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RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il)
Reynolds number: 50,000
Max Cl/Cd: 34.6 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15a213-il-50000-n5.txt
Download as CSV file: xf-rg15a213-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 15A 2.5/13.0 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4501   0.10144   0.09393  -0.0462   1.0000   0.0558
 -10.750  -0.4589   0.09585   0.08842  -0.0483   1.0000   0.0556
 -10.500  -0.4715   0.08945   0.08211  -0.0511   1.0000   0.0554
 -10.250  -0.4893   0.08222   0.07494  -0.0547   1.0000   0.0550
 -10.000  -0.5131   0.07539   0.06817  -0.0584   1.0000   0.0544
  -9.750  -0.5423   0.06980   0.06261  -0.0604   1.0000   0.0539
  -9.500  -0.5734   0.06581   0.05863  -0.0596   1.0000   0.0535
  -9.250  -0.5995   0.06212   0.05486  -0.0579   1.0000   0.0532
  -9.000  -0.6201   0.05842   0.05101  -0.0559   1.0000   0.0532
  -8.750  -0.6348   0.05490   0.04726  -0.0537   1.0000   0.0535
  -8.500  -0.6444   0.05147   0.04352  -0.0515   1.0000   0.0543
  -8.250  -0.6497   0.04807   0.03969  -0.0493   1.0000   0.0556
  -8.000  -0.6489   0.04500   0.03620  -0.0473   1.0000   0.0571
  -7.750  -0.6391   0.04339   0.03458  -0.0456   1.0000   0.0592
  -7.500  -0.6295   0.04138   0.03235  -0.0439   1.0000   0.0612
  -7.250  -0.6183   0.03913   0.02979  -0.0422   1.0000   0.0635
  -7.000  -0.6048   0.03694   0.02719  -0.0406   1.0000   0.0662
  -6.750  -0.5902   0.03533   0.02545  -0.0392   1.0000   0.0698
  -6.500  -0.5749   0.03408   0.02410  -0.0377   1.0000   0.0750
  -6.250  -0.5577   0.03253   0.02227  -0.0363   1.0000   0.0808
  -6.000  -0.5411   0.03137   0.02111  -0.0349   1.0000   0.0873
  -5.750  -0.5237   0.03025   0.01989  -0.0335   1.0000   0.0971
  -5.500  -0.5063   0.02931   0.01888  -0.0323   1.0000   0.1097
  -5.250  -0.4891   0.02858   0.01817  -0.0312   1.0000   0.1253
  -5.000  -0.4718   0.02798   0.01759  -0.0302   1.0000   0.1452
  -4.750  -0.4374   0.02727   0.01685  -0.0322   0.9938   0.1702
  -4.500  -0.4032   0.02657   0.01612  -0.0340   0.9866   0.1972
  -4.250  -0.3691   0.02591   0.01553  -0.0359   0.9794   0.2285
  -4.000  -0.3344   0.02526   0.01504  -0.0380   0.9721   0.2683
  -3.750  -0.3031   0.02461   0.01458  -0.0394   0.9636   0.3180
  -3.500  -0.2699   0.02402   0.01429  -0.0410   0.9561   0.3856
  -3.250  -0.2411   0.02354   0.01420  -0.0413   0.9471   0.4646
  -3.000  -0.2146   0.02342   0.01447  -0.0404   0.9378   0.5501
  -2.750  -0.1841   0.02360   0.01478  -0.0400   0.9295   0.6322
  -2.500  -0.1600   0.02378   0.01490  -0.0386   0.9187   0.6890
  -2.250  -0.1335   0.02396   0.01503  -0.0373   0.9093   0.7325
  -2.000  -0.1047   0.02408   0.01505  -0.0366   0.9002   0.7692
  -1.750  -0.0814   0.02416   0.01505  -0.0349   0.8894   0.7997
  -1.500  -0.0503   0.02420   0.01499  -0.0345   0.8812   0.8294
  -1.250  -0.0226   0.02421   0.01491  -0.0337   0.8708   0.8568
  -1.000   0.0097   0.02421   0.01482  -0.0338   0.8613   0.8836
  -0.750   0.0559   0.02418   0.01466  -0.0365   0.8539   0.9085
  -0.500   0.1038   0.02419   0.01455  -0.0400   0.8449   0.9306
  -0.250   0.1665   0.02408   0.01431  -0.0463   0.8385   0.9482
   0.000   0.2233   0.02400   0.01411  -0.0519   0.8292   0.9634
   0.250   0.2855   0.02373   0.01373  -0.0584   0.8218   0.9752
   0.500   0.3351   0.02356   0.01350  -0.0629   0.8101   0.9883
   0.750   0.3835   0.02333   0.01321  -0.0671   0.7993   1.0000
   1.000   0.4103   0.02310   0.01292  -0.0671   0.7876   1.0000
   1.250   0.4306   0.02297   0.01275  -0.0659   0.7742   1.0000
   1.500   0.4469   0.02294   0.01268  -0.0641   0.7599   1.0000
   1.750   0.4636   0.02293   0.01263  -0.0623   0.7459   1.0000
   2.000   0.4822   0.02293   0.01258  -0.0608   0.7320   1.0000
   2.250   0.5038   0.02294   0.01254  -0.0597   0.7184   1.0000
   2.500   0.5286   0.02294   0.01251  -0.0591   0.7051   1.0000
   2.750   0.5558   0.02294   0.01245  -0.0588   0.6919   1.0000
   3.000   0.5847   0.02293   0.01239  -0.0587   0.6787   1.0000
   3.250   0.6092   0.02305   0.01251  -0.0581   0.6639   1.0000
   3.500   0.6341   0.02320   0.01263  -0.0574   0.6489   1.0000
   3.750   0.6593   0.02336   0.01277  -0.0568   0.6337   1.0000
   4.000   0.6847   0.02354   0.01295  -0.0563   0.6183   1.0000
   4.250   0.7101   0.02374   0.01314  -0.0557   0.6027   1.0000
   4.500   0.7353   0.02396   0.01335  -0.0550   0.5869   1.0000
   4.750   0.7603   0.02420   0.01360  -0.0544   0.5709   1.0000
   5.000   0.7850   0.02446   0.01386  -0.0537   0.5547   1.0000
   5.250   0.8096   0.02475   0.01414  -0.0530   0.5384   1.0000
   5.500   0.8338   0.02506   0.01445  -0.0522   0.5219   1.0000
   5.750   0.8567   0.02542   0.01484  -0.0513   0.5051   1.0000
   6.000   0.8783   0.02585   0.01529  -0.0502   0.4879   1.0000
   6.250   0.8997   0.02629   0.01576  -0.0491   0.4709   1.0000
   6.500   0.9207   0.02676   0.01628  -0.0479   0.4536   1.0000
   6.750   0.9413   0.02727   0.01681  -0.0468   0.4366   1.0000
   7.000   0.9614   0.02779   0.01737  -0.0455   0.4195   1.0000
   7.250   0.9810   0.02836   0.01795  -0.0442   0.4025   1.0000
   7.500   0.9999   0.02895   0.01860  -0.0429   0.3857   1.0000
   7.750   1.0181   0.02959   0.01926  -0.0415   0.3691   1.0000
   8.000   1.0354   0.03027   0.01996  -0.0400   0.3527   1.0000
   8.250   1.0517   0.03099   0.02071  -0.0384   0.3364   1.0000
   8.500   1.0670   0.03177   0.02153  -0.0367   0.3205   1.0000
   8.750   1.0811   0.03260   0.02240  -0.0349   0.3050   1.0000
   9.000   1.0939   0.03350   0.02335  -0.0330   0.2899   1.0000
   9.250   1.1047   0.03446   0.02436  -0.0309   0.2755   1.0000
   9.750   1.1240   0.03663   0.02668  -0.0267   0.2484   1.0000
  10.000   1.1335   0.03783   0.02794  -0.0248   0.2359   1.0000
  10.250   1.1424   0.03908   0.02922  -0.0229   0.2240   1.0000
  10.500   1.1525   0.04032   0.03045  -0.0212   0.2129   1.0000
  10.750   1.1571   0.04194   0.03224  -0.0192   0.2017   1.0000
  11.000   1.1621   0.04360   0.03401  -0.0175   0.1913   1.0000
  11.250   1.1693   0.04515   0.03556  -0.0160   0.1818   1.0000
  11.500   1.1712   0.04710   0.03765  -0.0144   0.1722   1.0000
  11.750   1.1722   0.04921   0.03987  -0.0131   0.1633   1.0000
  12.000   1.1764   0.05100   0.04163  -0.0119   0.1550   1.0000
  12.250   1.1719   0.05382   0.04469  -0.0109   0.1471   1.0000
  12.500   1.1747   0.05589   0.04670  -0.0101   0.1399   1.0000
  12.750   1.1682   0.05923   0.05032  -0.0097   0.1332   1.0000
  13.000   1.1726   0.06130   0.05234  -0.0092   0.1269   1.0000
  13.250   1.1624   0.06545   0.05681  -0.0094   0.1216   1.0000
  13.500   1.1595   0.06873   0.06020  -0.0096   0.1164   1.0000
  13.750   1.1590   0.07185   0.06337  -0.0097   0.1117   1.0000
  14.000   1.1442   0.07718   0.06901  -0.0111   0.1081   1.0000
  14.250   1.1342   0.08199   0.07399  -0.0125   0.1045   1.0000
  14.500   1.1459   0.08352   0.07541  -0.0121   0.1001   1.0000
  14.750   1.1194   0.09132   0.08356  -0.0154   0.0984   1.0000
  15.000   1.0854   0.10115   0.09369  -0.0203   0.0973   1.0000
  15.250   1.0303   0.11649   0.10929  -0.0291   0.0969   1.0000
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