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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 200,000
Max Cl/Cd: 68.75 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15-il-200000.txt
Download as CSV file: xf-rg15-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4922   0.08612   0.08270  -0.0383   1.0000   0.0465
  -8.500  -0.5059   0.08177   0.07836  -0.0415   1.0000   0.0466
  -8.250  -0.5165   0.07774   0.07428  -0.0434   1.0000   0.0466
  -8.000  -0.5200   0.07136   0.06803  -0.0423   1.0000   0.0479
  -7.750  -0.5148   0.06906   0.06578  -0.0403   1.0000   0.0490
  -7.500  -0.5140   0.06614   0.06286  -0.0398   1.0000   0.0502
  -7.250  -0.5150   0.06263   0.05932  -0.0402   1.0000   0.0512
  -7.000  -0.5157   0.05887   0.05549  -0.0405   1.0000   0.0531
  -6.750  -0.5150   0.05491   0.05138  -0.0408   1.0000   0.0554
  -6.500  -0.5228   0.04987   0.04564  -0.0415   1.0000   0.0601
  -6.250  -0.5121   0.04601   0.04192  -0.0405   1.0000   0.0616
  -6.000  -0.5010   0.04339   0.03929  -0.0392   1.0000   0.0635
  -5.750  -0.4887   0.03212   0.02678  -0.0372   1.0000   0.0333
  -5.500  -0.4734   0.02778   0.02198  -0.0361   1.0000   0.0312
  -5.250  -0.4539   0.02449   0.01819  -0.0348   1.0000   0.0305
  -5.000  -0.4326   0.02292   0.01625  -0.0336   1.0000   0.0331
  -4.750  -0.4101   0.02133   0.01424  -0.0324   1.0000   0.0344
  -4.500  -0.3867   0.01906   0.01164  -0.0314   1.0000   0.0355
  -4.250  -0.3635   0.01719   0.00969  -0.0307   1.0000   0.0384
  -4.000  -0.3410   0.01664   0.00908  -0.0299   1.0000   0.0440
  -3.750  -0.3179   0.01572   0.00805  -0.0289   1.0000   0.0474
  -3.500  -0.2955   0.01481   0.00719  -0.0283   1.0000   0.0540
  -3.250  -0.2729   0.01414   0.00648  -0.0275   1.0000   0.0615
  -3.000  -0.2438   0.01334   0.00576  -0.0281   0.9985   0.0841
  -2.750  -0.2048   0.01208   0.00527  -0.0313   0.9944   0.2364
  -2.500  -0.1690   0.01099   0.00516  -0.0339   0.9890   0.4661
  -2.250  -0.1341   0.01055   0.00554  -0.0351   0.9834   0.6904
  -2.000  -0.1010   0.01050   0.00563  -0.0356   0.9754   0.7624
  -1.750  -0.0620   0.01053   0.00566  -0.0374   0.9697   0.8055
  -1.500  -0.0312   0.01044   0.00559  -0.0374   0.9603   0.8406
  -1.250   0.0020   0.01037   0.00551  -0.0378   0.9525   0.8722
  -1.000   0.0366   0.01024   0.00536  -0.0385   0.9451   0.8989
  -0.750   0.0702   0.01011   0.00522  -0.0390   0.9368   0.9246
  -0.500   0.1164   0.00997   0.00504  -0.0421   0.9319   0.9473
  -0.250   0.1719   0.00982   0.00483  -0.0473   0.9293   0.9631
   0.000   0.2226   0.00968   0.00465  -0.0517   0.9216   0.9772
   0.250   0.2798   0.00945   0.00439  -0.0574   0.9166   0.9856
   0.500   0.3320   0.00924   0.00415  -0.0623   0.9066   0.9944
   0.750   0.3788   0.00899   0.00388  -0.0661   0.8939   1.0000
   1.000   0.4087   0.00878   0.00364  -0.0665   0.8761   1.0000
   1.250   0.4333   0.00866   0.00347  -0.0658   0.8558   1.0000
   1.500   0.4560   0.00861   0.00334  -0.0647   0.8344   1.0000
   1.750   0.4779   0.00861   0.00328  -0.0634   0.8119   1.0000
   2.000   0.5015   0.00866   0.00325  -0.0624   0.7895   1.0000
   2.250   0.5245   0.00876   0.00326  -0.0612   0.7649   1.0000
   2.500   0.5485   0.00887   0.00329  -0.0603   0.7396   1.0000
   2.750   0.5727   0.00902   0.00334  -0.0593   0.7134   1.0000
   3.000   0.5969   0.00919   0.00345  -0.0584   0.6860   1.0000
   3.250   0.6211   0.00939   0.00355  -0.0575   0.6575   1.0000
   3.500   0.6450   0.00961   0.00367  -0.0566   0.6278   1.0000
   3.750   0.6689   0.00986   0.00382  -0.0556   0.5972   1.0000
   4.000   0.6925   0.01013   0.00398  -0.0547   0.5655   1.0000
   4.250   0.7159   0.01042   0.00422  -0.0537   0.5315   1.0000
   4.500   0.7391   0.01075   0.00444  -0.0528   0.4972   1.0000
   4.750   0.7621   0.01110   0.00469  -0.0518   0.4617   1.0000
   5.000   0.7847   0.01150   0.00498  -0.0508   0.4247   1.0000
   5.250   0.8070   0.01193   0.00529  -0.0498   0.3849   1.0000
   5.500   0.8289   0.01242   0.00568  -0.0488   0.3425   1.0000
   5.750   0.8504   0.01297   0.00608  -0.0478   0.2997   1.0000
   6.000   0.8719   0.01358   0.00654  -0.0468   0.2560   1.0000
   6.250   0.8927   0.01428   0.00708  -0.0458   0.2105   1.0000
   6.500   0.9129   0.01510   0.00772  -0.0448   0.1681   1.0000
   6.750   0.9323   0.01606   0.00848  -0.0436   0.1320   1.0000
   7.000   0.9515   0.01706   0.00940  -0.0423   0.1026   1.0000
   7.250   0.9712   0.01798   0.01021  -0.0413   0.0787   1.0000
   7.500   0.9909   0.01890   0.01105  -0.0402   0.0595   1.0000
   7.750   1.0078   0.02021   0.01237  -0.0386   0.0436   1.0000
   8.000   1.0218   0.02195   0.01415  -0.0364   0.0326   1.0000
   8.250   1.0382   0.02343   0.01570  -0.0346   0.0277   1.0000
   8.500   1.0510   0.02615   0.01848  -0.0326   0.0246   1.0000
   8.750   1.0709   0.02719   0.01972  -0.0313   0.0222   1.0000
   9.000   1.0890   0.02899   0.02173  -0.0300   0.0208   1.0000
   9.250   1.1063   0.03102   0.02395  -0.0286   0.0198   1.0000
   9.500   1.1220   0.03330   0.02645  -0.0271   0.0191   1.0000
   9.750   1.1353   0.03593   0.02933  -0.0255   0.0186   1.0000
  10.000   1.1450   0.03899   0.03272  -0.0236   0.0184   1.0000
  10.250   1.1498   0.04228   0.03639  -0.0212   0.0184   1.0000
  10.500   1.1480   0.04588   0.04041  -0.0183   0.0187   1.0000
  10.750   1.1366   0.04981   0.04476  -0.0145   0.0192   1.0000
  11.000   1.1139   0.05396   0.04932  -0.0107   0.0197   1.0000
  11.250   1.0898   0.05842   0.05411  -0.0084   0.0202   1.0000
  11.500   1.0663   0.06327   0.05923  -0.0080   0.0206   1.0000
  11.750   1.0435   0.06862   0.06481  -0.0093   0.0209   1.0000
  12.000   1.0199   0.07489   0.07127  -0.0124   0.0211   1.0000
  12.250   0.9950   0.08247   0.07904  -0.0173   0.0214   1.0000
  12.500   0.9698   0.09151   0.08822  -0.0240   0.0216   1.0000
  12.750   0.9423   0.10283   0.09966  -0.0324   0.0219   1.0000
  13.000   0.9109   0.11744   0.11432  -0.0418   0.0227   1.0000
  13.250   0.8896   0.12970   0.12651  -0.0482   0.0237   1.0000
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