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RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RG 14 9% AIRFOIL (rg149-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.01 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg149-il-1000000.txt
Download as CSV file: xf-rg149-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9% AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7938   0.04468   0.04271  -0.0538   1.0000   0.0073
 -11.000  -0.8438   0.03895   0.03674  -0.0516   1.0000   0.0071
 -10.750  -0.8588   0.03544   0.03298  -0.0489   1.0000   0.0072
 -10.500  -0.8643   0.03251   0.02979  -0.0462   1.0000   0.0072
 -10.250  -0.8624   0.03022   0.02726  -0.0438   1.0000   0.0073
 -10.000  -0.8860   0.02404   0.02038  -0.0388   1.0000   0.0076
  -9.750  -0.8751   0.02240   0.01856  -0.0367   1.0000   0.0078
  -9.500  -0.8577   0.02173   0.01784  -0.0353   1.0000   0.0081
  -9.250  -0.8395   0.02115   0.01720  -0.0339   1.0000   0.0083
  -9.000  -0.8219   0.02040   0.01635  -0.0324   1.0000   0.0086
  -8.750  -0.8056   0.01934   0.01514  -0.0306   1.0000   0.0088
  -8.500  -0.7876   0.01856   0.01424  -0.0291   1.0000   0.0092
  -8.250  -0.7704   0.01754   0.01307  -0.0274   1.0000   0.0095
  -8.000  -0.7517   0.01681   0.01222  -0.0259   1.0000   0.0099
  -7.750  -0.7253   0.01629   0.01160  -0.0259   0.9994   0.0102
  -7.500  -0.6964   0.01449   0.00957  -0.0268   0.9978   0.0109
  -7.250  -0.6634   0.01399   0.00905  -0.0283   0.9963   0.0116
  -7.000  -0.6288   0.01383   0.00887  -0.0300   0.9950   0.0125
  -6.750  -0.5954   0.01335   0.00833  -0.0313   0.9936   0.0133
  -6.500  -0.5633   0.01304   0.00796  -0.0323   0.9914   0.0140
  -6.250  -0.5330   0.01189   0.00669  -0.0331   0.9890   0.0149
  -6.000  -0.5004   0.01121   0.00597  -0.0344   0.9870   0.0160
  -5.750  -0.4660   0.01086   0.00561  -0.0360   0.9855   0.0172
  -5.500  -0.4308   0.01055   0.00527  -0.0376   0.9842   0.0184
  -5.250  -0.3974   0.01027   0.00497  -0.0389   0.9821   0.0192
  -5.000  -0.3689   0.00954   0.00414  -0.0391   0.9778   0.0206
  -4.750  -0.3356   0.00908   0.00366  -0.0403   0.9751   0.0224
  -4.500  -0.3004   0.00875   0.00332  -0.0419   0.9730   0.0241
  -4.250  -0.2645   0.00845   0.00299  -0.0437   0.9713   0.0256
  -4.000  -0.2357   0.00812   0.00261  -0.0438   0.9657   0.0282
  -3.750  -0.2044   0.00781   0.00233  -0.0444   0.9605   0.0337
  -3.500  -0.1721   0.00740   0.00204  -0.0454   0.9558   0.0607
  -3.250  -0.1438   0.00708   0.00184  -0.0455   0.9467   0.0906
  -3.000  -0.1137   0.00679   0.00166  -0.0460   0.9377   0.1240
  -2.750  -0.0843   0.00650   0.00149  -0.0464   0.9272   0.1664
  -2.500  -0.0568   0.00620   0.00135  -0.0463   0.9139   0.2212
  -2.250  -0.0305   0.00592   0.00123  -0.0460   0.8994   0.2830
  -2.000  -0.0049   0.00562   0.00113  -0.0456   0.8841   0.3572
  -1.750   0.0202   0.00530   0.00104  -0.0450   0.8681   0.4436
  -1.500   0.0441   0.00489   0.00096  -0.0443   0.8513   0.5612
  -1.250   0.0679   0.00457   0.00091  -0.0434   0.8339   0.6631
  -1.000   0.0917   0.00437   0.00093  -0.0424   0.8150   0.7528
  -0.750   0.1169   0.00436   0.00094  -0.0416   0.7937   0.7934
  -0.500   0.1424   0.00439   0.00096  -0.0408   0.7724   0.8222
  -0.250   0.1683   0.00446   0.00097  -0.0402   0.7514   0.8404
   0.000   0.1942   0.00453   0.00098  -0.0396   0.7277   0.8540
   0.250   0.2201   0.00460   0.00099  -0.0390   0.7058   0.8658
   0.500   0.2459   0.00468   0.00102  -0.0384   0.6843   0.8768
   0.750   0.2718   0.00476   0.00105  -0.0378   0.6643   0.8880
   1.000   0.2977   0.00485   0.00108  -0.0372   0.6416   0.8982
   1.250   0.3228   0.00496   0.00112  -0.0365   0.6149   0.9068
   1.500   0.3483   0.00507   0.00116  -0.0359   0.5915   0.9159
   1.750   0.3733   0.00518   0.00121  -0.0351   0.5685   0.9261
   2.000   0.3977   0.00530   0.00127  -0.0342   0.5431   0.9358
   2.250   0.4220   0.00546   0.00133  -0.0333   0.5107   0.9452
   2.500   0.4462   0.00563   0.00140  -0.0324   0.4803   0.9558
   2.750   0.4726   0.00579   0.00148  -0.0320   0.4520   0.9659
   3.000   0.5019   0.00600   0.00158  -0.0323   0.4207   0.9748
   3.250   0.5324   0.00622   0.00169  -0.0330   0.3899   0.9829
   3.500   0.5674   0.00645   0.00181  -0.0347   0.3582   0.9864
   3.750   0.6013   0.00675   0.00196  -0.0362   0.3191   0.9896
   4.000   0.6337   0.00704   0.00211  -0.0374   0.2818   0.9932
   4.250   0.6662   0.00744   0.00229  -0.0387   0.2348   0.9961
   4.500   0.6986   0.00788   0.00251  -0.0401   0.1857   0.9992
   4.750   0.7202   0.00820   0.00272  -0.0391   0.1593   1.0000
   5.000   0.7403   0.00846   0.00291  -0.0376   0.1431   1.0000
   5.250   0.7624   0.00871   0.00310  -0.0365   0.1298   1.0000
   5.500   0.7856   0.00896   0.00331  -0.0357   0.1154   1.0000
   5.750   0.8091   0.00926   0.00354  -0.0349   0.0988   1.0000
   6.000   0.8327   0.00960   0.00379  -0.0342   0.0837   1.0000
   6.250   0.8567   0.00992   0.00406  -0.0336   0.0718   1.0000
   6.500   0.8810   0.01023   0.00434  -0.0330   0.0618   1.0000
   6.750   0.9054   0.01055   0.00464  -0.0324   0.0536   1.0000
   7.000   0.9291   0.01094   0.00497  -0.0318   0.0449   1.0000
   7.250   0.9538   0.01122   0.00526  -0.0313   0.0402   1.0000
   7.500   0.9776   0.01161   0.00563  -0.0307   0.0342   1.0000
   7.750   1.0018   0.01195   0.00596  -0.0301   0.0302   1.0000
   8.000   1.0251   0.01239   0.00641  -0.0294   0.0259   1.0000
   8.250   1.0492   0.01271   0.00675  -0.0289   0.0232   1.0000
   8.500   1.0715   0.01325   0.00728  -0.0281   0.0193   1.0000
   8.750   1.0951   0.01362   0.00767  -0.0275   0.0168   1.0000
   9.000   1.1165   0.01423   0.00831  -0.0265   0.0138   1.0000
   9.250   1.1392   0.01468   0.00879  -0.0258   0.0120   1.0000
   9.500   1.1588   0.01547   0.00961  -0.0245   0.0102   1.0000
   9.750   1.1811   0.01591   0.01011  -0.0238   0.0096   1.0000
  10.000   1.2022   0.01647   0.01073  -0.0228   0.0089   1.0000
  10.250   1.2225   0.01708   0.01139  -0.0218   0.0083   1.0000
  10.500   1.2386   0.01810   0.01249  -0.0202   0.0075   1.0000
  10.750   1.2546   0.01904   0.01356  -0.0185   0.0072   1.0000
  11.000   1.2723   0.01978   0.01439  -0.0171   0.0070   1.0000
  11.250   1.2892   0.02053   0.01523  -0.0157   0.0068   1.0000
  11.500   1.3053   0.02130   0.01608  -0.0142   0.0065   1.0000
  11.750   1.3186   0.02222   0.01710  -0.0123   0.0063   1.0000
  12.000   1.3291   0.02311   0.01808  -0.0099   0.0061   1.0000
  12.250   1.3375   0.02402   0.01907  -0.0072   0.0059   1.0000
  12.500   1.3435   0.02507   0.02022  -0.0044   0.0057   1.0000
  12.750   1.3488   0.02620   0.02144  -0.0018   0.0056   1.0000
  13.000   1.3495   0.02768   0.02305   0.0010   0.0054   1.0000
  13.250   1.3493   0.02931   0.02479   0.0036   0.0054   1.0000
  13.500   1.3391   0.03185   0.02749   0.0063   0.0052   1.0000
  13.750   1.3200   0.03548   0.03135   0.0085   0.0050   1.0000
  14.000   1.3139   0.03832   0.03432   0.0094   0.0051   1.0000
  14.250   1.3025   0.04204   0.03822   0.0095   0.0050   1.0000
  14.500   1.3058   0.04440   0.04068   0.0092   0.0049   1.0000
  14.750   1.2791   0.05079   0.04728   0.0074   0.0050   1.0000
  15.000   1.2872   0.05303   0.04960   0.0064   0.0048   1.0000
  15.250   1.2761   0.05815   0.05486   0.0040   0.0048   1.0000
  15.500   1.2558   0.06512   0.06201   0.0004   0.0048   1.0000
  15.750   1.2519   0.06977   0.06675  -0.0022   0.0048   1.0000
  16.000   1.2314   0.07753   0.07467  -0.0067   0.0048   1.0000
  16.250   1.2112   0.08571   0.08299  -0.0115   0.0048   1.0000
  16.500   1.1819   0.09594   0.09338  -0.0174   0.0048   1.0000
  16.750   1.1502   0.10726   0.10487  -0.0240   0.0049   1.0000
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