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RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RAF 19 AIRFOIL (raf19-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.98 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf19-il-1000000-n5.txt
Download as CSV file: xf-raf19-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.1673   0.09316   0.09024  -0.1203   0.7383   0.0054
 -10.250   0.1743   0.09046   0.08748  -0.1212   0.7259   0.0055
 -10.000   0.1495   0.08145   0.07847  -0.1235   0.7189   0.0056
  -9.750   0.1782   0.08339   0.08035  -0.1231   0.7050   0.0058
  -9.500   0.1408   0.07329   0.07025  -0.1263   0.7031   0.0063
  -9.250   0.1462   0.07122   0.06815  -0.1267   0.6936   0.0065
  -9.000   0.1425   0.06825   0.06514  -0.1270   0.6831   0.0065
  -8.750   0.1394   0.06601   0.06286  -0.1265   0.6724   0.0067
  -8.500   0.1404   0.06370   0.06050  -0.1269   0.6597   0.0071
  -8.250   0.1472   0.06160   0.05834  -0.1278   0.6453   0.0071
  -8.000   0.1554   0.05955   0.05621  -0.1288   0.6263   0.0072
  -7.750   0.1646   0.05756   0.05410  -0.1299   0.6020   0.0075
  -7.500   0.1764   0.05567   0.05212  -0.1311   0.5833   0.0076
  -7.250   0.1895   0.05388   0.05022  -0.1324   0.5622   0.0078
  -7.000   0.2055   0.05204   0.04832  -0.1340   0.5528   0.0079
  -6.750   0.2232   0.05067   0.04689  -0.1351   0.5392   0.0083
  -6.500   0.2418   0.04902   0.04521  -0.1367   0.5312   0.0087
  -6.250   0.2616   0.04721   0.04336  -0.1386   0.5241   0.0092
  -6.000   0.2818   0.04519   0.04127  -0.1409   0.5170   0.0100
  -5.750   0.3041   0.04364   0.03968  -0.1425   0.5109   0.0102
  -5.500   0.3268   0.04166   0.03763  -0.1448   0.5044   0.0108
  -5.250   0.3504   0.04015   0.03606  -0.1465   0.4977   0.0116
  -5.000   0.3758   0.03772   0.03358  -0.1495   0.4925   0.0127
  -4.750   0.4025   0.03454   0.03028  -0.1533   0.4866   0.0140
  -4.500   0.4313   0.02272   0.01784  -0.1650   0.4841   0.0158
  -4.250   0.4434   0.01560   0.01004  -0.1665   0.4810   0.0192
  -4.000   0.4567   0.01191   0.00595  -0.1653   0.4764   0.0345
  -3.750   0.4806   0.01133   0.00529  -0.1646   0.4692   0.0379
  -3.500   0.5061   0.01119   0.00510  -0.1639   0.4625   0.0403
  -3.250   0.5316   0.01108   0.00492  -0.1632   0.4554   0.0415
  -3.000   0.5570   0.01102   0.00478  -0.1624   0.4485   0.0420
  -2.750   0.5820   0.01083   0.00449  -0.1617   0.4401   0.0434
  -2.500   0.6067   0.01071   0.00429  -0.1608   0.4299   0.0448
  -2.250   0.6312   0.01066   0.00413  -0.1599   0.4175   0.0455
  -2.000   0.6560   0.01066   0.00406  -0.1591   0.4054   0.0466
  -1.750   0.6804   0.01070   0.00401  -0.1582   0.3920   0.0479
  -1.500   0.7044   0.01070   0.00390  -0.1572   0.3792   0.0486
  -1.250   0.7284   0.01070   0.00379  -0.1562   0.3676   0.0491
  -0.750   0.7762   0.01075   0.00363  -0.1542   0.3457   0.0499
  -0.500   0.8001   0.01079   0.00359  -0.1532   0.3375   0.0504
  -0.250   0.8242   0.01083   0.00355  -0.1522   0.3293   0.0508
   0.000   0.8480   0.01088   0.00354  -0.1512   0.3230   0.0511
   0.250   0.8725   0.01091   0.00352  -0.1503   0.3185   0.0514
   0.500   0.8965   0.01094   0.00351  -0.1494   0.3137   0.0519
   0.750   0.9201   0.01099   0.00350  -0.1483   0.3087   0.0532
   1.000   0.9437   0.01101   0.00349  -0.1473   0.3052   0.0553
   1.250   0.9670   0.01104   0.00350  -0.1462   0.3019   0.0571
   1.500   0.9896   0.01108   0.00353  -0.1450   0.2981   0.0593
   1.750   1.0118   0.01116   0.00358  -0.1437   0.2942   0.0610
   2.000   1.0340   0.01124   0.00364  -0.1424   0.2902   0.0637
   2.250   1.0567   0.01128   0.00371  -0.1413   0.2874   0.0718
   2.500   1.0792   0.01136   0.00382  -0.1401   0.2842   0.0816
   2.750   1.1014   0.01148   0.00392  -0.1389   0.2810   0.0869
   3.000   1.1231   0.01162   0.00405  -0.1376   0.2778   0.0904
   3.250   1.1449   0.01176   0.00419  -0.1363   0.2748   0.0941
   3.500   1.1674   0.01187   0.00431  -0.1351   0.2728   0.0972
   3.750   1.1898   0.01199   0.00443  -0.1340   0.2706   0.0991
   4.000   1.2119   0.01212   0.00456  -0.1328   0.2682   0.1006
   4.250   1.2334   0.01228   0.00470  -0.1316   0.2654   0.1018
   4.500   1.2544   0.01242   0.00486  -0.1302   0.2627   0.1054
   4.750   1.2752   0.01260   0.00503  -0.1289   0.2598   0.1077
   5.000   1.2968   0.01274   0.00519  -0.1277   0.2580   0.1094
   5.250   1.3185   0.01288   0.00535  -0.1265   0.2564   0.1113
   5.500   1.3397   0.01304   0.00553  -0.1253   0.2538   0.1135
   5.750   1.3604   0.01321   0.00571  -0.1240   0.2515   0.1152
   6.000   1.3805   0.01342   0.00591  -0.1226   0.2487   0.1165
   6.250   1.3994   0.01368   0.00615  -0.1210   0.2426   0.1180
   6.500   1.4201   0.01384   0.00635  -0.1198   0.2402   0.1211
   6.750   1.4394   0.01408   0.00658  -0.1184   0.2352   0.1234
   7.000   1.4579   0.01435   0.00685  -0.1168   0.2310   0.1257
   7.250   1.4766   0.01462   0.00713  -0.1153   0.2268   0.1284
   7.500   1.4954   0.01489   0.00740  -0.1139   0.2218   0.1305
   7.750   1.5118   0.01526   0.00775  -0.1121   0.2153   0.1340
   8.000   1.5290   0.01560   0.00810  -0.1104   0.2089   0.1399
   8.250   1.5421   0.01615   0.00858  -0.1082   0.1973   0.1446
   8.500   1.5515   0.01687   0.00920  -0.1055   0.1799   0.1483
   8.750   1.5439   0.01849   0.01053  -0.1004   0.1414   0.1515
   9.000   1.5187   0.02117   0.01289  -0.0933   0.0885   0.1525
   9.250   1.4939   0.02416   0.01566  -0.0871   0.0344   0.1533
   9.500   1.4975   0.02554   0.01706  -0.0846   0.0149   0.1585
   9.750   1.5083   0.02651   0.01807  -0.0830   0.0129   0.1622
  10.000   1.5195   0.02748   0.01911  -0.0815   0.0120   0.1682
  10.250   1.5294   0.02859   0.02027  -0.0801   0.0107   0.1733
  10.500   1.5382   0.02983   0.02157  -0.0786   0.0099   0.1780
  10.750   1.5476   0.03108   0.02288  -0.0774   0.0092   0.1830
  11.000   1.5560   0.03244   0.02431  -0.0761   0.0086   0.1877
  11.250   1.5636   0.03392   0.02584  -0.0750   0.0078   0.1908
  11.500   1.5694   0.03564   0.02763  -0.0738   0.0074   0.1949
  11.750   1.5759   0.03734   0.02940  -0.0728   0.0070   0.1993
  12.000   1.5811   0.03918   0.03132  -0.0719   0.0065   0.2039
  12.250   1.5851   0.04121   0.03341  -0.0710   0.0062   0.2064
  12.500   1.5886   0.04335   0.03562  -0.0702   0.0059   0.2126
  12.750   1.5902   0.04575   0.03810  -0.0695   0.0056   0.2178
  13.000   1.5893   0.04849   0.04093  -0.0688   0.0053   0.2248
  13.500   1.5885   0.05415   0.04680  -0.0680   0.0050   0.2616
  14.000   1.6965   0.06526   0.05908  -0.0956   0.0038   1.0000
  14.250   1.6892   0.06930   0.06321  -0.0954   0.0038   1.0000
  14.500   1.6785   0.07387   0.06790  -0.0955   0.0038   1.0000
  14.750   1.6692   0.07826   0.07238  -0.0955   0.0037   1.0000
  15.000   1.6576   0.08305   0.07728  -0.0957   0.0036   1.0000
  15.250   1.6453   0.08800   0.08234  -0.0961   0.0035   1.0000
  15.500   1.6311   0.09330   0.08776  -0.0966   0.0035   1.0000
  15.750   1.6178   0.09854   0.09310  -0.0971   0.0034   1.0000
  16.000   1.6033   0.10405   0.09873  -0.0979   0.0034   1.0000
  16.250   1.5880   0.10979   0.10458  -0.0989   0.0033   1.0000
  16.500   1.5735   0.11545   0.11035  -0.0999   0.0033   1.0000
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