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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.52 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15-il-1000000.txt
Download as CSV file: xf-rg15-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-15 8.9%                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5749   0.05818   0.05667  -0.0419   1.0000   0.0067
  -8.250  -0.6022   0.04949   0.04782  -0.0438   1.0000   0.0064
  -8.000  -0.6363   0.03823   0.03617  -0.0426   1.0000   0.0062
  -7.750  -0.6499   0.02734   0.02447  -0.0420   0.9990   0.0061
  -7.500  -0.6263   0.02183   0.01830  -0.0441   0.9967   0.0062
  -7.250  -0.5966   0.01915   0.01524  -0.0457   0.9952   0.0063
  -7.000  -0.5657   0.01709   0.01286  -0.0471   0.9939   0.0065
  -6.750  -0.5368   0.01545   0.01099  -0.0479   0.9917   0.0066
  -6.500  -0.5041   0.01508   0.01054  -0.0491   0.9896   0.0069
  -6.250  -0.4755   0.01256   0.00767  -0.0499   0.9875   0.0074
  -6.000  -0.4428   0.01159   0.00660  -0.0513   0.9859   0.0081
  -5.750  -0.4082   0.01114   0.00612  -0.0529   0.9845   0.0091
  -5.500  -0.3728   0.01074   0.00567  -0.0546   0.9834   0.0103
  -5.250  -0.3416   0.01044   0.00534  -0.0553   0.9806   0.0110
  -5.000  -0.3120   0.00947   0.00426  -0.0559   0.9768   0.0136
  -4.750  -0.2779   0.00919   0.00397  -0.0573   0.9744   0.0159
  -4.500  -0.2431   0.00877   0.00350  -0.0589   0.9725   0.0185
  -4.250  -0.2074   0.00836   0.00308  -0.0607   0.9710   0.0213
  -4.000  -0.1752   0.00807   0.00275  -0.0616   0.9676   0.0232
  -3.750  -0.1453   0.00782   0.00247  -0.0620   0.9620   0.0251
  -3.500  -0.1123   0.00737   0.00208  -0.0630   0.9580   0.0417
  -3.250  -0.0830   0.00696   0.00183  -0.0635   0.9508   0.0844
  -3.000  -0.0508   0.00661   0.00162  -0.0645   0.9442   0.1273
  -2.750  -0.0211   0.00628   0.00145  -0.0650   0.9342   0.1779
  -2.500   0.0084   0.00593   0.00128  -0.0654   0.9230   0.2425
  -2.250   0.0367   0.00561   0.00115  -0.0656   0.9098   0.3156
  -2.000   0.0637   0.00524   0.00103  -0.0656   0.8949   0.4103
  -1.750   0.0889   0.00470   0.00095  -0.0653   0.8788   0.5683
  -1.500   0.1153   0.00456   0.00093  -0.0649   0.8620   0.6369
  -1.250   0.1422   0.00455   0.00090  -0.0645   0.8446   0.6638
  -1.000   0.1689   0.00455   0.00089  -0.0641   0.8260   0.6920
  -0.750   0.1955   0.00457   0.00088  -0.0637   0.8067   0.7141
  -0.500   0.2222   0.00462   0.00088  -0.0633   0.7870   0.7296
  -0.250   0.2488   0.00466   0.00088  -0.0629   0.7665   0.7437
   0.000   0.2753   0.00473   0.00089  -0.0625   0.7459   0.7574
   0.250   0.3019   0.00479   0.00090  -0.0621   0.7240   0.7706
   0.500   0.3283   0.00486   0.00093  -0.0617   0.7023   0.7835
   0.750   0.3546   0.00494   0.00096  -0.0613   0.6794   0.7959
   1.000   0.3810   0.00503   0.00100  -0.0609   0.6561   0.8085
   1.250   0.4071   0.00512   0.00104  -0.0605   0.6321   0.8216
   1.500   0.4330   0.00523   0.00109  -0.0600   0.6066   0.8358
   1.750   0.4588   0.00533   0.00115  -0.0595   0.5812   0.8507
   2.000   0.4844   0.00543   0.00123  -0.0589   0.5558   0.8671
   2.250   0.5094   0.00555   0.00130  -0.0583   0.5295   0.8860
   2.500   0.5334   0.00565   0.00138  -0.0573   0.5033   0.9067
   2.750   0.5566   0.00577   0.00147  -0.0562   0.4756   0.9301
   3.000   0.5807   0.00591   0.00156  -0.0553   0.4456   0.9580
   3.250   0.6145   0.00608   0.00165  -0.0567   0.4168   0.9848
   3.500   0.6454   0.00632   0.00176  -0.0576   0.3851   1.0000
   3.750   0.6715   0.00655   0.00189  -0.0573   0.3581   1.0000
   4.000   0.6970   0.00684   0.00204  -0.0570   0.3248   1.0000
   4.250   0.7224   0.00715   0.00222  -0.0566   0.2905   1.0000
   4.500   0.7477   0.00746   0.00241  -0.0563   0.2591   1.0000
   4.750   0.7727   0.00782   0.00262  -0.0559   0.2239   1.0000
   5.000   0.7973   0.00823   0.00286  -0.0554   0.1877   1.0000
   5.250   0.8218   0.00865   0.00312  -0.0550   0.1528   1.0000
   5.500   0.8463   0.00906   0.00341  -0.0545   0.1242   1.0000
   5.750   0.8712   0.00943   0.00369  -0.0541   0.1024   1.0000
   6.000   0.8955   0.00987   0.00400  -0.0536   0.0794   1.0000
   6.250   0.9199   0.01030   0.00434  -0.0531   0.0606   1.0000
   6.500   0.9442   0.01073   0.00469  -0.0526   0.0453   1.0000
   6.750   0.9686   0.01114   0.00506  -0.0521   0.0338   1.0000
   7.000   0.9928   0.01157   0.00545  -0.0516   0.0238   1.0000
   7.250   1.0146   0.01230   0.00606  -0.0507   0.0103   1.0000
   7.500   1.0375   0.01290   0.00671  -0.0499   0.0077   1.0000
   7.750   1.0614   0.01336   0.00723  -0.0492   0.0071   1.0000
   8.000   1.0846   0.01390   0.00784  -0.0485   0.0065   1.0000
   8.250   1.1071   0.01449   0.00850  -0.0476   0.0061   1.0000
   8.500   1.1289   0.01515   0.00924  -0.0467   0.0055   1.0000
   8.750   1.1484   0.01606   0.01026  -0.0454   0.0050   1.0000
   9.000   1.1651   0.01725   0.01160  -0.0437   0.0047   1.0000
   9.250   1.1787   0.01876   0.01328  -0.0415   0.0045   1.0000
   9.500   1.1941   0.02001   0.01467  -0.0397   0.0044   1.0000
   9.750   1.2113   0.02101   0.01578  -0.0383   0.0044   1.0000
  10.000   1.2282   0.02199   0.01687  -0.0368   0.0043   1.0000
  10.250   1.2445   0.02298   0.01797  -0.0352   0.0042   1.0000
  10.500   1.2581   0.02418   0.01932  -0.0334   0.0041   1.0000
  10.750   1.2704   0.02542   0.02070  -0.0314   0.0040   1.0000
  11.000   1.2787   0.02682   0.02224  -0.0288   0.0039   1.0000
  11.250   1.2828   0.02826   0.02383  -0.0256   0.0038   1.0000
  11.500   1.2852   0.02978   0.02550  -0.0225   0.0037   1.0000
  11.750   1.2844   0.03161   0.02750  -0.0193   0.0036   1.0000
  12.000   1.2795   0.03387   0.02995  -0.0163   0.0036   1.0000
  12.250   1.2781   0.03580   0.03202  -0.0140   0.0034   1.0000
  12.500   1.2708   0.03849   0.03489  -0.0120   0.0034   1.0000
  12.750   1.2591   0.04194   0.03854  -0.0106   0.0034   1.0000
  13.000   1.2504   0.04528   0.04204  -0.0101   0.0033   1.0000
  13.250   1.2350   0.04990   0.04686  -0.0106   0.0033   1.0000
  13.500   1.2188   0.05518   0.05233  -0.0121   0.0034   1.0000
  13.750   1.2033   0.06092   0.05823  -0.0147   0.0033   1.0000
  14.000   1.1810   0.06849   0.06600  -0.0187   0.0034   1.0000
  14.250   1.1649   0.07562   0.07328  -0.0231   0.0033   1.0000
  14.500   1.1416   0.08479   0.08263  -0.0287   0.0035   1.0000
  14.750   1.1219   0.09390   0.09188  -0.0345   0.0035   1.0000
  15.000   1.0990   0.10432   0.10243  -0.0410   0.0035   1.0000
  15.250   1.0749   0.11558   0.11382  -0.0478   0.0036   1.0000
  15.500   1.0498   0.12775   0.12611  -0.0550   0.0037   1.0000
  15.750   1.0177   0.14269   0.14117  -0.0634   0.0038   1.0000
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