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RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAF 19 AIRFOIL (raf19-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.78 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf19-il-1000000.txt
Download as CSV file: xf-raf19-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0438   0.10265   0.10106  -0.0805   0.9625   0.0142
  -9.750   0.0597   0.09900   0.09741  -0.0839   0.9560   0.0143
  -9.500   0.0738   0.09512   0.09352  -0.0869   0.9455   0.0146
  -9.250   0.1138   0.09122   0.08955  -0.0953   0.9291   0.0149
  -9.000   0.1854   0.08520   0.08329  -0.1130   0.8858   0.0158
  -8.250   0.2262   0.07293   0.07030  -0.1253   0.7587   0.0148
  -8.000   0.2360   0.07170   0.06900  -0.1252   0.7411   0.0151
  -7.750   0.1462   0.05279   0.05002  -0.1355   0.7368   0.0142
  -7.500   0.1561   0.04932   0.04645  -0.1390   0.7249   0.0147
  -7.250   0.1737   0.04770   0.04478  -0.1404   0.7142   0.0152
  -7.000   0.1921   0.04626   0.04327  -0.1416   0.7031   0.0156
  -6.750   0.2112   0.04430   0.04127  -0.1436   0.6921   0.0163
  -6.500   0.2312   0.04197   0.03885  -0.1461   0.6810   0.0172
  -6.250   0.2522   0.03995   0.03674  -0.1481   0.6685   0.0180
  -6.000   0.2744   0.03898   0.03576  -0.1488   0.6547   0.0200
  -5.750   0.2912   0.02206   0.01830  -0.1665   0.6482   0.0354
  -5.500   0.3189   0.03585   0.03257  -0.1513   0.6209   0.0318
  -5.250   0.3398   0.03723   0.03389  -0.1486   0.5980   0.0325
  -5.000   0.3606   0.03803   0.03459  -0.1467   0.5783   0.0333
  -4.750   0.3858   0.03478   0.03118  -0.1504   0.5649   0.0381
  -4.500   0.4079   0.03547   0.03180  -0.1490   0.5514   0.0386
  -4.250   0.4296   0.03612   0.03239  -0.1476   0.5402   0.0393
  -4.000   0.4519   0.03627   0.03250  -0.1469   0.5303   0.0404
  -3.750   0.4815   0.03359   0.02968  -0.1502   0.5230   0.0443
  -2.750   0.5668   0.01293   0.00755  -0.1586   0.5018   0.0526
  -2.500   0.5902   0.01244   0.00688  -0.1577   0.4945   0.0532
  -2.250   0.6114   0.01120   0.00533  -0.1565   0.4885   0.0547
  -2.000   0.6357   0.01089   0.00490  -0.1556   0.4815   0.0554
  -1.750   0.6603   0.01067   0.00458  -0.1547   0.4748   0.0561
  -1.500   0.6855   0.01047   0.00429  -0.1539   0.4674   0.0566
  -1.250   0.7100   0.01034   0.00406  -0.1529   0.4595   0.0572
  -1.000   0.7352   0.01021   0.00386  -0.1521   0.4505   0.0579
  -0.750   0.7598   0.01014   0.00370  -0.1512   0.4410   0.0587
  -0.500   0.7840   0.01011   0.00356  -0.1503   0.4288   0.0597
  -0.250   0.8086   0.01008   0.00344  -0.1494   0.4162   0.0605
   0.000   0.8326   0.01011   0.00337  -0.1484   0.4028   0.0616
   0.250   0.8562   0.01018   0.00334  -0.1473   0.3890   0.0625
   0.500   0.8795   0.01022   0.00328  -0.1462   0.3758   0.0633
   0.750   0.9024   0.01025   0.00323  -0.1450   0.3639   0.0659
   1.000   0.9258   0.01032   0.00324  -0.1439   0.3539   0.0685
   1.250   0.9491   0.01041   0.00329  -0.1428   0.3456   0.0711
   1.500   0.9721   0.01051   0.00333  -0.1416   0.3376   0.0748
   1.750   0.9950   0.01061   0.00344  -0.1405   0.3310   0.0821
   2.000   1.0178   0.01073   0.00355  -0.1393   0.3252   0.0894
   2.250   1.0391   0.01092   0.00371  -0.1378   0.3189   0.0949
   2.500   1.0617   0.01107   0.00384  -0.1366   0.3149   0.0976
   2.750   1.0838   0.01114   0.00391  -0.1353   0.3109   0.1024
   3.000   1.1052   0.01131   0.00408  -0.1339   0.3065   0.1057
   3.250   1.1259   0.01150   0.00424  -0.1324   0.3018   0.1084
   3.500   1.1489   0.01160   0.00435  -0.1313   0.2993   0.1104
   3.750   1.1711   0.01174   0.00448  -0.1301   0.2962   0.1115
   4.000   1.1924   0.01181   0.00453  -0.1287   0.2929   0.1144
   4.250   1.2130   0.01197   0.00469  -0.1272   0.2892   0.1174
   4.500   1.2334   0.01216   0.00488  -0.1257   0.2857   0.1195
   4.750   1.2561   0.01227   0.00501  -0.1246   0.2836   0.1222
   5.000   1.2780   0.01241   0.00516  -0.1234   0.2809   0.1245
   5.250   1.2989   0.01259   0.00534  -0.1221   0.2776   0.1263
   5.500   1.3190   0.01275   0.00549  -0.1206   0.2747   0.1290
   5.750   1.3375   0.01298   0.00570  -0.1189   0.2708   0.1313
   6.000   1.3600   0.01306   0.00583  -0.1178   0.2682   0.1335
   6.250   1.3817   0.01319   0.00597  -0.1167   0.2648   0.1356
   6.500   1.4019   0.01338   0.00616  -0.1153   0.2613   0.1380
   6.750   1.4198   0.01367   0.00642  -0.1136   0.2563   0.1404
   7.000   1.4406   0.01383   0.00661  -0.1123   0.2537   0.1423
   7.250   1.4617   0.01397   0.00678  -0.1112   0.2506   0.1477
   7.500   1.4808   0.01422   0.00702  -0.1098   0.2449   0.1523
   7.750   1.4986   0.01452   0.00731  -0.1081   0.2394   0.1564
   8.000   1.5188   0.01471   0.00753  -0.1069   0.2346   0.1630
   8.250   1.5353   0.01508   0.00786  -0.1051   0.2272   0.1695
   8.500   1.5529   0.01541   0.00818  -0.1035   0.2179   0.1760
   8.750   1.5652   0.01597   0.00865  -0.1012   0.2027   0.1825
   9.000   1.5676   0.01705   0.00949  -0.0974   0.1730   0.1868
   9.250   1.5576   0.01878   0.01094  -0.0920   0.1329   0.1899
   9.500   1.5306   0.02159   0.01342  -0.0848   0.0806   0.1908
   9.750   1.5028   0.02482   0.01643  -0.0785   0.0216   0.1913
  10.000   1.5099   0.02601   0.01768  -0.0764   0.0157   0.1963
  10.250   1.5193   0.02709   0.01882  -0.0748   0.0140   0.2011
  10.500   1.5295   0.02819   0.02000  -0.0734   0.0137   0.2075
  10.750   1.5383   0.02942   0.02130  -0.0719   0.0129   0.2130
  11.000   1.5454   0.03086   0.02283  -0.0705   0.0123   0.2193
  11.250   1.5521   0.03240   0.02445  -0.0693   0.0119   0.2256
  11.500   1.5537   0.03445   0.02661  -0.0678   0.0113   0.2313
  11.750   1.5564   0.03652   0.02878  -0.0666   0.0108   0.2387
  12.000   1.5607   0.03851   0.03087  -0.0657   0.0106   0.2509
  12.250   1.5663   0.04052   0.03300  -0.0652   0.0100   0.2984
  12.500   1.6766   0.04788   0.04151  -0.0931   0.0084   1.0000
  12.750   1.6698   0.05142   0.04516  -0.0923   0.0083   1.0000
  13.000   1.6660   0.05470   0.04852  -0.0917   0.0082   1.0000
  13.250   1.6623   0.05808   0.05199  -0.0912   0.0080   1.0000
  13.500   1.6531   0.06230   0.05632  -0.0910   0.0079   1.0000
  13.750   1.6458   0.06634   0.06046  -0.0909   0.0077   1.0000
  14.000   1.6350   0.07095   0.06518  -0.0910   0.0076   1.0000
  14.250   1.6190   0.07642   0.07078  -0.0913   0.0076   1.0000
  14.500   1.6048   0.08169   0.07616  -0.0917   0.0075   1.0000
  14.750   1.5889   0.08728   0.08187  -0.0922   0.0074   1.0000
  15.000   1.5735   0.09292   0.08762  -0.0929   0.0073   1.0000
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