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RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 100,000
Max Cl/Cd: 48.5 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg1495-il-100000.txt
Download as CSV file: xf-rg1495-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9.5% 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4909   0.09736   0.09226  -0.0202   1.0000   0.1231
  -9.000  -0.5100   0.09380   0.08882  -0.0249   1.0000   0.1278
  -8.750  -0.5502   0.08986   0.08505  -0.0320   1.0000   0.1288
  -8.500  -0.4984   0.08683   0.08191  -0.0234   1.0000   0.1384
  -8.250  -0.5235   0.08296   0.07818  -0.0275   1.0000   0.1417
  -8.000  -0.5645   0.07881   0.07403  -0.0333   1.0000   0.1431
  -7.750  -0.5243   0.07597   0.07128  -0.0264   1.0000   0.1507
  -7.500  -0.5664   0.07211   0.06728  -0.0323   1.0000   0.1576
  -7.250  -0.5417   0.06828   0.06363  -0.0283   1.0000   0.1622
  -7.000  -0.5611   0.06472   0.05991  -0.0302   1.0000   0.1734
  -6.750  -0.5447   0.06144   0.05674  -0.0275   1.0000   0.1770
  -6.500  -0.5682   0.04288   0.03672  -0.0321   1.0000   0.0820
  -6.250  -0.5628   0.03716   0.02996  -0.0293   1.0000   0.0724
  -6.000  -0.5493   0.03377   0.02622  -0.0275   1.0000   0.0716
  -5.750  -0.5335   0.03151   0.02338  -0.0255   1.0000   0.0730
  -5.500  -0.5168   0.02859   0.02011  -0.0239   1.0000   0.0748
  -5.250  -0.4971   0.02635   0.01763  -0.0225   1.0000   0.0761
  -5.000  -0.4764   0.02461   0.01570  -0.0211   1.0000   0.0784
  -4.750  -0.4552   0.02329   0.01419  -0.0198   1.0000   0.0830
  -4.500  -0.4333   0.02189   0.01256  -0.0184   1.0000   0.0883
  -4.250  -0.4117   0.02059   0.01129  -0.0172   1.0000   0.0944
  -4.000  -0.3900   0.01941   0.01006  -0.0159   1.0000   0.1037
  -3.750  -0.3694   0.01845   0.00921  -0.0147   1.0000   0.1198
  -3.500  -0.3491   0.01736   0.00830  -0.0133   1.0000   0.1475
  -3.250  -0.3296   0.01636   0.00761  -0.0121   1.0000   0.2022
  -3.000  -0.3116   0.01517   0.00715  -0.0108   1.0000   0.3068
  -2.750  -0.2976   0.01383   0.00698  -0.0084   1.0000   0.5156
  -2.500  -0.2897   0.01325   0.00746  -0.0028   1.0000   0.7561
  -2.250  -0.2767   0.01344   0.00779   0.0019   1.0000   0.8801
  -2.000  -0.1719   0.01411   0.00808  -0.0104   1.0000   0.9788
  -1.750  -0.1019   0.01421   0.00784  -0.0190   1.0000   1.0000
  -1.500  -0.1068   0.01415   0.00772  -0.0146   1.0000   1.0000
  -1.250  -0.1082   0.01416   0.00763  -0.0107   1.0000   1.0000
  -1.000  -0.1050   0.01424   0.00761  -0.0077   1.0000   1.0000
  -0.750  -0.0763   0.01455   0.00779  -0.0091   0.9955   1.0000
  -0.500  -0.0227   0.01499   0.00807  -0.0150   0.9849   1.0000
  -0.250   0.0290   0.01531   0.00828  -0.0203   0.9734   1.0000
   0.000   0.0791   0.01553   0.00841  -0.0252   0.9612   1.0000
   0.250   0.1286   0.01567   0.00849  -0.0298   0.9488   1.0000
   0.500   0.1789   0.01573   0.00852  -0.0343   0.9366   1.0000
   0.750   0.2332   0.01569   0.00847  -0.0395   0.9256   1.0000
   1.000   0.2900   0.01552   0.00832  -0.0449   0.9148   1.0000
   1.250   0.3405   0.01528   0.00812  -0.0489   0.9015   1.0000
   1.500   0.3879   0.01497   0.00786  -0.0522   0.8872   1.0000
   1.750   0.4318   0.01464   0.00759  -0.0546   0.8716   1.0000
   2.000   0.4691   0.01434   0.00731  -0.0555   0.8527   1.0000
   2.250   0.4992   0.01409   0.00707  -0.0549   0.8295   1.0000
   2.500   0.5261   0.01388   0.00687  -0.0537   0.8044   1.0000
   2.750   0.5517   0.01374   0.00669  -0.0522   0.7789   1.0000
   3.000   0.5746   0.01372   0.00663  -0.0504   0.7529   1.0000
   3.250   0.5960   0.01379   0.00667  -0.0485   0.7264   1.0000
   3.500   0.6176   0.01389   0.00675  -0.0467   0.6995   1.0000
   3.750   0.6389   0.01403   0.00683  -0.0448   0.6714   1.0000
   4.000   0.6595   0.01419   0.00693  -0.0428   0.6412   1.0000
   4.250   0.6796   0.01438   0.00703  -0.0407   0.6088   1.0000
   4.500   0.6997   0.01461   0.00717  -0.0387   0.5753   1.0000
   4.750   0.7187   0.01488   0.00738  -0.0366   0.5382   1.0000
   5.000   0.7377   0.01521   0.00758  -0.0345   0.4995   1.0000
   5.250   0.7557   0.01561   0.00784  -0.0323   0.4555   1.0000
   5.500   0.7728   0.01612   0.00820  -0.0301   0.4056   1.0000
   5.750   0.7888   0.01681   0.00862  -0.0279   0.3518   1.0000
   6.000   0.8049   0.01767   0.00920  -0.0257   0.3004   1.0000
   6.250   0.8217   0.01863   0.00990  -0.0239   0.2580   1.0000
   6.500   0.8393   0.01968   0.01070  -0.0222   0.2250   1.0000
   6.750   0.8579   0.02075   0.01163  -0.0208   0.1972   1.0000
   7.000   0.8777   0.02192   0.01272  -0.0195   0.1748   1.0000
   7.250   0.8979   0.02316   0.01385  -0.0184   0.1562   1.0000
   7.500   0.9194   0.02457   0.01517  -0.0175   0.1407   1.0000
   7.750   0.9406   0.02592   0.01654  -0.0165   0.1267   1.0000
   8.000   0.9621   0.02740   0.01819  -0.0155   0.1154   1.0000
   8.250   0.9829   0.02894   0.01983  -0.0145   0.1050   1.0000
   8.500   1.0051   0.03082   0.02167  -0.0138   0.0966   1.0000
   8.750   1.0231   0.03220   0.02334  -0.0123   0.0883   1.0000
   9.000   1.0417   0.03453   0.02585  -0.0112   0.0818   1.0000
   9.250   1.0580   0.03608   0.02763  -0.0097   0.0750   1.0000
   9.500   1.0722   0.03910   0.03089  -0.0083   0.0704   1.0000
   9.750   1.0811   0.04148   0.03376  -0.0059   0.0659   1.0000
  10.000   1.0965   0.04341   0.03567  -0.0049   0.0612   1.0000
  10.250   1.0999   0.04776   0.04038  -0.0029   0.0594   1.0000
  10.500   1.0947   0.05118   0.04436   0.0003   0.0584   1.0000
  10.750   1.0839   0.05482   0.04846   0.0035   0.0575   1.0000
  11.000   1.0686   0.05847   0.05247   0.0066   0.0570   1.0000
  11.250   1.0483   0.06205   0.05631   0.0096   0.0570   1.0000
  11.500   1.0252   0.06608   0.06057   0.0113   0.0571   1.0000
  11.750   1.0021   0.07075   0.06543   0.0114   0.0576   1.0000
  12.000   0.9761   0.07622   0.07107   0.0098   0.0580   1.0000
  12.250   0.9528   0.08262   0.07758   0.0069   0.0587   1.0000
  12.500   0.9306   0.08984   0.08488   0.0030   0.0594   1.0000
  12.750   0.8398   0.11674   0.11183  -0.0168   0.0711   1.0000
  13.000   0.8387   0.12272   0.11781  -0.0182   0.0719   1.0000
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