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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 500,000
Max Cl/Cd: 118.58 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n6409-il-500000-n5.txt
Download as CSV file: xf-n6409-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA6409 9%                                     
  
 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  -0.1682   0.09359   0.09116  -0.0743   0.9740   0.0102
  -9.250  -0.1603   0.08762   0.08519  -0.0794   0.9712   0.0108
  -9.000  -0.1535   0.08337   0.08095  -0.0824   0.9644   0.0110
  -8.750  -0.1337   0.08114   0.07871  -0.0858   0.9606   0.0113
  -8.500  -0.1153   0.07742   0.07498  -0.0906   0.9558   0.0115
  -8.250  -0.0970   0.07376   0.07129  -0.0955   0.9487   0.0119
  -7.750  -0.1417   0.02118   0.01733  -0.1516   0.9047   0.0141
  -7.500  -0.1187   0.01893   0.01474  -0.1526   0.8963   0.0147
  -7.250  -0.0931   0.01814   0.01383  -0.1528   0.8883   0.0152
  -7.000  -0.0678   0.01713   0.01262  -0.1530   0.8817   0.0157
  -6.750  -0.0428   0.01604   0.01129  -0.1531   0.8746   0.0162
  -6.500  -0.0171   0.01501   0.00999  -0.1531   0.8681   0.0168
  -6.250   0.0084   0.01418   0.00893  -0.1530   0.8608   0.0173
  -6.000   0.0351   0.01356   0.00810  -0.1529   0.8542   0.0179
  -5.750   0.0606   0.01278   0.00713  -0.1527   0.8462   0.0186
  -5.500   0.0870   0.01221   0.00644  -0.1525   0.8389   0.0192
  -5.250   0.1134   0.01179   0.00591  -0.1523   0.8309   0.0199
  -5.000   0.1401   0.01138   0.00539  -0.1521   0.8234   0.0205
  -4.750   0.1666   0.01101   0.00491  -0.1518   0.8148   0.0213
  -4.500   0.1932   0.01070   0.00448  -0.1516   0.8062   0.0221
  -4.250   0.2199   0.01045   0.00411  -0.1513   0.7972   0.0229
  -4.000   0.2462   0.01006   0.00365  -0.1510   0.7880   0.0241
  -3.750   0.2728   0.00983   0.00334  -0.1507   0.7791   0.0253
  -3.500   0.2992   0.00964   0.00306  -0.1503   0.7689   0.0266
  -3.250   0.3258   0.00947   0.00281  -0.1500   0.7586   0.0283
  -3.000   0.3521   0.00929   0.00257  -0.1496   0.7483   0.0309
  -2.750   0.3784   0.00918   0.00239  -0.1492   0.7379   0.0348
  -2.500   0.4048   0.00905   0.00224  -0.1488   0.7272   0.0403
  -2.250   0.4310   0.00897   0.00210  -0.1484   0.7161   0.0468
  -2.000   0.4570   0.00891   0.00200  -0.1480   0.7044   0.0544
  -1.500   0.5090   0.00883   0.00185  -0.1472   0.6810   0.0726
  -1.250   0.5350   0.00880   0.00180  -0.1467   0.6697   0.0847
  -1.000   0.5607   0.00879   0.00177  -0.1463   0.6579   0.0995
  -0.750   0.5863   0.00879   0.00176  -0.1458   0.6457   0.1151
  -0.500   0.6119   0.00881   0.00175  -0.1453   0.6338   0.1303
  -0.250   0.6377   0.00881   0.00176  -0.1449   0.6225   0.1486
   0.000   0.6634   0.00884   0.00178  -0.1444   0.6115   0.1675
   0.250   0.6888   0.00889   0.00181  -0.1439   0.6003   0.1873
   0.500   0.7142   0.00892   0.00186  -0.1435   0.5894   0.2125
   0.750   0.7399   0.00895   0.00191  -0.1430   0.5793   0.2382
   1.000   0.7651   0.00899   0.00198  -0.1425   0.5694   0.2708
   1.250   0.7904   0.00900   0.00206  -0.1421   0.5598   0.3132
   1.500   0.8157   0.00896   0.00215  -0.1417   0.5512   0.3775
   2.000   0.8714   0.00805   0.00245  -0.1420   0.5342   1.0000
   2.250   0.8966   0.00820   0.00254  -0.1414   0.5267   1.0000
   2.500   0.9223   0.00833   0.00263  -0.1410   0.5193   1.0000
   2.750   0.9472   0.00850   0.00274  -0.1404   0.5124   1.0000
   3.000   0.9730   0.00862   0.00285  -0.1400   0.5058   1.0000
   3.250   0.9980   0.00878   0.00297  -0.1395   0.4994   1.0000
   3.500   1.0234   0.00893   0.00310  -0.1390   0.4935   1.0000
   3.750   1.0486   0.00908   0.00325  -0.1385   0.4874   1.0000
   4.000   1.0732   0.00926   0.00340  -0.1379   0.4817   1.0000
   4.250   1.0986   0.00939   0.00355  -0.1375   0.4760   1.0000
   4.500   1.1233   0.00956   0.00372  -0.1369   0.4704   1.0000
   4.750   1.1480   0.00973   0.00390  -0.1364   0.4650   1.0000
   5.000   1.1728   0.00989   0.00408  -0.1358   0.4590   1.0000
   5.250   1.1963   0.01011   0.00428  -0.1351   0.4520   1.0000
   5.500   1.2197   0.01029   0.00449  -0.1343   0.4405   1.0000
   5.750   1.2402   0.01058   0.00470  -0.1329   0.4190   1.0000
   6.000   1.2585   0.01096   0.00494  -0.1312   0.3860   1.0000
   6.250   1.2741   0.01150   0.00527  -0.1291   0.3448   1.0000
   6.500   1.2885   0.01215   0.00570  -0.1267   0.3036   1.0000
   6.750   1.3007   0.01287   0.00622  -0.1241   0.2623   1.0000
   7.000   1.3090   0.01379   0.00686  -0.1207   0.2116   1.0000
   7.250   1.3144   0.01489   0.00765  -0.1170   0.1572   1.0000
   7.500   1.3196   0.01600   0.00849  -0.1134   0.1102   1.0000
   7.750   1.3279   0.01693   0.00925  -0.1103   0.0786   1.0000
   8.000   1.3381   0.01777   0.01000  -0.1076   0.0579   1.0000
   8.250   1.3498   0.01852   0.01070  -0.1052   0.0447   1.0000
   8.500   1.3620   0.01926   0.01142  -0.1029   0.0356   1.0000
   8.750   1.3741   0.02001   0.01216  -0.1007   0.0290   1.0000
   9.000   1.3855   0.02082   0.01297  -0.0984   0.0239   1.0000
   9.250   1.3972   0.02163   0.01382  -0.0963   0.0206   1.0000
   9.500   1.4081   0.02250   0.01472  -0.0941   0.0184   1.0000
   9.750   1.4199   0.02335   0.01563  -0.0921   0.0172   1.0000
  10.000   1.4303   0.02430   0.01664  -0.0901   0.0161   1.0000
  10.250   1.4396   0.02537   0.01776  -0.0880   0.0152   1.0000
  10.500   1.4469   0.02662   0.01907  -0.0858   0.0144   1.0000
  10.750   1.4554   0.02782   0.02036  -0.0838   0.0140   1.0000
  11.000   1.4636   0.02908   0.02170  -0.0820   0.0136   1.0000
  11.250   1.4710   0.03045   0.02316  -0.0802   0.0132   1.0000
  11.500   1.4773   0.03196   0.02475  -0.0784   0.0128   1.0000
  11.750   1.4837   0.03351   0.02639  -0.0767   0.0124   1.0000
  12.000   1.4891   0.03521   0.02817  -0.0752   0.0120   1.0000
  12.250   1.4936   0.03704   0.03009  -0.0737   0.0116   1.0000
  12.500   1.4962   0.03913   0.03226  -0.0723   0.0113   1.0000
  12.750   1.4965   0.04154   0.03475  -0.0709   0.0110   1.0000
  13.000   1.4944   0.04430   0.03761  -0.0696   0.0107   1.0000
  13.250   1.4953   0.04685   0.04026  -0.0686   0.0106   1.0000
  13.500   1.4979   0.04929   0.04281  -0.0679   0.0104   1.0000
  13.750   1.4995   0.05194   0.04557  -0.0672   0.0103   1.0000
  14.000   1.5005   0.05472   0.04846  -0.0667   0.0101   1.0000
  14.250   1.5018   0.05754   0.05138  -0.0663   0.0099   1.0000
  14.500   1.5031   0.06044   0.05439  -0.0660   0.0097   1.0000
  14.750   1.5037   0.06349   0.05755  -0.0659   0.0095   1.0000
  15.000   1.5043   0.06661   0.06077  -0.0659   0.0092   1.0000
  15.250   1.5048   0.06980   0.06407  -0.0660   0.0090   1.0000
  15.500   1.5047   0.07314   0.06750  -0.0663   0.0088   1.0000
  15.750   1.5044   0.07657   0.07103  -0.0666   0.0086   1.0000
  16.000   1.5033   0.08018   0.07474  -0.0671   0.0085   1.0000
  16.250   1.5016   0.08392   0.07858  -0.0677   0.0084   1.0000
  16.500   1.4992   0.08784   0.08260  -0.0685   0.0082   1.0000
  16.750   1.4961   0.09190   0.08676  -0.0693   0.0081   1.0000
  17.000   1.4915   0.09624   0.09118  -0.0703   0.0079   1.0000
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