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RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAF 19 AIRFOIL (raf19-il)
Reynolds number: 50,000
Max Cl/Cd: 32.18 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf19-il-50000-n5.txt
Download as CSV file: xf-raf19-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 19 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.0043   0.11391   0.10840  -0.0556   0.9238   0.0691
  -7.500   0.0097   0.11117   0.10565  -0.0580   0.9125   0.0708
  -7.250   0.0273   0.10828   0.10277  -0.0616   0.9035   0.0731
  -7.000   0.0370   0.10636   0.10087  -0.0637   0.8906   0.0745
  -6.750   0.0442   0.10508   0.09960  -0.0661   0.8767   0.0755
  -6.500   0.0569   0.10347   0.09800  -0.0700   0.8633   0.0760
  -6.250   0.0818   0.09743   0.09195  -0.0713   0.8586   0.0780
  -6.000   0.0955   0.09452   0.08905  -0.0721   0.8466   0.0815
  -5.750   0.1120   0.09204   0.08653  -0.0748   0.8353   0.0842
  -5.500   0.1384   0.08993   0.08436  -0.0816   0.8258   0.0870
  -5.250   0.1613   0.08831   0.08268  -0.0875   0.8135   0.0877
  -5.000   0.1726   0.08351   0.07790  -0.0855   0.8034   0.0898
  -4.750   0.2017   0.07996   0.07426  -0.0890   0.7957   0.0974
  -4.500   0.2316   0.07907   0.07323  -0.0966   0.7816   0.1008
  -4.250   0.2533   0.07580   0.06990  -0.0996   0.7694   0.1020
  -4.000   0.2725   0.07120   0.06523  -0.0982   0.7612   0.1103
  -3.750   0.3162   0.06994   0.06373  -0.1084   0.7477   0.1170
  -3.500   0.3189   0.06614   0.05996  -0.1036   0.7358   0.1235
  -3.250   0.3557   0.06382   0.05742  -0.1097   0.7247   0.1335
  -3.000   0.3801   0.06102   0.05447  -0.1108   0.7142   0.1417
  -2.750   0.4119   0.05948   0.05273  -0.1153   0.7014   0.1485
  -2.500   0.4316   0.05696   0.05010  -0.1152   0.6909   0.1530
  -2.250   0.4690   0.05530   0.04817  -0.1194   0.6804   0.1599
  -2.000   0.5024   0.05442   0.04705  -0.1232   0.6676   0.1628
  -1.750   0.5153   0.05196   0.04456  -0.1213   0.6570   0.1668
  -1.500   0.5542   0.05072   0.04303  -0.1251   0.6469   0.1754
  -1.000   0.6044   0.04827   0.04027  -0.1270   0.6233   0.1782
  -0.750   0.6326   0.04643   0.03824  -0.1280   0.6138   0.1803
  -0.500   0.6553   0.04534   0.03702  -0.1280   0.6020   0.1821
  -0.250   0.6820   0.04432   0.03582  -0.1288   0.5909   0.1827
   0.250   0.7524   0.04167   0.03249  -0.1328   0.5701   0.1429
   0.500   0.7799   0.04059   0.03118  -0.1334   0.5594   0.1367
   0.750   0.8207   0.03944   0.02952  -0.1358   0.5502   0.1307
   1.000   0.8414   0.03887   0.02881  -0.1349   0.5389   0.1301
   1.250   0.8694   0.03814   0.02782  -0.1352   0.5292   0.1301
   1.500   0.8949   0.03761   0.02713  -0.1350   0.5194   0.1344
   1.750   0.9160   0.03745   0.02686  -0.1341   0.5091   0.1394
   2.000   0.9489   0.03687   0.02591  -0.1349   0.5006   0.1430
   2.250   0.9679   0.03682   0.02571  -0.1336   0.4903   0.1444
   2.500   0.9982   0.03638   0.02489  -0.1338   0.4823   0.1472
   2.750   1.0166   0.03647   0.02495  -0.1326   0.4727   0.1503
   3.000   1.0453   0.03651   0.02468  -0.1327   0.4649   0.1616
   3.250   1.0654   0.03675   0.02491  -0.1319   0.4562   0.1693
   3.500   1.0983   0.03673   0.02449  -0.1327   0.4492   0.1761
   3.750   1.1170   0.03719   0.02495  -0.1317   0.4409   0.1852
   4.000   1.1506   0.03717   0.02461  -0.1327   0.4348   0.1963
   4.250   1.1670   0.03788   0.02527  -0.1314   0.4268   0.2004
   4.500   1.1960   0.03808   0.02526  -0.1317   0.4208   0.2098
   4.750   1.2173   0.03871   0.02579  -0.1311   0.4146   0.2175
   5.000   1.2390   0.03932   0.02634  -0.1305   0.4085   0.2210
   5.250   1.2704   0.03948   0.02632  -0.1312   0.4037   0.2256
   5.500   1.2834   0.04049   0.02737  -0.1295   0.3978   0.2298
   5.750   1.3022   0.04121   0.02811  -0.1286   0.3924   0.2377
   6.000   1.3311   0.04147   0.02823  -0.1288   0.3882   0.2466
   6.250   1.3410   0.04263   0.02949  -0.1267   0.3831   0.2503
   6.500   1.3511   0.04378   0.03074  -0.1247   0.3783   0.2544
   6.750   1.3726   0.04447   0.03142  -0.1241   0.3745   0.2605
   7.000   1.4048   0.04471   0.03160  -0.1249   0.3714   0.2697
   7.250   1.3929   0.04703   0.03415  -0.1203   0.3668   0.2738
   7.500   1.3935   0.04883   0.03610  -0.1175   0.3624   0.2811
   7.750   1.4111   0.04970   0.03704  -0.1166   0.3588   0.2945
   8.000   1.4434   0.04979   0.03712  -0.1171   0.3558   0.3118
   8.250   1.4102   0.05386   0.04148  -0.1116   0.3513   0.3101
   8.500   1.3753   0.05879   0.04665  -0.1074   0.3465   0.3085
   8.750   1.3757   0.06131   0.04929  -0.1059   0.3432   0.3174
   9.000   1.4009   0.06171   0.04981  -0.1056   0.3409   0.3453
   9.500   1.2308   0.08839   0.07685  -0.1036   0.3241   0.2959
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