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RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
Reynolds number: 50,000
Max Cl/Cd: 35.08 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15a111-il-50000-n5.txt
Download as CSV file: xf-rg15a111-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 15A-1.8/11.0 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  -0.4980   0.10791   0.10048  -0.0331   1.0000   0.0500
 -10.750  -0.4993   0.10318   0.09580  -0.0347   1.0000   0.0497
 -10.500  -0.5022   0.09825   0.09094  -0.0366   1.0000   0.0495
 -10.250  -0.5071   0.09294   0.08569  -0.0389   1.0000   0.0493
 -10.000  -0.5148   0.08697   0.07979  -0.0420   1.0000   0.0490
  -9.750  -0.5258   0.08064   0.07352  -0.0457   1.0000   0.0486
  -9.500  -0.5419   0.07484   0.06775  -0.0490   1.0000   0.0482
  -9.250  -0.5627   0.07004   0.06298  -0.0508   1.0000   0.0479
  -9.000  -0.5833   0.06598   0.05889  -0.0506   1.0000   0.0476
  -8.750  -0.6002   0.06182   0.05461  -0.0502   1.0000   0.0474
  -8.500  -0.6128   0.05776   0.05036  -0.0492   1.0000   0.0475
  -8.250  -0.6216   0.05375   0.04604  -0.0479   1.0000   0.0480
  -8.000  -0.6261   0.04985   0.04171  -0.0463   1.0000   0.0491
  -7.750  -0.6252   0.04629   0.03770  -0.0446   1.0000   0.0504
  -7.500  -0.6152   0.04406   0.03541  -0.0433   1.0000   0.0525
  -7.250  -0.6047   0.04160   0.03271  -0.0417   1.0000   0.0544
  -7.000  -0.5925   0.03890   0.02962  -0.0402   1.0000   0.0561
  -6.750  -0.5780   0.03635   0.02667  -0.0386   1.0000   0.0582
  -6.500  -0.5613   0.03413   0.02391  -0.0370   1.0000   0.0618
  -6.250  -0.5448   0.03258   0.02240  -0.0357   1.0000   0.0663
  -6.000  -0.5263   0.03096   0.02055  -0.0343   1.0000   0.0715
  -5.750  -0.5068   0.02930   0.01868  -0.0327   1.0000   0.0764
  -5.500  -0.4884   0.02808   0.01739  -0.0312   1.0000   0.0846
  -5.250  -0.4701   0.02694   0.01623  -0.0298   1.0000   0.0961
  -5.000  -0.4516   0.02586   0.01511  -0.0284   1.0000   0.1114
  -4.750  -0.4334   0.02491   0.01420  -0.0271   1.0000   0.1341
  -4.500  -0.4151   0.02401   0.01339  -0.0259   1.0000   0.1627
  -4.250  -0.3963   0.02311   0.01260  -0.0248   1.0000   0.1948
  -4.000  -0.3770   0.02226   0.01190  -0.0239   1.0000   0.2367
  -3.750  -0.3584   0.02147   0.01133  -0.0229   1.0000   0.2907
  -3.500  -0.3404   0.02070   0.01092  -0.0217   1.0000   0.3621
  -3.250  -0.3237   0.02006   0.01075  -0.0200   1.0000   0.4536
  -3.000  -0.3099   0.01975   0.01094  -0.0169   1.0000   0.5536
  -2.750  -0.2963   0.01976   0.01111  -0.0137   1.0000   0.6395
  -2.500  -0.2725   0.01997   0.01133  -0.0124   0.9945   0.7096
  -2.250  -0.2422   0.02023   0.01153  -0.0121   0.9847   0.7672
  -2.000  -0.2124   0.02043   0.01166  -0.0116   0.9747   0.8144
  -1.750  -0.1797   0.02059   0.01170  -0.0118   0.9651   0.8571
  -1.500  -0.1366   0.02078   0.01174  -0.0140   0.9572   0.8974
  -1.250  -0.0843   0.02091   0.01168  -0.0184   0.9493   0.9314
  -1.000  -0.0181   0.02107   0.01162  -0.0259   0.9439   0.9597
  -0.750   0.0456   0.02110   0.01145  -0.0333   0.9364   0.9829
  -0.500   0.1067   0.02109   0.01127  -0.0405   0.9292   1.0000
  -0.250   0.1392   0.02101   0.01109  -0.0423   0.9155   1.0000
   0.000   0.1715   0.02094   0.01093  -0.0439   0.9018   1.0000
   0.250   0.2042   0.02087   0.01079  -0.0454   0.8882   1.0000
   0.500   0.2372   0.02080   0.01065  -0.0468   0.8747   1.0000
   0.750   0.2686   0.02072   0.01053  -0.0478   0.8608   1.0000
   1.000   0.2993   0.02066   0.01042  -0.0484   0.8466   1.0000
   1.250   0.3295   0.02062   0.01034  -0.0489   0.8321   1.0000
   1.500   0.3595   0.02058   0.01027  -0.0493   0.8173   1.0000
   1.750   0.3895   0.02055   0.01022  -0.0495   0.8021   1.0000
   2.000   0.4194   0.02052   0.01020  -0.0496   0.7865   1.0000
   2.250   0.4491   0.02050   0.01017  -0.0497   0.7705   1.0000
   2.500   0.4790   0.02048   0.01015  -0.0496   0.7540   1.0000
   2.750   0.5076   0.02050   0.01018  -0.0493   0.7368   1.0000
   3.000   0.5327   0.02060   0.01030  -0.0485   0.7175   1.0000
   3.250   0.5598   0.02067   0.01037  -0.0480   0.6984   1.0000
   3.500   0.5882   0.02072   0.01045  -0.0475   0.6796   1.0000
   3.750   0.6125   0.02089   0.01064  -0.0466   0.6582   1.0000
   4.000   0.6388   0.02102   0.01077  -0.0458   0.6372   1.0000
   4.250   0.6634   0.02122   0.01098  -0.0448   0.6148   1.0000
   4.500   0.6887   0.02141   0.01120  -0.0439   0.5923   1.0000
   4.750   0.7120   0.02168   0.01150  -0.0428   0.5682   1.0000
   5.000   0.7362   0.02195   0.01175  -0.0417   0.5443   1.0000
   5.250   0.7591   0.02229   0.01209  -0.0406   0.5192   1.0000
   5.500   0.7812   0.02267   0.01252  -0.0393   0.4934   1.0000
   5.750   0.8031   0.02310   0.01294  -0.0381   0.4675   1.0000
   6.000   0.8245   0.02356   0.01338  -0.0368   0.4416   1.0000
   6.250   0.8450   0.02409   0.01390  -0.0354   0.4151   1.0000
   6.500   0.8643   0.02468   0.01450  -0.0339   0.3879   1.0000
   6.750   0.8831   0.02533   0.01518  -0.0325   0.3608   1.0000
   7.000   0.9012   0.02604   0.01588  -0.0309   0.3342   1.0000
   7.250   0.9186   0.02682   0.01663  -0.0294   0.3085   1.0000
   7.500   0.9352   0.02766   0.01745  -0.0278   0.2836   1.0000
   7.750   0.9514   0.02861   0.01842  -0.0263   0.2592   1.0000
   8.000   0.9666   0.02962   0.01945  -0.0246   0.2367   1.0000
   8.250   0.9815   0.03073   0.02058  -0.0230   0.2153   1.0000
   8.500   0.9948   0.03191   0.02170  -0.0213   0.1960   1.0000
   8.750   1.0082   0.03319   0.02306  -0.0197   0.1773   1.0000
   9.000   1.0202   0.03453   0.02444  -0.0180   0.1606   1.0000
   9.250   1.0318   0.03596   0.02590  -0.0163   0.1461   1.0000
   9.500   1.0424   0.03746   0.02750  -0.0146   0.1331   1.0000
   9.750   1.0526   0.03905   0.02916  -0.0128   0.1223   1.0000
  10.000   1.0623   0.04069   0.03075  -0.0111   0.1133   1.0000
  10.250   1.0710   0.04250   0.03281  -0.0093   0.1040   1.0000
  10.500   1.0811   0.04448   0.03490  -0.0079   0.0969   1.0000
  10.750   1.0901   0.04654   0.03713  -0.0064   0.0905   1.0000
  11.000   1.0976   0.04874   0.03943  -0.0050   0.0851   1.0000
  11.250   1.1000   0.05119   0.04218  -0.0035   0.0798   1.0000
  11.500   1.1077   0.05342   0.04447  -0.0024   0.0759   1.0000
  11.750   1.1084   0.05652   0.04785  -0.0013   0.0727   1.0000
  12.000   1.1015   0.06000   0.05170  -0.0003   0.0699   1.0000
  12.250   1.0945   0.06346   0.05539   0.0001   0.0672   1.0000
  12.500   1.0906   0.06663   0.05868   0.0003   0.0647   1.0000
  12.750   1.0928   0.06981   0.06185   0.0004   0.0624   1.0000
  13.000   1.0741   0.07516   0.06754  -0.0008   0.0619   1.0000
  13.250   1.0522   0.08136   0.07402  -0.0032   0.0615   1.0000
  13.500   1.0281   0.08850   0.08140  -0.0067   0.0615   1.0000
  13.750   1.0018   0.09675   0.08983  -0.0114   0.0618   1.0000
  14.000   0.9731   0.10641   0.09964  -0.0173   0.0621   1.0000
  14.250   0.9438   0.11736   0.11063  -0.0241   0.0625   1.0000
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