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RG-12 (rg12-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG-12 (rg12-il)
Reynolds number: 100,000
Max Cl/Cd: 48.85 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12-il-100000.txt
Download as CSV file: xf-rg12-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-12                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4959   0.10320   0.09819  -0.0205   1.0000   0.1016
  -9.250  -0.5196   0.09973   0.09486  -0.0272   1.0000   0.1041
  -9.000  -0.5156   0.09487   0.09004  -0.0269   1.0000   0.1059
  -8.750  -0.4974   0.09189   0.08703  -0.0237   1.0000   0.1102
  -8.500  -0.5018   0.08835   0.08356  -0.0253   1.0000   0.1142
  -8.250  -0.5318   0.08426   0.07962  -0.0312   1.0000   0.1170
  -8.000  -0.5758   0.08094   0.07618  -0.0368   1.0000   0.1182
  -7.750  -0.5318   0.07658   0.07203  -0.0302   1.0000   0.1226
  -7.500  -0.5371   0.07312   0.06858  -0.0310   1.0000   0.1278
  -7.250  -0.5609   0.06860   0.06395  -0.0342   1.0000   0.1332
  -7.000  -0.5438   0.06592   0.06138  -0.0312   1.0000   0.1392
  -6.750  -0.5499   0.06221   0.05760  -0.0315   1.0000   0.1490
  -6.500  -0.5617   0.04943   0.04337  -0.0347   1.0000   0.0773
  -6.250  -0.5509   0.04239   0.03608  -0.0333   1.0000   0.0625
  -6.000  -0.5395   0.03868   0.03202  -0.0317   1.0000   0.0617
  -5.750  -0.5256   0.03510   0.02806  -0.0301   1.0000   0.0601
  -5.500  -0.5092   0.03137   0.02379  -0.0283   1.0000   0.0572
  -5.250  -0.4897   0.02813   0.01992  -0.0265   1.0000   0.0555
  -5.000  -0.4684   0.02575   0.01714  -0.0250   1.0000   0.0558
  -4.750  -0.4462   0.02379   0.01489  -0.0236   1.0000   0.0578
  -4.500  -0.4233   0.02210   0.01297  -0.0222   1.0000   0.0617
  -4.250  -0.4017   0.02054   0.01139  -0.0210   1.0000   0.0702
  -4.000  -0.3802   0.01920   0.01008  -0.0197   1.0000   0.0859
  -3.750  -0.3591   0.01794   0.00890  -0.0184   1.0000   0.1183
  -3.500  -0.3391   0.01660   0.00794  -0.0173   1.0000   0.1665
  -3.250  -0.3201   0.01499   0.00713  -0.0161   1.0000   0.2820
  -3.000  -0.3089   0.01317   0.00695  -0.0130   1.0000   0.5825
  -2.750  -0.3023   0.01317   0.00745  -0.0070   1.0000   0.7611
  -2.500  -0.2947   0.01335   0.00767  -0.0016   1.0000   0.8325
  -2.250  -0.2863   0.01350   0.00780   0.0038   1.0000   0.8884
  -2.000  -0.2458   0.01385   0.00798   0.0032   1.0000   0.9475
  -1.750  -0.1103   0.01442   0.00794  -0.0158   1.0000   0.9905
  -1.500  -0.0722   0.01435   0.00769  -0.0191   1.0000   1.0000
  -1.250  -0.0794   0.01423   0.00754  -0.0144   1.0000   1.0000
  -1.000  -0.0869   0.01412   0.00740  -0.0098   1.0000   1.0000
  -0.750  -0.0901   0.01407   0.00728  -0.0060   1.0000   1.0000
  -0.500  -0.0832   0.01415   0.00727  -0.0038   1.0000   1.0000
  -0.250  -0.0299   0.01464   0.00760  -0.0098   0.9891   1.0000
   0.000   0.0217   0.01504   0.00790  -0.0153   0.9777   1.0000
   0.250   0.0724   0.01534   0.00811  -0.0205   0.9660   1.0000
   0.500   0.1234   0.01553   0.00825  -0.0255   0.9540   1.0000
   0.750   0.1769   0.01563   0.00833  -0.0308   0.9429   1.0000
   1.000   0.2264   0.01560   0.00830  -0.0351   0.9299   1.0000
   1.250   0.2767   0.01548   0.00821  -0.0394   0.9169   1.0000
   1.500   0.3295   0.01526   0.00805  -0.0440   0.9041   1.0000
   1.750   0.3809   0.01493   0.00779  -0.0480   0.8904   1.0000
   2.000   0.4293   0.01454   0.00747  -0.0513   0.8752   1.0000
   2.250   0.4669   0.01424   0.00726  -0.0525   0.8557   1.0000
   2.500   0.5025   0.01396   0.00702  -0.0531   0.8348   1.0000
   2.750   0.5310   0.01379   0.00688  -0.0524   0.8107   1.0000
   3.000   0.5578   0.01368   0.00677  -0.0514   0.7855   1.0000
   3.250   0.5822   0.01365   0.00676  -0.0500   0.7585   1.0000
   3.500   0.6049   0.01370   0.00678  -0.0483   0.7296   1.0000
   3.750   0.6270   0.01380   0.00684  -0.0465   0.6993   1.0000
   4.000   0.6493   0.01395   0.00693  -0.0448   0.6678   1.0000
   4.250   0.6712   0.01415   0.00705  -0.0431   0.6351   1.0000
   4.500   0.6921   0.01440   0.00729  -0.0413   0.5997   1.0000
   4.750   0.7132   0.01469   0.00750  -0.0396   0.5632   1.0000
   5.000   0.7339   0.01504   0.00773  -0.0378   0.5252   1.0000
   5.250   0.7538   0.01543   0.00803  -0.0360   0.4842   1.0000
   5.500   0.7733   0.01589   0.00838  -0.0342   0.4418   1.0000
   5.750   0.7920   0.01642   0.00880  -0.0324   0.3956   1.0000
   6.000   0.8099   0.01706   0.00933  -0.0306   0.3471   1.0000
   6.250   0.8270   0.01784   0.00992  -0.0287   0.2958   1.0000
   6.500   0.8429   0.01882   0.01064  -0.0268   0.2436   1.0000
   6.750   0.8582   0.02001   0.01156  -0.0249   0.1944   1.0000
   7.000   0.8735   0.02139   0.01269  -0.0231   0.1530   1.0000
   7.250   0.8894   0.02294   0.01408  -0.0213   0.1197   1.0000
   7.500   0.9061   0.02466   0.01563  -0.0198   0.0964   1.0000
   7.750   0.9256   0.02654   0.01760  -0.0183   0.0800   1.0000
   8.000   0.9476   0.02888   0.01994  -0.0174   0.0694   1.0000
   8.250   0.9679   0.03123   0.02223  -0.0166   0.0597   1.0000
   8.500   0.9892   0.03365   0.02513  -0.0151   0.0550   1.0000
   8.750   1.0077   0.03595   0.02755  -0.0140   0.0499   1.0000
   9.000   1.0207   0.03918   0.03117  -0.0123   0.0460   1.0000
   9.250   1.0311   0.04247   0.03500  -0.0100   0.0445   1.0000
   9.500   1.0363   0.04625   0.03929  -0.0076   0.0438   1.0000
   9.750   1.0364   0.05028   0.04379  -0.0050   0.0438   1.0000
  10.000   1.0309   0.05444   0.04838  -0.0024   0.0442   1.0000
  10.250   1.0199   0.05864   0.05293   0.0002   0.0446   1.0000
  10.500   1.0048   0.06244   0.05699   0.0028   0.0452   1.0000
  10.750   0.9866   0.06627   0.06102   0.0048   0.0457   1.0000
  11.000   0.9664   0.07061   0.06554   0.0055   0.0461   1.0000
  11.250   0.9467   0.07538   0.07045   0.0047   0.0466   1.0000
  11.500   0.9266   0.08096   0.07614   0.0025   0.0470   1.0000
  11.750   0.9120   0.08732   0.08256   0.0000   0.0477   1.0000
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