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RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAF 19 AIRFOIL (raf19-il)
Reynolds number: 200,000
Max Cl/Cd: 62.38 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf19-il-200000.txt
Download as CSV file: xf-raf19-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000   0.0642   0.09759   0.09462  -0.0720   0.9449   0.0426
  -7.750   0.0823   0.09489   0.09192  -0.0767   0.9334   0.0440
  -7.500   0.0963   0.09331   0.09033  -0.0825   0.9201   0.0444
  -7.250   0.1152   0.09095   0.08795  -0.0895   0.9054   0.0446
  -7.000   0.1425   0.08409   0.08107  -0.0899   0.9000   0.0451
  -6.750   0.1723   0.07974   0.07668  -0.0932   0.8883   0.0463
  -6.500   0.2058   0.07610   0.07298  -0.0991   0.8750   0.0487
  -6.250   0.2436   0.07336   0.07012  -0.1096   0.8567   0.0524
  -6.000   0.2839   0.07128   0.06785  -0.1236   0.8360   0.0530
  -5.750   0.3010   0.06585   0.06234  -0.1215   0.8205   0.0537
  -5.500   0.3219   0.06303   0.05940  -0.1218   0.8030   0.0553
  -5.250   0.3403   0.06108   0.05732  -0.1233   0.7845   0.0585
  -5.000   0.3780   0.06044   0.05646  -0.1367   0.7655   0.0628
  -4.750   0.3807   0.05651   0.05249  -0.1309   0.7515   0.0639
  -4.500   0.3947   0.05458   0.05045  -0.1296   0.7368   0.0660
  -4.000   0.4369   0.05033   0.04595  -0.1345   0.7077   0.0757
  -3.750   0.4810   0.04917   0.04452  -0.1437   0.6931   0.0855
  -3.500   0.4859   0.04649   0.04184  -0.1396   0.6807   0.0867
  -3.250   0.5006   0.04489   0.04016  -0.1381   0.6685   0.0895
  -3.000   0.5636   0.04614   0.04093  -0.1491   0.6543   0.0977
  -2.750   0.5718   0.04244   0.03725  -0.1471   0.6427   0.0985
  -2.500   0.5856   0.04033   0.03510  -0.1455   0.6311   0.0992
  -2.250   0.6032   0.03870   0.03338  -0.1446   0.6203   0.1003
  -2.000   0.6235   0.03736   0.03194  -0.1442   0.6089   0.1019
  -1.750   0.6462   0.03618   0.03065  -0.1443   0.5972   0.1038
  -1.500   0.6724   0.03519   0.02950  -0.1451   0.5860   0.1078
  -1.250   0.7223   0.03547   0.02930  -0.1503   0.5743   0.1121
  -1.000   0.7369   0.03319   0.02701  -0.1489   0.5635   0.1129
  -0.750   0.7550   0.03179   0.02554  -0.1478   0.5531   0.1139
  -0.500   0.7759   0.03076   0.02437  -0.1471   0.5430   0.1152
  -0.250   0.7969   0.02988   0.02343  -0.1463   0.5315   0.1172
   0.000   0.8204   0.02915   0.02256  -0.1459   0.5205   0.1202
   0.250   0.8613   0.02967   0.02259  -0.1479   0.5091   0.1271
   0.500   0.8751   0.02779   0.02076  -0.1461   0.4980   0.1285
   0.750   0.8934   0.02693   0.01985  -0.1447   0.4872   0.1302
   1.250   0.9364   0.02582   0.01851  -0.1426   0.4655   0.1373
   1.500   0.9654   0.02548   0.01785  -0.1424   0.4551   0.1433
   1.750   0.9835   0.02464   0.01692  -0.1408   0.4454   0.1450
   2.000   1.0028   0.02411   0.01636  -0.1393   0.4351   0.1473
   2.250   1.0244   0.02377   0.01585  -0.1381   0.4263   0.1518
   2.500   1.0503   0.02237   0.01410  -0.1371   0.4178   0.1327
   2.750   1.0767   0.02090   0.01208  -0.1361   0.4109   0.1287
   3.000   1.0966   0.02103   0.01226  -0.1346   0.4027   0.1328
   3.250   1.1212   0.02080   0.01165  -0.1337   0.3964   0.1432
   3.500   1.1406   0.02099   0.01200  -0.1323   0.3891   0.1490
   3.750   1.1646   0.02091   0.01161  -0.1313   0.3833   0.1584
   4.000   1.1859   0.02105   0.01179  -0.1303   0.3773   0.1637
   4.250   1.2081   0.02118   0.01177  -0.1290   0.3714   0.1732
   4.500   1.2313   0.02137   0.01192  -0.1284   0.3663   0.1797
   4.750   1.2534   0.02155   0.01203  -0.1273   0.3612   0.1860
   5.000   1.2758   0.02161   0.01204  -0.1263   0.3563   0.1886
   5.250   1.3001   0.02180   0.01217  -0.1258   0.3519   0.1920
   5.500   1.3256   0.02212   0.01243  -0.1255   0.3479   0.1969
   5.750   1.3472   0.02231   0.01264  -0.1244   0.3439   0.1993
   6.000   1.3704   0.02257   0.01285  -0.1236   0.3398   0.2016
   6.250   1.3966   0.02281   0.01309  -0.1236   0.3364   0.2047
   6.500   1.4250   0.02326   0.01348  -0.1240   0.3327   0.2089
   6.750   1.4438   0.02354   0.01386  -0.1225   0.3292   0.2134
   7.000   1.4682   0.02386   0.01424  -0.1222   0.3254   0.2198
   7.250   1.4967   0.02426   0.01466  -0.1228   0.3220   0.2272
   7.500   1.5342   0.02487   0.01516  -0.1252   0.3176   0.2356
   7.750   1.5457   0.02507   0.01554  -0.1224   0.3132   0.2423
   8.000   1.5615   0.02526   0.01580  -0.1205   0.3080   0.2510
   8.250   1.5848   0.02562   0.01607  -0.1201   0.3029   0.2636
   8.500   1.5944   0.02596   0.01655  -0.1171   0.2983   0.2760
   8.750   1.6040   0.02624   0.01693  -0.1142   0.2933   0.2922
   9.000   1.6182   0.02655   0.01722  -0.1122   0.2882   0.3173
   9.250   1.6811   0.02695   0.01845  -0.1216   0.2790   1.0000
   9.500   1.6886   0.02739   0.01889  -0.1185   0.2740   1.0000
   9.750   1.6927   0.02798   0.01948  -0.1152   0.2675   1.0000
  10.000   1.6969   0.02862   0.02021  -0.1120   0.2613   1.0000
  10.250   1.7030   0.02940   0.02093  -0.1093   0.2555   1.0000
  10.500   1.7082   0.03023   0.02192  -0.1066   0.2489   1.0000
  10.750   1.7111   0.03130   0.02298  -0.1040   0.2415   1.0000
  11.000   1.7174   0.03236   0.02415  -0.1019   0.2338   1.0000
  11.250   1.7227   0.03361   0.02543  -0.0999   0.2278   1.0000
  11.500   1.7267   0.03505   0.02692  -0.0980   0.2179   1.0000
  11.750   1.7279   0.03682   0.02871  -0.0961   0.2082   1.0000
  12.000   1.7277   0.03886   0.03074  -0.0944   0.1973   1.0000
  12.250   1.7245   0.04133   0.03318  -0.0927   0.1816   1.0000
  12.500   1.7183   0.04421   0.03603  -0.0911   0.1648   1.0000
  12.750   1.7092   0.04753   0.03932  -0.0898   0.1491   1.0000
  13.000   1.6832   0.05289   0.04456  -0.0884   0.1252   1.0000
  13.250   1.6572   0.05862   0.05024  -0.0875   0.1067   1.0000
  13.500   1.6310   0.06473   0.05635  -0.0872   0.0893   1.0000
  13.750   1.6043   0.07127   0.06292  -0.0874   0.0733   1.0000
  14.000   1.5832   0.07732   0.06905  -0.0878   0.0628   1.0000
  14.250   1.5577   0.08421   0.07603  -0.0886   0.0518   1.0000
  14.500   1.5323   0.09133   0.08326  -0.0898   0.0403   1.0000
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