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RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
Reynolds number: 200,000
Max Cl/Cd: 66.79 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15a111-il-200000.txt
Download as CSV file: xf-rg15a111-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4716   0.09561   0.09198  -0.0322   1.0000   0.0614
  -9.750  -0.4743   0.09151   0.08793  -0.0338   1.0000   0.0627
  -9.500  -0.4817   0.08673   0.08320  -0.0364   1.0000   0.0648
  -9.250  -0.4092   0.07261   0.06935  -0.0402   1.0000   0.0722
  -9.000  -0.4160   0.06818   0.06496  -0.0410   1.0000   0.0734
  -8.750  -0.5701   0.04635   0.04269  -0.0516   1.0000   0.0445
  -8.500  -0.6568   0.04741   0.04297  -0.0477   1.0000   0.0348
  -8.250  -0.6628   0.04293   0.03832  -0.0455   1.0000   0.0338
  -8.000  -0.6659   0.03891   0.03399  -0.0429   1.0000   0.0331
  -7.750  -0.6649   0.03508   0.02976  -0.0403   1.0000   0.0324
  -7.500  -0.6582   0.03201   0.02628  -0.0379   1.0000   0.0326
  -7.250  -0.6467   0.02985   0.02373  -0.0358   1.0000   0.0338
  -7.000  -0.6328   0.02790   0.02139  -0.0338   1.0000   0.0346
  -6.750  -0.6169   0.02607   0.01920  -0.0320   1.0000   0.0351
  -6.500  -0.6001   0.02346   0.01628  -0.0305   1.0000   0.0358
  -6.250  -0.5818   0.02166   0.01438  -0.0293   1.0000   0.0374
  -6.000  -0.5627   0.02092   0.01360  -0.0281   1.0000   0.0401
  -5.750  -0.5426   0.02008   0.01264  -0.0269   1.0000   0.0426
  -5.500  -0.5220   0.01927   0.01167  -0.0256   1.0000   0.0445
  -5.250  -0.5025   0.01788   0.01028  -0.0244   1.0000   0.0475
  -5.000  -0.4718   0.01729   0.00967  -0.0254   0.9976   0.0535
  -4.750  -0.4338   0.01631   0.00870  -0.0278   0.9935   0.0623
  -4.500  -0.3969   0.01538   0.00786  -0.0300   0.9882   0.0850
  -4.250  -0.3572   0.01470   0.00736  -0.0329   0.9838   0.1261
  -4.000  -0.3218   0.01413   0.00696  -0.0350   0.9774   0.1685
  -3.750  -0.2828   0.01352   0.00668  -0.0379   0.9723   0.2370
  -3.500  -0.2485   0.01282   0.00642  -0.0398   0.9658   0.3331
  -3.250  -0.2128   0.01209   0.00622  -0.0418   0.9598   0.4558
  -3.000  -0.1788   0.01162   0.00622  -0.0430   0.9536   0.5725
  -2.750  -0.1439   0.01146   0.00623  -0.0440   0.9465   0.6493
  -2.500  -0.1022   0.01138   0.00619  -0.0463   0.9427   0.6989
  -2.250  -0.0723   0.01132   0.00614  -0.0463   0.9332   0.7321
  -2.000  -0.0308   0.01122   0.00605  -0.0483   0.9293   0.7612
  -1.750   0.0006   0.01114   0.00597  -0.0484   0.9207   0.7832
  -1.500   0.0397   0.01099   0.00582  -0.0500   0.9158   0.8035
  -1.250   0.0708   0.01089   0.00569  -0.0500   0.9070   0.8216
  -1.000   0.1069   0.01072   0.00551  -0.0509   0.9005   0.8383
  -0.750   0.1351   0.01061   0.00539  -0.0503   0.8900   0.8534
  -0.500   0.1661   0.01046   0.00523  -0.0501   0.8809   0.8673
  -0.250   0.1957   0.01033   0.00507  -0.0497   0.8705   0.8806
   0.000   0.2216   0.01023   0.00496  -0.0485   0.8577   0.8937
   0.250   0.2483   0.01013   0.00484  -0.0476   0.8447   0.9067
   0.500   0.2763   0.01006   0.00473  -0.0470   0.8313   0.9196
   0.750   0.3064   0.01000   0.00463  -0.0468   0.8173   0.9320
   1.000   0.3390   0.00995   0.00454  -0.0473   0.8024   0.9438
   1.250   0.3763   0.00994   0.00447  -0.0489   0.7867   0.9535
   1.500   0.4164   0.00993   0.00440  -0.0511   0.7698   0.9614
   1.750   0.4549   0.00994   0.00434  -0.0531   0.7522   0.9704
   2.000   0.4991   0.00995   0.00429  -0.0564   0.7322   0.9761
   2.250   0.5388   0.00997   0.00425  -0.0589   0.7107   0.9840
   2.500   0.5801   0.00999   0.00421  -0.0617   0.6887   0.9910
   2.750   0.6202   0.01003   0.00418  -0.0644   0.6645   0.9990
   3.000   0.6377   0.01010   0.00418  -0.0627   0.6431   1.0000
   3.250   0.6510   0.01020   0.00422  -0.0602   0.6219   1.0000
   3.500   0.6657   0.01035   0.00427  -0.0578   0.6010   1.0000
   3.750   0.6828   0.01051   0.00437  -0.0558   0.5780   1.0000
   4.000   0.7029   0.01073   0.00448  -0.0544   0.5548   1.0000
   4.250   0.7243   0.01097   0.00464  -0.0531   0.5302   1.0000
   4.500   0.7463   0.01122   0.00481  -0.0520   0.5047   1.0000
   4.750   0.7685   0.01151   0.00501  -0.0509   0.4787   1.0000
   5.000   0.7906   0.01184   0.00523  -0.0499   0.4525   1.0000
   5.250   0.8128   0.01217   0.00549  -0.0489   0.4262   1.0000
   5.500   0.8351   0.01251   0.00578  -0.0479   0.4000   1.0000
   5.750   0.8570   0.01289   0.00608  -0.0468   0.3735   1.0000
   6.000   0.8786   0.01331   0.00642  -0.0458   0.3470   1.0000
   6.250   0.8998   0.01377   0.00680  -0.0447   0.3206   1.0000
   6.500   0.9207   0.01425   0.00719  -0.0436   0.2925   1.0000
   6.750   0.9411   0.01477   0.00762  -0.0424   0.2639   1.0000
   7.000   0.9612   0.01533   0.00808  -0.0413   0.2359   1.0000
   7.250   0.9811   0.01593   0.00862  -0.0401   0.2096   1.0000
   7.500   1.0003   0.01659   0.00920  -0.0389   0.1855   1.0000
   7.750   1.0185   0.01733   0.00983  -0.0375   0.1633   1.0000
   8.000   1.0371   0.01807   0.01053  -0.0362   0.1433   1.0000
   8.250   1.0547   0.01887   0.01128  -0.0347   0.1258   1.0000
   8.500   1.0712   0.01974   0.01211  -0.0332   0.1104   1.0000
   8.750   1.0869   0.02067   0.01302  -0.0315   0.0971   1.0000
   9.000   1.1021   0.02166   0.01401  -0.0297   0.0860   1.0000
   9.250   1.1157   0.02277   0.01513  -0.0277   0.0769   1.0000
   9.500   1.1274   0.02396   0.01626  -0.0256   0.0697   1.0000
   9.750   1.1412   0.02497   0.01740  -0.0236   0.0639   1.0000
  10.000   1.1522   0.02607   0.01851  -0.0214   0.0588   1.0000
  10.250   1.1642   0.02737   0.01992  -0.0194   0.0543   1.0000
  10.500   1.1755   0.02832   0.02095  -0.0174   0.0500   1.0000
  10.750   1.1849   0.03021   0.02279  -0.0156   0.0460   1.0000
  11.000   1.1947   0.03114   0.02394  -0.0134   0.0427   1.0000
  11.250   1.2029   0.03234   0.02521  -0.0115   0.0395   1.0000
  11.500   1.2109   0.03473   0.02760  -0.0099   0.0364   1.0000
  11.750   1.2165   0.03601   0.02911  -0.0079   0.0342   1.0000
  12.000   1.2211   0.03752   0.03078  -0.0062   0.0317   1.0000
  12.250   1.2260   0.03938   0.03268  -0.0047   0.0300   1.0000
  12.500   1.2293   0.04268   0.03611  -0.0033   0.0281   1.0000
  12.750   1.2291   0.04500   0.03871  -0.0019   0.0271   1.0000
  13.000   1.2279   0.04771   0.04165  -0.0007   0.0260   1.0000
  13.250   1.2257   0.05048   0.04461   0.0001   0.0250   1.0000
  13.500   1.2222   0.05345   0.04775   0.0005   0.0242   1.0000
  13.750   1.2196   0.05629   0.05069   0.0005   0.0234   1.0000
  14.000   1.2168   0.05953   0.05400   0.0003   0.0226   1.0000
  14.250   1.2077   0.06406   0.05868  -0.0002   0.0220   1.0000
  14.750   1.1740   0.07517   0.07027  -0.0037   0.0216   1.0000
  15.000   1.1562   0.08114   0.07648  -0.0066   0.0215   1.0000
  15.250   1.1386   0.08758   0.08314  -0.0102   0.0214   1.0000
  15.500   1.1191   0.09489   0.09066  -0.0144   0.0214   1.0000
  15.750   1.0984   0.10296   0.09892  -0.0192   0.0215   1.0000
  16.000   1.0760   0.11189   0.10802  -0.0246   0.0217   1.0000
  16.250   0.8776   0.18058   0.17714  -0.0649   0.0346   1.0000
  16.500   0.8813   0.18548   0.18204  -0.0668   0.0357   1.0000
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