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RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RAF 19 AIRFOIL (raf19-il)
Reynolds number: 500,000
Max Cl/Cd: 83.27 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf19-il-500000-n5.txt
Download as CSV file: xf-raf19-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.2073   0.08766   0.08472  -0.1214   0.8250   0.0089
  -9.250   0.2174   0.08498   0.08178  -0.1230   0.7825   0.0088
  -9.000   0.2204   0.08210   0.07877  -0.1232   0.7586   0.0085
  -8.750   0.2260   0.07986   0.07645  -0.1234   0.7434   0.0086
  -8.500   0.2309   0.07767   0.07419  -0.1234   0.7276   0.0090
  -8.250   0.2346   0.07539   0.07185  -0.1233   0.7133   0.0092
  -8.000   0.2353   0.07266   0.06910  -0.1232   0.7018   0.0093
  -7.750   0.2295   0.06944   0.06588  -0.1227   0.6923   0.0099
  -7.500   0.2079   0.06391   0.06036  -0.1234   0.6840   0.0103
  -7.250   0.2038   0.05901   0.05539  -0.1265   0.6759   0.0108
  -7.000   0.2122   0.05636   0.05266  -0.1284   0.6606   0.0111
  -6.750   0.2267   0.05470   0.05095  -0.1296   0.6478   0.0117
  -6.500   0.2417   0.05280   0.04899  -0.1311   0.6336   0.0121
  -6.250   0.2577   0.05086   0.04697  -0.1327   0.6177   0.0127
  -6.000   0.2749   0.04881   0.04482  -0.1346   0.6022   0.0135
  -5.750   0.2930   0.04701   0.04289  -0.1361   0.5840   0.0139
  -5.500   0.3129   0.04491   0.04067  -0.1383   0.5697   0.0147
  -5.250   0.3344   0.04359   0.03931  -0.1396   0.5575   0.0166
  -5.000   0.3569   0.04194   0.03761  -0.1413   0.5477   0.0188
  -4.000   0.4537   0.03629   0.03163  -0.1472   0.5140   0.0366
  -3.750   0.4784   0.03552   0.03078  -0.1478   0.5066   0.0389
  -3.250   0.5337   0.03104   0.02602  -0.1525   0.4937   0.0433
  -3.000   0.5557   0.03150   0.02643  -0.1514   0.4856   0.0444
  -2.500   0.6055   0.02997   0.02475  -0.1521   0.4713   0.0480
  -2.000   0.6529   0.01435   0.00757  -0.1580   0.4636   0.0521
  -1.750   0.6758   0.01344   0.00637  -0.1570   0.4556   0.0529
  -1.500   0.6993   0.01306   0.00582  -0.1561   0.4469   0.0538
  -1.250   0.7231   0.01285   0.00546  -0.1551   0.4369   0.0545
  -1.000   0.7470   0.01270   0.00518  -0.1541   0.4258   0.0552
  -0.750   0.7706   0.01262   0.00498  -0.1531   0.4151   0.0559
  -0.250   0.8172   0.01256   0.00470  -0.1509   0.3913   0.0578
   0.000   0.8403   0.01258   0.00461  -0.1498   0.3801   0.0586
   0.250   0.8629   0.01264   0.00456  -0.1486   0.3692   0.0599
   0.500   0.8857   0.01269   0.00451  -0.1474   0.3589   0.0612
   0.750   0.9081   0.01276   0.00450  -0.1462   0.3502   0.0625
   1.000   0.9299   0.01285   0.00450  -0.1449   0.3418   0.0638
   1.250   0.9520   0.01292   0.00453  -0.1436   0.3355   0.0668
   1.500   0.9740   0.01300   0.00459  -0.1423   0.3296   0.0709
   1.750   0.9953   0.01312   0.00467  -0.1409   0.3245   0.0751
   2.000   1.0173   0.01324   0.00480  -0.1396   0.3201   0.0811
   2.250   1.0393   0.01336   0.00489  -0.1383   0.3157   0.0876
   2.500   1.0605   0.01353   0.00505  -0.1369   0.3114   0.0919
   3.000   1.1033   0.01388   0.00535  -0.1342   0.3040   0.0995
   3.250   1.1251   0.01404   0.00549  -0.1330   0.3004   0.1020
   3.500   1.1461   0.01421   0.00567  -0.1316   0.2965   0.1057
   3.750   1.1662   0.01445   0.00588  -0.1301   0.2927   0.1086
   4.000   1.1871   0.01464   0.00607  -0.1288   0.2899   0.1114
   4.250   1.2087   0.01478   0.00623  -0.1276   0.2873   0.1136
   4.500   1.2299   0.01496   0.00640  -0.1263   0.2845   0.1154
   4.750   1.2504   0.01515   0.00659  -0.1250   0.2816   0.1169
   5.000   1.2702   0.01535   0.00681  -0.1235   0.2787   0.1197
   5.250   1.2893   0.01563   0.00709  -0.1220   0.2760   0.1235
   5.500   1.3097   0.01583   0.00732  -0.1207   0.2738   0.1261
   5.750   1.3304   0.01602   0.00753  -0.1194   0.2718   0.1280
   6.000   1.3506   0.01622   0.00776  -0.1181   0.2695   0.1295
   6.250   1.3701   0.01646   0.00802  -0.1167   0.2668   0.1309
   6.500   1.3891   0.01672   0.00830  -0.1153   0.2642   0.1334
   6.750   1.4070   0.01703   0.00863  -0.1137   0.2613   0.1360
   7.000   1.4246   0.01736   0.00898  -0.1121   0.2586   0.1386
   7.250   1.4446   0.01759   0.00926  -0.1109   0.2539   0.1420
   7.500   1.4621   0.01793   0.00961  -0.1094   0.2488   0.1451
   7.750   1.4775   0.01837   0.01003  -0.1076   0.2440   0.1487
   8.000   1.4959   0.01869   0.01041  -0.1062   0.2399   0.1543
   8.250   1.5129   0.01908   0.01083  -0.1047   0.2346   0.1594
   8.500   1.5264   0.01964   0.01137  -0.1028   0.2282   0.1651
   8.750   1.5429   0.02007   0.01184  -0.1013   0.2216   0.1716
   9.000   1.5541   0.02080   0.01251  -0.0992   0.2108   0.1769
   9.250   1.5635   0.02166   0.01331  -0.0970   0.1963   0.1819
   9.500   1.5653   0.02300   0.01450  -0.0939   0.1718   0.1866
   9.750   1.5475   0.02570   0.01688  -0.0890   0.1278   0.1882
  10.000   1.5206   0.02934   0.02028  -0.0840   0.0836   0.1884
  10.250   1.4939   0.03344   0.02423  -0.0799   0.0388   0.1887
  10.500   1.4900   0.03595   0.02677  -0.0780   0.0176   0.1919
  10.750   1.4961   0.03768   0.02860  -0.0769   0.0150   0.1967
  11.000   1.5008   0.03959   0.03061  -0.0758   0.0135   0.2017
  11.250   1.5057   0.04152   0.03264  -0.0748   0.0125   0.2059
  11.500   1.5101   0.04358   0.03480  -0.0740   0.0117   0.2111
  11.750   1.5133   0.04581   0.03714  -0.0732   0.0110   0.2164
  12.000   1.5145   0.04834   0.03978  -0.0726   0.0102   0.2239
  12.250   1.5125   0.05129   0.04286  -0.0719   0.0097   0.2278
  12.500   1.5135   0.05401   0.04570  -0.0716   0.0094   0.2390
  12.750   1.5130   0.05699   0.04880  -0.0713   0.0090   0.2504
  13.000   1.5107   0.06031   0.05227  -0.0712   0.0085   0.2771
  13.500   1.5904   0.07349   0.06663  -0.0957   0.0070   1.0000
  13.750   1.5805   0.07809   0.07135  -0.0958   0.0068   1.0000
  14.000   1.5703   0.08279   0.07617  -0.0961   0.0066   1.0000
  14.250   1.5584   0.08783   0.08135  -0.0965   0.0065   1.0000
  14.500   1.5452   0.09313   0.08678  -0.0970   0.0064   1.0000
  14.750   1.5315   0.09858   0.09236  -0.0977   0.0063   1.0000
  15.000   1.5171   0.10427   0.09817  -0.0986   0.0062   1.0000
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