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RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
Reynolds number: 100,000
Max Cl/Cd: 49.45 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15a111-il-100000-n5.txt
Download as CSV file: xf-rg15a111-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5178   0.08836   0.08321  -0.0375   1.0000   0.0272
 -10.250  -0.5343   0.08020   0.07513  -0.0419   1.0000   0.0268
 -10.000  -0.5756   0.06607   0.06098  -0.0523   1.0000   0.0257
  -9.750  -0.6151   0.05864   0.05343  -0.0564   1.0000   0.0251
  -9.500  -0.6473   0.05438   0.04901  -0.0550   1.0000   0.0248
  -9.250  -0.6666   0.05041   0.04480  -0.0533   1.0000   0.0247
  -9.000  -0.6776   0.04681   0.04093  -0.0512   1.0000   0.0248
  -8.750  -0.6814   0.04364   0.03747  -0.0491   1.0000   0.0252
  -8.500  -0.6811   0.04063   0.03413  -0.0470   1.0000   0.0255
  -8.250  -0.6766   0.03786   0.03102  -0.0449   1.0000   0.0262
  -8.000  -0.6688   0.03534   0.02815  -0.0429   1.0000   0.0270
  -7.750  -0.6579   0.03315   0.02558  -0.0410   1.0000   0.0285
  -7.500  -0.6446   0.03119   0.02315  -0.0392   1.0000   0.0301
  -7.250  -0.6305   0.02925   0.02109  -0.0377   1.0000   0.0314
  -7.000  -0.6143   0.02777   0.01948  -0.0361   1.0000   0.0327
  -6.500  -0.5793   0.02531   0.01666  -0.0332   1.0000   0.0368
  -6.250  -0.5606   0.02427   0.01539  -0.0317   1.0000   0.0394
  -6.000  -0.5433   0.02304   0.01416  -0.0304   1.0000   0.0418
  -5.750  -0.5249   0.02212   0.01318  -0.0290   1.0000   0.0445
  -5.500  -0.5059   0.02128   0.01222  -0.0277   1.0000   0.0484
  -5.250  -0.4793   0.02043   0.01135  -0.0281   0.9975   0.0552
  -5.000  -0.4452   0.01955   0.01042  -0.0298   0.9925   0.0660
  -4.750  -0.4115   0.01876   0.00963  -0.0315   0.9868   0.0834
  -4.500  -0.3768   0.01813   0.00908  -0.0334   0.9815   0.1097
  -4.250  -0.3442   0.01753   0.00864  -0.0349   0.9748   0.1485
  -4.000  -0.3096   0.01694   0.00824  -0.0369   0.9692   0.1946
  -3.750  -0.2783   0.01638   0.00785  -0.0380   0.9615   0.2456
  -3.500  -0.2437   0.01580   0.00753  -0.0398   0.9557   0.3121
  -3.250  -0.2138   0.01524   0.00724  -0.0405   0.9475   0.3903
  -3.000  -0.1811   0.01469   0.00712  -0.0416   0.9412   0.4900
  -2.750  -0.1525   0.01440   0.00717  -0.0413   0.9327   0.5837
  -2.500  -0.1199   0.01430   0.00714  -0.0418   0.9256   0.6497
  -2.250  -0.0882   0.01424   0.00708  -0.0420   0.9175   0.6930
  -2.000  -0.0564   0.01419   0.00702  -0.0422   0.9096   0.7263
  -1.750  -0.0238   0.01413   0.00691  -0.0426   0.9018   0.7544
  -1.500   0.0055   0.01408   0.00683  -0.0423   0.8921   0.7789
  -1.250   0.0395   0.01399   0.00670  -0.0428   0.8850   0.8002
  -1.000   0.0669   0.01393   0.00660  -0.0422   0.8738   0.8198
  -0.750   0.0963   0.01385   0.00649  -0.0419   0.8633   0.8385
  -0.500   0.1286   0.01374   0.00635  -0.0421   0.8540   0.8556
  -0.250   0.1585   0.01366   0.00623  -0.0419   0.8425   0.8720
   0.000   0.1886   0.01358   0.00613  -0.0418   0.8301   0.8880
   0.250   0.2211   0.01351   0.00602  -0.0422   0.8177   0.9032
   0.500   0.2559   0.01343   0.00590  -0.0431   0.8048   0.9170
   0.750   0.2921   0.01336   0.00579  -0.0445   0.7909   0.9299
   1.000   0.3293   0.01331   0.00570  -0.0461   0.7760   0.9422
   1.250   0.3688   0.01327   0.00562  -0.0482   0.7600   0.9525
   1.500   0.4080   0.01323   0.00554  -0.0504   0.7429   0.9624
   1.750   0.4463   0.01322   0.00548  -0.0524   0.7251   0.9725
   2.000   0.4842   0.01322   0.00544  -0.0544   0.7059   0.9830
   2.250   0.5223   0.01325   0.00542  -0.0566   0.6850   0.9934
   2.500   0.5503   0.01331   0.00543  -0.0568   0.6650   1.0000
   2.750   0.5682   0.01342   0.00548  -0.0550   0.6449   1.0000
   3.000   0.5877   0.01355   0.00555  -0.0534   0.6243   1.0000
   3.250   0.6089   0.01372   0.00565  -0.0521   0.6033   1.0000
   3.500   0.6307   0.01391   0.00578  -0.0510   0.5810   1.0000
   3.750   0.6532   0.01413   0.00592  -0.0499   0.5587   1.0000
   4.000   0.6759   0.01437   0.00610  -0.0489   0.5355   1.0000
   4.250   0.6987   0.01464   0.00632  -0.0479   0.5118   1.0000
   4.500   0.7214   0.01494   0.00654  -0.0469   0.4881   1.0000
   4.750   0.7440   0.01525   0.00681  -0.0460   0.4634   1.0000
   5.000   0.7664   0.01560   0.00710  -0.0450   0.4387   1.0000
   5.250   0.7884   0.01599   0.00743  -0.0439   0.4138   1.0000
   5.500   0.8103   0.01639   0.00778  -0.0429   0.3879   1.0000
   5.750   0.8318   0.01682   0.00816  -0.0419   0.3617   1.0000
   6.000   0.8531   0.01729   0.00858  -0.0408   0.3363   1.0000
   6.250   0.8738   0.01781   0.00902  -0.0397   0.3114   1.0000
   6.500   0.8947   0.01833   0.00955  -0.0386   0.2866   1.0000
   6.750   0.9150   0.01890   0.01008  -0.0375   0.2627   1.0000
   7.000   0.9346   0.01953   0.01066  -0.0363   0.2399   1.0000
   7.250   0.9543   0.02017   0.01129  -0.0352   0.2168   1.0000
   7.500   0.9727   0.02090   0.01196  -0.0339   0.1947   1.0000
   7.750   0.9910   0.02165   0.01271  -0.0327   0.1732   1.0000
   8.000   1.0081   0.02248   0.01348  -0.0313   0.1539   1.0000
   8.250   1.0255   0.02331   0.01432  -0.0300   0.1366   1.0000
   8.500   1.0420   0.02420   0.01522  -0.0285   0.1218   1.0000
   8.750   1.0575   0.02515   0.01618  -0.0270   0.1088   1.0000
   9.000   1.0717   0.02617   0.01723  -0.0253   0.0978   1.0000
   9.250   1.0848   0.02723   0.01834  -0.0235   0.0887   1.0000
   9.500   1.0977   0.02831   0.01952  -0.0217   0.0803   1.0000
   9.750   1.1062   0.02953   0.02073  -0.0194   0.0738   1.0000
  10.000   1.1171   0.03070   0.02205  -0.0173   0.0677   1.0000
  10.250   1.1238   0.03209   0.02345  -0.0151   0.0632   1.0000
  10.500   1.1333   0.03348   0.02499  -0.0131   0.0587   1.0000
  10.750   1.1411   0.03488   0.02651  -0.0112   0.0544   1.0000
  11.000   1.1457   0.03659   0.02827  -0.0093   0.0516   1.0000
  11.250   1.1534   0.03831   0.03019  -0.0077   0.0486   1.0000
  11.500   1.1594   0.04006   0.03211  -0.0062   0.0454   1.0000
  11.750   1.1626   0.04190   0.03405  -0.0048   0.0427   1.0000
  12.000   1.1641   0.04418   0.03634  -0.0036   0.0406   1.0000
  12.250   1.1673   0.04645   0.03892  -0.0025   0.0382   1.0000
  12.500   1.1679   0.04890   0.04157  -0.0018   0.0360   1.0000
  12.750   1.1665   0.05147   0.04427  -0.0014   0.0340   1.0000
  13.000   1.1635   0.05438   0.04724  -0.0013   0.0325   1.0000
  13.250   1.1596   0.05780   0.05082  -0.0014   0.0311   1.0000
  13.500   1.1536   0.06161   0.05493  -0.0020   0.0297   1.0000
  13.750   1.1463   0.06575   0.05931  -0.0030   0.0285   1.0000
  14.000   1.1372   0.07028   0.06404  -0.0046   0.0274   1.0000
  14.250   1.1275   0.07516   0.06915  -0.0065   0.0268   1.0000
  14.500   1.1165   0.08042   0.07457  -0.0089   0.0261   1.0000
  14.750   1.1050   0.08603   0.08032  -0.0117   0.0255   1.0000
  15.000   1.0927   0.09208   0.08652  -0.0149   0.0251   1.0000
  15.250   1.0788   0.09873   0.09332  -0.0186   0.0248   1.0000
  15.500   1.0630   0.10616   0.10091  -0.0230   0.0246   1.0000
  15.750   1.0345   0.11719   0.11219  -0.0298   0.0250   1.0000
  16.000   0.9259   0.15313   0.14848  -0.0511   0.0297   1.0000
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