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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 1,000,000
Max Cl/Cd: 144.34 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n6409-il-1000000-n5.txt
Download as CSV file: xf-n6409-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3661   0.02071   0.01778  -0.1548   0.9288   0.0094
  -9.750  -0.3453   0.01893   0.01579  -0.1552   0.9219   0.0097
  -9.500  -0.3211   0.01770   0.01437  -0.1557   0.9158   0.0100
  -9.250  -0.2974   0.01669   0.01318  -0.1557   0.9091   0.0104
  -9.000  -0.2729   0.01577   0.01207  -0.1558   0.9013   0.0107
  -8.750  -0.2483   0.01505   0.01118  -0.1556   0.8927   0.0109
  -8.500  -0.2246   0.01404   0.00997  -0.1555   0.8833   0.0112
  -8.250  -0.1997   0.01342   0.00922  -0.1553   0.8737   0.0116
  -8.000  -0.1739   0.01296   0.00866  -0.1551   0.8658   0.0119
  -7.750  -0.1481   0.01254   0.00813  -0.1549   0.8581   0.0122
  -7.500  -0.1220   0.01211   0.00759  -0.1547   0.8514   0.0126
  -7.250  -0.0959   0.01173   0.00710  -0.1545   0.8439   0.0130
  -7.000  -0.0698   0.01134   0.00659  -0.1542   0.8364   0.0134
  -6.750  -0.0435   0.01104   0.00618  -0.1540   0.8282   0.0138
  -6.500  -0.0171   0.01073   0.00575  -0.1538   0.8205   0.0141
  -6.250   0.0087   0.01027   0.00516  -0.1535   0.8125   0.0145
  -6.000   0.0348   0.00985   0.00464  -0.1532   0.8041   0.0150
  -5.750   0.0611   0.00959   0.00430  -0.1529   0.7952   0.0155
  -5.500   0.0876   0.00938   0.00401  -0.1526   0.7856   0.0161
  -5.250   0.1142   0.00918   0.00373  -0.1523   0.7768   0.0166
  -5.000   0.1405   0.00896   0.00342  -0.1520   0.7676   0.0170
  -4.750   0.1672   0.00877   0.00314  -0.1517   0.7578   0.0175
  -4.500   0.1936   0.00861   0.00289  -0.1514   0.7475   0.0179
  -4.250   0.2198   0.00845   0.00264  -0.1510   0.7366   0.0184
  -4.000   0.2463   0.00825   0.00238  -0.1507   0.7262   0.0194
  -3.500   0.2992   0.00803   0.00203  -0.1500   0.7054   0.0214
  -3.250   0.3255   0.00796   0.00189  -0.1496   0.6934   0.0224
  -3.000   0.3520   0.00788   0.00174  -0.1493   0.6816   0.0237
  -2.750   0.3783   0.00780   0.00162  -0.1489   0.6697   0.0262
  -2.500   0.4047   0.00776   0.00153  -0.1486   0.6586   0.0291
  -2.250   0.4308   0.00771   0.00145  -0.1482   0.6472   0.0351
  -2.000   0.4571   0.00767   0.00139  -0.1478   0.6351   0.0426
  -1.750   0.4834   0.00766   0.00134  -0.1475   0.6230   0.0494
  -1.500   0.5097   0.00766   0.00131  -0.1471   0.6111   0.0557
  -1.250   0.5358   0.00766   0.00128  -0.1468   0.6003   0.0636
  -1.000   0.5621   0.00768   0.00127  -0.1464   0.5892   0.0716
  -0.750   0.5884   0.00768   0.00127  -0.1461   0.5782   0.0845
  -0.500   0.6145   0.00768   0.00128  -0.1457   0.5678   0.1016
  -0.250   0.6405   0.00771   0.00129  -0.1453   0.5575   0.1162
   0.000   0.6669   0.00773   0.00131  -0.1451   0.5477   0.1300
   0.250   0.6931   0.00775   0.00135  -0.1447   0.5390   0.1474
   0.500   0.7193   0.00779   0.00138  -0.1444   0.5299   0.1640
   0.750   0.7456   0.00782   0.00143  -0.1441   0.5221   0.1814
   1.000   0.7715   0.00787   0.00149  -0.1437   0.5137   0.2044
   1.250   0.7979   0.00789   0.00155  -0.1434   0.5067   0.2269
   1.500   0.8238   0.00793   0.00162  -0.1431   0.4996   0.2561
   1.750   0.8499   0.00794   0.00170  -0.1428   0.4935   0.2911
   2.000   0.8760   0.00796   0.00179  -0.1425   0.4874   0.3308
   2.250   0.9010   0.00786   0.00191  -0.1421   0.4816   0.4420
   2.750   0.9577   0.00706   0.00222  -0.1427   0.4707   1.0000
   3.000   0.9835   0.00717   0.00232  -0.1423   0.4658   1.0000
   3.250   1.0096   0.00727   0.00240  -0.1419   0.4607   1.0000
   3.500   1.0352   0.00739   0.00250  -0.1415   0.4556   1.0000
   3.750   1.0607   0.00752   0.00262  -0.1411   0.4509   1.0000
   4.000   1.0866   0.00762   0.00273  -0.1407   0.4459   1.0000
   4.250   1.1119   0.00776   0.00285  -0.1403   0.4405   1.0000
   4.500   1.1371   0.00789   0.00298  -0.1398   0.4352   1.0000
   4.750   1.1619   0.00805   0.00311  -0.1393   0.4251   1.0000
   5.000   1.1848   0.00829   0.00328  -0.1384   0.4060   1.0000
   5.250   1.2059   0.00865   0.00348  -0.1372   0.3749   1.0000
   5.500   1.2231   0.00923   0.00381  -0.1353   0.3254   1.0000
   5.750   1.2395   0.00988   0.00421  -0.1334   0.2795   1.0000
   6.000   1.2523   0.01076   0.00475  -0.1308   0.2209   1.0000
   6.250   1.2662   0.01153   0.00527  -0.1284   0.1743   1.0000
   6.500   1.2788   0.01233   0.00583  -0.1258   0.1291   1.0000
   6.750   1.2906   0.01303   0.00635  -0.1230   0.0951   1.0000
   7.000   1.3034   0.01365   0.00685  -0.1203   0.0701   1.0000
   7.250   1.3174   0.01422   0.00732  -0.1179   0.0523   1.0000
   7.500   1.3323   0.01473   0.00777  -0.1157   0.0407   1.0000
   7.750   1.3481   0.01520   0.00822  -0.1138   0.0328   1.0000
   8.000   1.3630   0.01572   0.00871  -0.1117   0.0255   1.0000
   8.250   1.3780   0.01624   0.00921  -0.1096   0.0202   1.0000
   8.500   1.3931   0.01676   0.00973  -0.1076   0.0169   1.0000
   8.750   1.4080   0.01729   0.01026  -0.1057   0.0149   1.0000
   9.000   1.4232   0.01781   0.01082  -0.1038   0.0137   1.0000
   9.250   1.4380   0.01836   0.01141  -0.1019   0.0129   1.0000
   9.500   1.4519   0.01897   0.01204  -0.1000   0.0122   1.0000
   9.750   1.4652   0.01964   0.01274  -0.0980   0.0116   1.0000
  10.000   1.4770   0.02039   0.01354  -0.0959   0.0109   1.0000
  10.250   1.4891   0.02116   0.01436  -0.0938   0.0105   1.0000
  10.500   1.5015   0.02193   0.01518  -0.0919   0.0103   1.0000
  10.750   1.5134   0.02275   0.01605  -0.0901   0.0101   1.0000
  11.000   1.5247   0.02362   0.01698  -0.0882   0.0097   1.0000
  11.250   1.5353   0.02458   0.01799  -0.0863   0.0094   1.0000
  11.500   1.5448   0.02564   0.01911  -0.0844   0.0092   1.0000
  11.750   1.5539   0.02676   0.02030  -0.0826   0.0089   1.0000
  12.000   1.5620   0.02800   0.02159  -0.0808   0.0087   1.0000
  12.250   1.5692   0.02936   0.02300  -0.0790   0.0085   1.0000
  12.500   1.5746   0.03091   0.02462  -0.0771   0.0082   1.0000
  12.750   1.5764   0.03282   0.02662  -0.0752   0.0078   1.0000
  13.000   1.5827   0.03443   0.02830  -0.0737   0.0077   1.0000
  13.250   1.5885   0.03612   0.03007  -0.0723   0.0077   1.0000
  13.500   1.5940   0.03790   0.03194  -0.0711   0.0075   1.0000
  13.750   1.5988   0.03982   0.03394  -0.0700   0.0074   1.0000
  14.000   1.6030   0.04188   0.03608  -0.0689   0.0073   1.0000
  14.250   1.6070   0.04401   0.03829  -0.0680   0.0072   1.0000
  14.500   1.6096   0.04637   0.04073  -0.0672   0.0070   1.0000
  14.750   1.6126   0.04876   0.04320  -0.0665   0.0069   1.0000
  15.000   1.6163   0.05114   0.04566  -0.0660   0.0066   1.0000
  15.250   1.6183   0.05376   0.04836  -0.0655   0.0065   1.0000
  15.500   1.6210   0.05637   0.05104  -0.0653   0.0063   1.0000
  15.750   1.6213   0.05936   0.05413  -0.0651   0.0062   1.0000
  16.000   1.6220   0.06236   0.05721  -0.0650   0.0061   1.0000
  16.250   1.6214   0.06562   0.06055  -0.0651   0.0060   1.0000
  16.500   1.6191   0.06916   0.06418  -0.0653   0.0059   1.0000
  16.750   1.6163   0.07287   0.06798  -0.0657   0.0058   1.0000
  17.000   1.6108   0.07707   0.07229  -0.0663   0.0056   1.0000
  17.250   1.6033   0.08166   0.07698  -0.0671   0.0055   1.0000
  17.500   1.6021   0.08535   0.08077  -0.0679   0.0055   1.0000
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