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RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il)
Reynolds number: 50,000
Max Cl/Cd: 29.15 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15a213-il-50000.txt
Download as CSV file: xf-rg15a213-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3831   0.11742   0.11020  -0.0253   1.0000   0.2755
  -9.750  -0.3606   0.11243   0.10517  -0.0241   1.0000   0.2845
  -9.500  -0.3844   0.11149   0.10440  -0.0244   1.0000   0.2926
  -9.250  -0.3586   0.10649   0.09935  -0.0232   1.0000   0.3008
  -9.000  -0.3748   0.10456   0.09756  -0.0229   1.0000   0.3094
  -8.750  -0.3627   0.10113   0.09414  -0.0217   1.0000   0.3205
  -8.500  -0.3589   0.09783   0.09090  -0.0206   1.0000   0.3301
  -8.250  -0.4918   0.08091   0.07444  -0.0402   1.0000   0.1638
  -8.000  -0.5774   0.07004   0.06343  -0.0452   1.0000   0.1367
  -7.750  -0.5806   0.06610   0.05943  -0.0438   1.0000   0.1352
  -7.500  -0.5871   0.06208   0.05531  -0.0425   1.0000   0.1343
  -7.250  -0.5917   0.05804   0.05110  -0.0412   1.0000   0.1332
  -7.000  -0.5945   0.05387   0.04665  -0.0401   1.0000   0.1325
  -6.750  -0.5931   0.04975   0.04215  -0.0391   1.0000   0.1323
  -6.500  -0.5869   0.04581   0.03772  -0.0381   1.0000   0.1325
  -6.250  -0.5765   0.04221   0.03353  -0.0372   1.0000   0.1346
  -6.000  -0.5618   0.03966   0.03083  -0.0361   1.0000   0.1404
  -5.750  -0.5452   0.03730   0.02809  -0.0350   1.0000   0.1485
  -5.500  -0.5269   0.03502   0.02563  -0.0340   1.0000   0.1580
  -5.250  -0.5079   0.03316   0.02360  -0.0330   1.0000   0.1736
  -5.000  -0.4883   0.03157   0.02180  -0.0320   1.0000   0.1949
  -4.750  -0.4700   0.03043   0.02076  -0.0308   1.0000   0.2216
  -4.500  -0.4509   0.02928   0.01963  -0.0297   1.0000   0.2500
  -4.250  -0.4306   0.02813   0.01845  -0.0286   1.0000   0.2783
  -4.000  -0.4109   0.02712   0.01753  -0.0275   1.0000   0.3099
  -3.750  -0.3919   0.02618   0.01680  -0.0261   1.0000   0.3476
  -3.500  -0.3733   0.02527   0.01617  -0.0247   1.0000   0.3985
  -3.250  -0.3563   0.02442   0.01580  -0.0226   1.0000   0.4701
  -3.000  -0.3445   0.02409   0.01615  -0.0189   1.0000   0.5608
  -2.750  -0.3384   0.02440   0.01686  -0.0133   1.0000   0.6534
  -2.500  -0.3362   0.02480   0.01744  -0.0068   1.0000   0.7294
  -2.250  -0.3366   0.02506   0.01777   0.0002   1.0000   0.7930
  -2.000  -0.3367   0.02516   0.01790   0.0071   1.0000   0.8538
  -1.750  -0.3046   0.02569   0.01831   0.0086   1.0000   0.9305
  -1.500  -0.1359   0.02762   0.01943  -0.0171   1.0000   1.0000
  -1.250  -0.1487   0.02713   0.01888  -0.0137   1.0000   1.0000
  -1.000  -0.1590   0.02668   0.01835  -0.0104   1.0000   1.0000
  -0.750  -0.1644   0.02636   0.01793  -0.0078   1.0000   1.0000
  -0.500  -0.1272   0.02714   0.01848  -0.0123   0.9889   1.0000
  -0.250  -0.0804   0.02818   0.01927  -0.0181   0.9735   1.0000
   0.000  -0.0347   0.02916   0.02003  -0.0234   0.9584   1.0000
   0.250   0.0089   0.03004   0.02072  -0.0280   0.9433   1.0000
   0.500   0.0483   0.03080   0.02132  -0.0317   0.9278   1.0000
   0.750   0.0876   0.03155   0.02193  -0.0352   0.9122   1.0000
   1.000   0.1265   0.03229   0.02254  -0.0384   0.8969   1.0000
   1.250   0.1645   0.03298   0.02313  -0.0412   0.8814   1.0000
   1.500   0.2022   0.03365   0.02371  -0.0439   0.8660   1.0000
   1.750   0.2391   0.03429   0.02429  -0.0462   0.8505   1.0000
   2.000   0.2757   0.03489   0.02483  -0.0483   0.8350   1.0000
   2.250   0.3122   0.03545   0.02535  -0.0503   0.8195   1.0000
   2.500   0.3497   0.03595   0.02583  -0.0522   0.8044   1.0000
   2.750   0.3850   0.03642   0.02630  -0.0537   0.7889   1.0000
   3.000   0.4186   0.03688   0.02676  -0.0548   0.7733   1.0000
   3.250   0.4524   0.03728   0.02717  -0.0557   0.7577   1.0000
   3.500   0.4858   0.03764   0.02756  -0.0565   0.7422   1.0000
   3.750   0.5195   0.03793   0.02789  -0.0571   0.7267   1.0000
   4.000   0.5537   0.03813   0.02815  -0.0577   0.7112   1.0000
   4.250   0.5889   0.03821   0.02828  -0.0581   0.6958   1.0000
   4.500   0.6245   0.03823   0.02837  -0.0586   0.6803   1.0000
   4.750   0.6618   0.03813   0.02837  -0.0590   0.6648   1.0000
   5.000   0.6985   0.03795   0.02827  -0.0591   0.6491   1.0000
   5.250   0.7357   0.03768   0.02809  -0.0592   0.6333   1.0000
   5.500   0.7748   0.03724   0.02775  -0.0593   0.6173   1.0000
   5.750   0.8164   0.03663   0.02722  -0.0596   0.6010   1.0000
   6.000   0.8594   0.03592   0.02660  -0.0599   0.5841   1.0000
   6.250   0.8731   0.03689   0.02765  -0.0578   0.5651   1.0000
   6.500   0.8983   0.03720   0.02804  -0.0566   0.5463   1.0000
   6.750   0.9312   0.03706   0.02798  -0.0560   0.5275   1.0000
   7.000   0.9717   0.03647   0.02741  -0.0560   0.5081   1.0000
   7.250   1.0052   0.03639   0.02734  -0.0555   0.4885   1.0000
   7.500   1.0203   0.03733   0.02839  -0.0534   0.4688   1.0000
   7.750   1.0459   0.03770   0.02880  -0.0522   0.4486   1.0000
   8.000   1.0868   0.03728   0.02826  -0.0524   0.4273   1.0000
   8.250   1.0977   0.03852   0.02963  -0.0499   0.4080   1.0000
   8.500   1.1148   0.03946   0.03066  -0.0480   0.3885   1.0000
   8.750   1.1399   0.04001   0.03118  -0.0469   0.3685   1.0000
   9.000   1.1680   0.04057   0.03165  -0.0462   0.3487   1.0000
   9.250   1.1791   0.04201   0.03324  -0.0438   0.3314   1.0000
   9.500   1.1917   0.04348   0.03480  -0.0417   0.3147   1.0000
   9.750   1.2046   0.04501   0.03642  -0.0397   0.2986   1.0000
  10.000   1.2168   0.04656   0.03805  -0.0377   0.2830   1.0000
  10.250   1.2291   0.04826   0.03982  -0.0357   0.2686   1.0000
  10.500   1.2409   0.04987   0.04148  -0.0337   0.2541   1.0000
  10.750   1.2534   0.05146   0.04312  -0.0319   0.2400   1.0000
  11.000   1.2665   0.05297   0.04463  -0.0301   0.2260   1.0000
  11.250   1.2412   0.05651   0.04856  -0.0255   0.2208   1.0000
  11.500   1.2506   0.05832   0.05038  -0.0236   0.2094   1.0000
  11.750   1.2169   0.06240   0.05475  -0.0191   0.2072   1.0000
  12.000   1.1740   0.06798   0.06056  -0.0161   0.2074   1.0000
  12.250   1.1198   0.07605   0.06879  -0.0157   0.2100   1.0000
  12.500   1.0644   0.08663   0.07942  -0.0185   0.2122   1.0000
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