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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 100,000
Max Cl/Cd: 52.06 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15-il-100000.txt
Download as CSV file: xf-rg15-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4676   0.10268   0.09767  -0.0221   1.0000   0.0962
  -9.000  -0.4828   0.09964   0.09475  -0.0268   1.0000   0.0985
  -8.750  -0.5052   0.09647   0.09172  -0.0324   1.0000   0.0991
  -8.500  -0.4662   0.09231   0.08746  -0.0244   1.0000   0.1069
  -8.250  -0.4759   0.08900   0.08426  -0.0269   1.0000   0.1107
  -8.000  -0.5005   0.08558   0.08099  -0.0314   1.0000   0.1121
  -7.750  -0.4814   0.08225   0.07766  -0.0268   1.0000   0.1186
  -7.500  -0.4928   0.07871   0.07421  -0.0294   1.0000   0.1236
  -7.250  -0.5140   0.07419   0.06964  -0.0365   1.0000   0.1261
  -7.000  -0.4618   0.05934   0.05521  -0.0349   1.0000   0.1416
  -6.750  -0.4403   0.05644   0.05235  -0.0300   1.0000   0.1469
  -6.500  -0.4701   0.05165   0.04747  -0.0345   1.0000   0.1553
  -6.250  -0.5035   0.05976   0.05519  -0.0351   1.0000   0.1567
  -5.750  -0.4901   0.05388   0.04910  -0.0342   1.0000   0.1812
  -5.500  -0.4669   0.03684   0.03036  -0.0392   1.0000   0.0680
  -5.250  -0.4460   0.03277   0.02515  -0.0376   1.0000   0.0594
  -5.000  -0.4258   0.02938   0.02129  -0.0365   1.0000   0.0590
  -4.750  -0.4062   0.02647   0.01828  -0.0359   1.0000   0.0637
  -4.500  -0.3836   0.02456   0.01606  -0.0349   1.0000   0.0674
  -4.250  -0.3593   0.02264   0.01375  -0.0337   1.0000   0.0699
  -4.000  -0.3363   0.02100   0.01200  -0.0328   1.0000   0.0767
  -3.750  -0.3127   0.01984   0.01068  -0.0317   1.0000   0.0842
  -3.500  -0.2896   0.01843   0.00937  -0.0307   1.0000   0.0933
  -3.250  -0.2667   0.01735   0.00833  -0.0297   1.0000   0.1135
  -3.000  -0.2440   0.01578   0.00725  -0.0290   1.0000   0.1829
  -2.750  -0.2255   0.01350   0.00681  -0.0282   1.0000   0.4973
  -2.500  -0.2179   0.01316   0.00729  -0.0228   1.0000   0.7251
  -2.250  -0.2094   0.01321   0.00745  -0.0178   1.0000   0.8072
  -2.000  -0.2016   0.01322   0.00750  -0.0127   1.0000   0.8695
  -1.750  -0.1734   0.01323   0.00746  -0.0116   1.0000   0.9472
  -1.500  -0.1216   0.01323   0.00716  -0.0170   1.0000   1.0000
  -1.250  -0.1067   0.01324   0.00699  -0.0163   1.0000   1.0000
  -1.000  -0.0872   0.01338   0.00695  -0.0163   1.0000   1.0000
  -0.750  -0.0665   0.01361   0.00701  -0.0163   1.0000   1.0000
  -0.500  -0.0268   0.01408   0.00727  -0.0198   0.9941   1.0000
  -0.250   0.0247   0.01456   0.00759  -0.0253   0.9834   1.0000
   0.000   0.0736   0.01491   0.00782  -0.0302   0.9717   1.0000
   0.250   0.1214   0.01517   0.00797  -0.0346   0.9595   1.0000
   0.500   0.1683   0.01534   0.00807  -0.0388   0.9469   1.0000
   0.750   0.2149   0.01543   0.00812  -0.0427   0.9342   1.0000
   1.000   0.2616   0.01544   0.00811  -0.0464   0.9214   1.0000
   1.250   0.3089   0.01536   0.00804  -0.0501   0.9087   1.0000
   1.500   0.3588   0.01514   0.00786  -0.0540   0.8966   1.0000
   1.750   0.4059   0.01487   0.00763  -0.0572   0.8835   1.0000
   2.000   0.4482   0.01459   0.00740  -0.0593   0.8682   1.0000
   2.250   0.4879   0.01430   0.00719  -0.0607   0.8513   1.0000
   2.500   0.5262   0.01402   0.00695  -0.0618   0.8334   1.0000
   2.750   0.5571   0.01388   0.00683  -0.0615   0.8110   1.0000
   3.000   0.5891   0.01373   0.00669  -0.0613   0.7887   1.0000
   3.250   0.6168   0.01370   0.00669  -0.0604   0.7628   1.0000
   3.500   0.6432   0.01374   0.00671  -0.0593   0.7351   1.0000
   3.750   0.6689   0.01383   0.00676  -0.0581   0.7060   1.0000
   4.000   0.6930   0.01399   0.00689  -0.0568   0.6742   1.0000
   4.250   0.7168   0.01419   0.00708  -0.0554   0.6411   1.0000
   4.500   0.7406   0.01444   0.00723  -0.0540   0.6075   1.0000
   4.750   0.7629   0.01474   0.00749  -0.0525   0.5703   1.0000
   5.000   0.7850   0.01509   0.00775  -0.0510   0.5321   1.0000
   5.250   0.8064   0.01549   0.00806  -0.0494   0.4922   1.0000
   5.500   0.8271   0.01596   0.00847  -0.0478   0.4497   1.0000
   5.750   0.8469   0.01650   0.00890  -0.0461   0.4043   1.0000
   6.000   0.8657   0.01716   0.00938  -0.0444   0.3567   1.0000
   6.250   0.8835   0.01794   0.00999  -0.0427   0.3049   1.0000
   6.500   0.9004   0.01893   0.01073  -0.0409   0.2535   1.0000
   6.750   0.9170   0.02013   0.01169  -0.0392   0.2065   1.0000
   7.000   0.9336   0.02151   0.01284  -0.0375   0.1669   1.0000
   7.250   0.9509   0.02304   0.01423  -0.0359   0.1371   1.0000
   7.500   0.9690   0.02460   0.01573  -0.0344   0.1126   1.0000
   7.750   0.9869   0.02638   0.01745  -0.0331   0.0923   1.0000
   8.000   1.0037   0.02797   0.01907  -0.0315   0.0737   1.0000
   8.250   1.0217   0.03013   0.02124  -0.0301   0.0601   1.0000
   8.500   1.0404   0.03245   0.02375  -0.0288   0.0508   1.0000
   8.750   1.0609   0.03593   0.02723  -0.0281   0.0456   1.0000
   9.000   1.0781   0.03889   0.03073  -0.0263   0.0436   1.0000
   9.250   1.0906   0.04239   0.03480  -0.0242   0.0423   1.0000
   9.500   1.0978   0.04624   0.03917  -0.0219   0.0418   1.0000
   9.750   1.0995   0.05026   0.04367  -0.0194   0.0417   1.0000
  10.000   1.0956   0.05430   0.04815  -0.0167   0.0415   1.0000
  10.250   1.0864   0.05830   0.05254  -0.0141   0.0416   1.0000
  10.500   1.0711   0.06206   0.05660  -0.0113   0.0417   1.0000
  10.750   1.0517   0.06595   0.06073  -0.0090   0.0422   1.0000
  11.000   1.0304   0.07017   0.06516  -0.0080   0.0425   1.0000
  11.250   1.0084   0.07511   0.07028  -0.0087   0.0431   1.0000
  11.500   0.9878   0.08074   0.07604  -0.0109   0.0439   1.0000
  11.750   0.9681   0.08709   0.08249  -0.0142   0.0446   1.0000
  12.000   0.9479   0.09440   0.08988  -0.0187   0.0451   1.0000
  12.250   0.9385   0.10144   0.09692  -0.0214   0.0459   1.0000
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