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RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAF 19 AIRFOIL (raf19-il)
Reynolds number: 500,000
Max Cl/Cd: 82.22 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf19-il-500000.txt
Download as CSV file: xf-raf19-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0441   0.10121   0.09912  -0.0745   0.9628   0.0223
  -9.000   0.0660   0.09811   0.09602  -0.0781   0.9582   0.0229
  -8.750   0.0785   0.09557   0.09348  -0.0793   0.9467   0.0238
  -8.500   0.0948   0.09242   0.09033  -0.0822   0.9346   0.0253
  -8.250   0.1153   0.08832   0.08620  -0.0912   0.9194   0.0263
  -8.000   0.1560   0.08297   0.08078  -0.0979   0.9043   0.0269
  -7.750   0.2147   0.07829   0.07596  -0.1104   0.8837   0.0281
  -7.500   0.2567   0.07400   0.07140  -0.1231   0.8391   0.0314
  -7.250   0.2636   0.07188   0.06906  -0.1251   0.8015   0.0315
  -7.000   0.2701   0.06988   0.06693  -0.1255   0.7773   0.0315
  -6.750   0.2774   0.06748   0.06443  -0.1259   0.7593   0.0315
  -6.500   0.2807   0.06332   0.06019  -0.1247   0.7455   0.0259
  -6.250   0.2903   0.06157   0.05837  -0.1248   0.7306   0.0254
  -6.000   0.2986   0.05887   0.05560  -0.1261   0.7178   0.0252
  -5.750   0.3083   0.05580   0.05247  -0.1281   0.7056   0.0251
  -5.500   0.3189   0.05074   0.04736  -0.1327   0.6946   0.0268
  -5.250   0.3382   0.05113   0.04769  -0.1315   0.6806   0.0279
  -5.000   0.3565   0.04471   0.04115  -0.1388   0.6702   0.0319
  -4.750   0.3760   0.04488   0.04126  -0.1377   0.6545   0.0327
  -4.500   0.3967   0.04393   0.04022  -0.1382   0.6384   0.0358
  -4.250   0.4247   0.04172   0.03787  -0.1423   0.6225   0.0453
  -4.000   0.4391   0.04250   0.03860  -0.1390   0.6060   0.0464
  -3.500   0.5050   0.04121   0.03696  -0.1458   0.5769   0.0627
  -3.250   0.5176   0.03823   0.03391  -0.1451   0.5664   0.0638
  -3.000   0.5330   0.03744   0.03306  -0.1433   0.5557   0.0648
  -2.750   0.5524   0.03671   0.03225  -0.1426   0.5456   0.0667
  -2.500   0.5998   0.03592   0.03122  -0.1486   0.5366   0.0732
  -2.250   0.6270   0.03444   0.02958  -0.1498   0.5281   0.0734
  -2.000   0.6439   0.03143   0.02651  -0.1498   0.5209   0.0745
  -1.750   0.6642   0.03038   0.02539  -0.1491   0.5126   0.0749
  -1.500   0.6854   0.02946   0.02442  -0.1485   0.5046   0.0756
  -1.250   0.7077   0.02859   0.02346  -0.1480   0.4962   0.0764
  -1.000   0.7313   0.02770   0.02251  -0.1478   0.4885   0.0776
  -0.750   0.7553   0.02687   0.02158  -0.1476   0.4800   0.0797
  -0.500   0.7940   0.02613   0.02058  -0.1495   0.4716   0.0848
  -0.250   0.8044   0.01360   0.00671  -0.1486   0.4700   0.0714
   0.000   0.8271   0.01323   0.00611  -0.1474   0.4607   0.0728
   0.250   0.8510   0.01272   0.00541  -0.1465   0.4503   0.0744
   0.500   0.8740   0.01256   0.00515  -0.1453   0.4389   0.0761
   0.750   0.8964   0.01261   0.00512  -0.1440   0.4264   0.0780
   1.000   0.9187   0.01266   0.00508  -0.1427   0.4134   0.0803
   1.250   0.9414   0.01268   0.00500  -0.1415   0.4007   0.0830
   1.500   0.9636   0.01269   0.00490  -0.1402   0.3887   0.0863
   1.750   0.9847   0.01289   0.00505  -0.1387   0.3780   0.0900
   2.000   1.0056   0.01309   0.00519  -0.1372   0.3685   0.0948
   2.250   1.0266   0.01322   0.00526  -0.1357   0.3606   0.1003
   2.500   1.0463   0.01350   0.00554  -0.1339   0.3531   0.1049
   2.750   1.0666   0.01374   0.00572  -0.1323   0.3467   0.1101
   3.000   1.0878   0.01383   0.00577  -0.1309   0.3406   0.1147
   3.250   1.1067   0.01411   0.00602  -0.1291   0.3347   0.1181
   3.500   1.1280   0.01429   0.00620  -0.1277   0.3301   0.1219
   3.750   1.1490   0.01447   0.00635  -0.1263   0.3257   0.1252
   4.000   1.1692   0.01464   0.00645  -0.1248   0.3213   0.1283
   4.250   1.1885   0.01491   0.00672  -0.1232   0.3172   0.1321
   4.500   1.2104   0.01505   0.00691  -0.1220   0.3139   0.1350
   4.750   1.2312   0.01525   0.00710  -0.1206   0.3103   0.1386
   5.000   1.2506   0.01554   0.00735  -0.1190   0.3068   0.1419
   5.250   1.2700   0.01573   0.00749  -0.1175   0.3030   0.1443
   5.500   1.2908   0.01591   0.00772  -0.1162   0.3003   0.1470
   5.750   1.3120   0.01607   0.00792  -0.1150   0.2975   0.1496
   6.000   1.3323   0.01625   0.00812  -0.1137   0.2943   0.1520
   6.250   1.3517   0.01648   0.00834  -0.1122   0.2913   0.1542
   6.500   1.3701   0.01679   0.00862  -0.1106   0.2883   0.1564
   6.750   1.3892   0.01705   0.00889  -0.1092   0.2849   0.1590
   7.000   1.4093   0.01714   0.00907  -0.1079   0.2806   0.1625
   7.250   1.4281   0.01738   0.00934  -0.1064   0.2772   0.1659
   7.500   1.4446   0.01773   0.00966  -0.1046   0.2731   0.1700
   7.750   1.4624   0.01803   0.00999  -0.1031   0.2690   0.1745
   8.000   1.4818   0.01823   0.01027  -0.1018   0.2653   0.1806
   8.250   1.4992   0.01854   0.01059  -0.1002   0.2611   0.1870
   8.500   1.5136   0.01899   0.01103  -0.0983   0.2560   0.1931
   8.750   1.5329   0.01920   0.01131  -0.0971   0.2502   0.2009
   9.000   1.5489   0.01958   0.01171  -0.0955   0.2437   0.2095
   9.250   1.5645   0.02002   0.01217  -0.0939   0.2377   0.2176
   9.500   1.5798   0.02049   0.01265  -0.0924   0.2289   0.2270
   9.750   1.5924   0.02114   0.01326  -0.0906   0.2150   0.2363
  10.000   1.5985   0.02220   0.01418  -0.0880   0.1947   0.2449
  10.250   1.6005   0.02359   0.01543  -0.0852   0.1708   0.2545
  10.500   1.5878   0.02602   0.01761  -0.0811   0.1340   0.2611
  10.750   1.5606   0.02976   0.02110  -0.0763   0.0931   0.2623
  11.000   1.5303   0.03425   0.02543  -0.0724   0.0515   0.2630
  11.250   1.5156   0.03783   0.02900  -0.0702   0.0227   0.2695
  11.500   1.5167   0.04021   0.03150  -0.0693   0.0190   0.3028
  11.750   1.6298   0.04519   0.03755  -0.0938   0.0150   1.0000
  12.000   1.6270   0.04814   0.04062  -0.0927   0.0146   1.0000
  12.250   1.6193   0.05177   0.04442  -0.0919   0.0141   1.0000
  12.500   1.6144   0.05518   0.04795  -0.0912   0.0139   1.0000
  12.750   1.6088   0.05881   0.05170  -0.0908   0.0139   1.0000
  13.000   1.6022   0.06270   0.05572  -0.0905   0.0136   1.0000
  13.250   1.5935   0.06695   0.06009  -0.0904   0.0133   1.0000
  13.500   1.5824   0.07165   0.06492  -0.0905   0.0131   1.0000
  13.750   1.5697   0.07669   0.07009  -0.0908   0.0128   1.0000
  14.000   1.5564   0.08187   0.07540  -0.0912   0.0127   1.0000
  14.250   1.5411   0.08745   0.08112  -0.0918   0.0127   1.0000
  14.500   1.5246   0.09336   0.08716  -0.0926   0.0125   1.0000
  14.750   1.5072   0.09948   0.09342  -0.0936   0.0124   1.0000
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