.6562   0.03356   0.02572  -0.0330   1.0000   0.0345
  -7.250  -0.6435   0.03126   0.02318  -0.0312   1.0000   0.0357
  -7.000  -0.6280   0.02952   0.02126  -0.0296   1.0000   0.0367
  -6.750  -0.6113   0.02797   0.01951  -0.0280   1.0000   0.0379
  -6.500  -0.5936   0.02655   0.01786  -0.0264   1.0000   0.0395
  -6.250  -0.5752   0.02538   0.01647  -0.0249   1.0000   0.0421
  -6.000  -0.5558   0.02424   0.01506  -0.0234   1.0000   0.0443
  -5.750  -0.5372   0.02290   0.01367  -0.0219   1.0000   0.0460
  -5.500  -0.5184   0.02192   0.01267  -0.0205   1.0000   0.0482
  -5.250  -0.4993   0.02106   0.01173  -0.0190   1.0000   0.0510
  -5.000  -0.4797   0.02033   0.01085  -0.0176   1.0000   0.0552
  -4.750  -0.4610   0.01958   0.01013  -0.0163   1.0000   0.0603
  -4.500  -0.4415   0.01895   0.00943  -0.0149   1.0000   0.0670
  -4.250  -0.4206   0.01827   0.00878  -0.0139   0.9995   0.0755
  -4.000  -0.3849   0.01767   0.00816  -0.0159   0.9940   0.0949
  -3.750  -0.3507   0.01706   0.00769  -0.0177   0.9877   0.1238
  -3.500  -0.3158   0.01648   0.00734  -0.0196   0.9818   0.1682
  -3.250  -0.2832   0.01588   0.00702  -0.0211   0.9746   0.2279
  -3.000  -0.2497   0.01529   0.00675  -0.0227   0.9681   0.3057
  -2.750  -0.2184   0.01469   0.00653  -0.0237   0.9603   0.4009
  -2.500  -0.1881   0.01407   0.00640  -0.0243   0.9528   0.5183
  -2.250  -0.1584   0.01356   0.00647  -0.0239   0.9454   0.6577
  -2.000  -0.1289   0.01348   0.00668  -0.0230   0.9374   0.7708
  -1.750  -0.0945   0.01350   0.00670  -0.0234   0.9302   0.8325
  -1.500  -0.0604   0.01354   0.00668  -0.0237   0.9218   0.8724
  -1.250  -0.0176   0.01357   0.00664  -0.0259   0.9156   0.9034
  -1.000   0.0255   0.01360   0.00657  -0.0283   0.9078   0.9284
  -0.750   0.0772   0.01359   0.00647  -0.0326   0.9013   0.9461
  -0.500   0.1299   0.01356   0.00634  -0.0373   0.8933   0.9606
  -0.250   0.1846   0.01345   0.00615  -0.0425   0.8848   0.9720
   0.000   0.2346   0.01331   0.00596  -0.0468   0.8725   0.9820
   0.250   0.2846   0.01313   0.00572  -0.0512   0.8590   0.9904
   0.500   0.3323   0.01295   0.00550  -0.0552   0.8436   0.9987
   0.750   0.3638   0.01284   0.00533  -0.0558   0.8255   1.0000
   1.000   0.3888   0.01278   0.00522  -0.0552   0.8053   1.0000
   1.250   0.4134   0.01274   0.00513  -0.0544   0.7847   1.0000
   1.500   0.4379   0.01272   0.00506  -0.0536   0.7642   1.0000
   1.750   0.4601   0.01275   0.00504  -0.0523   0.7412   1.0000
   2.000   0.4823   0.01279   0.00500  -0.0510   0.7172   1.0000
   2.250   0.5038   0.01286   0.00500  -0.0495   0.6917   1.0000
   2.500   0.5243   0.01297   0.00503  -0.0478   0.6647   1.0000
   2.750   0.5445   0.01310   0.00507  -0.0461   0.6369   1.0000
   3.000   0.5645   0.01327   0.00515  -0.0444   0.6097   1.0000
   3.250   0.5847   0.01346   0.00527  -0.0428   0.5845   1.0000
   3.500   0.6049   0.01367   0.00542  -0.0412   0.5603   1.0000
   3.750   0.6251   0.01390   0.00560  -0.0396   0.5357   1.0000
   4.000   0.6449   0.01416   0.00579  -0.0380   0.5094   1.0000
   4.250   0.6644   0.01445   0.00601  -0.0363   0.4807   1.0000
   4.500   0.6837   0.01478   0.00624  -0.0346   0.4492   1.0000
   4.750   0.7030   0.01514   0.00650  -0.0329   0.4162   1.0000
   5.000   0.7222   0.01555   0.00679  -0.0313   0.3824   1.0000
   5.250   0.7415   0.01600   0.00715  -0.0298   0.3475   1.0000
   5.500   0.7608   0.01649   0.00753  -0.0283   0.3124   1.0000
   5.750   0.7796   0.01706   0.00796  -0.0268   0.2770   1.0000
   6.000   0.7987   0.01766   0.00845  -0.0254   0.2435   1.0000
   6.250   0.8177   0.01831   0.00901  -0.0241   0.2140   1.0000
   6.500   0.8365   0.01901   0.00960  -0.0227   0.1902   1.0000
   6.750   0.8557   0.01971   0.01026  -0.0214   0.1700   1.0000
   7.000   0.8743   0.02048   0.01097  -0.0201   0.1533   1.0000
   7.250   0.8929   0.02126   0.01175  -0.0188   0.1391   1.0000
   7.500   0.9116   0.02204   0.01258  -0.0175   0.1262   1.0000
   7.750   0.9301   0.02284   0.01341  -0.0162   0.1150   1.0000
   8.000   0.9480   0.02367   0.01424  -0.0149   0.1053   1.0000
   8.250   0.9665   0.02446   0.01512  -0.0137   0.0960   1.0000
   8.500   0.9839   0.02539   0.01610  -0.0123   0.0885   1.0000
   8.750   1.0002   0.02634   0.01710  -0.0108   0.0817   1.0000
   9.000   1.0169   0.02738   0.01826  -0.0094   0.0755   1.0000
   9.250   1.0326   0.02845   0.01941  -0.0079   0.0705   1.0000
   9.500   1.0473   0.02971   0.02073  -0.0064   0.0659   1.0000
   9.750   1.0626   0.03084   0.02204  -0.0049   0.0609   1.0000
  10.000   1.0753   0.03212   0.02334  -0.0033   0.0572   1.0000
  10.250   1.0886   0.03359   0.02500  -0.0017   0.0537   1.0000
  10.500   1.0990   0.03483   0.02646   0.0003   0.0496   1.0000
  10.750   1.1066   0.03608   0.02776   0.0023   0.0467   1.0000
  11.000   1.1138   0.03778   0.02962   0.0043   0.0438   1.0000
  11.250   1.1200   0.03941   0.03151   0.0062   0.0407   1.0000
  11.500   1.1240   0.04098   0.03321   0.0081   0.0382   1.0000
  11.750   1.1255   0.04274   0.03500   0.0097   0.0362   1.0000
  12.000   1.1260   0.04514   0.03766   0.0112   0.0344   1.0000
  12.250   1.1243   0.04771   0.04052   0.0124   0.0326   1.0000
  12.500   1.1210   0.05053   0.04357   0.0133   0.0313   1.0000
  12.750   1.1164   0.05353   0.04675   0.0137   0.0302   1.0000
  13.000   1.1110   0.05670   0.05010   0.0136   0.0293   1.0000
  13.250   1.1050   0.06008   0.05358   0.0131   0.0285   1.0000
  13.500   1.0976   0.06389   0.05749   0.0121   0.0278   1.0000
  13.750   1.0826   0.06917   0.06301   0.0101   0.0273   1.0000
  14.000   1.0661   0.07509   0.06918   0.0073   0.0271   1.0000
  14.250   1.0461   0.08203   0.07636   0.0035   0.0269   1.0000
  14.500   1.0245   0.08981   0.08434  -0.0012   0.0270   1.0000
  14.750   1.0019   0.09839   0.09310  -0.0065   0.0272   1.0000
  15.000   0.9771   0.10812   0.10295  -0.0126   0.0275   1.0000
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