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


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 1,000,000
Max Cl/Cd: 150.99 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n6409-il-1000000.txt
Download as CSV file: xf-n6409-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1128   0.08228   0.08057  -0.0891   0.9737   0.0150
  -8.500  -0.0962   0.07788   0.07617  -0.0942   0.9717   0.0150
  -7.500  -0.0938   0.01913   0.01606  -0.1571   0.9150   0.0148
  -7.250  -0.0768   0.01594   0.01235  -0.1573   0.9070   0.0153
  -7.000  -0.0537   0.01425   0.01038  -0.1574   0.9007   0.0159
  -6.750  -0.0287   0.01365   0.00969  -0.1571   0.8943   0.0164
  -6.500  -0.0027   0.01308   0.00900  -0.1570   0.8882   0.0169
  -6.250   0.0232   0.01248   0.00825  -0.1568   0.8819   0.0176
  -6.000   0.0494   0.01206   0.00771  -0.1565   0.8749   0.0183
  -5.750   0.0759   0.01160   0.00710  -0.1563   0.8684   0.0188
  -5.500   0.1024   0.01126   0.00664  -0.1560   0.8611   0.0191
  -5.250   0.1265   0.00988   0.00501  -0.1556   0.8544   0.0201
  -5.000   0.1527   0.00949   0.00456  -0.1553   0.8467   0.0209
  -4.750   0.1795   0.00920   0.00419  -0.1550   0.8394   0.0218
  -4.500   0.2061   0.00895   0.00387  -0.1547   0.8310   0.0228
  -4.250   0.2329   0.00872   0.00356  -0.1544   0.8233   0.0236
  -4.000   0.2596   0.00851   0.00326  -0.1541   0.8148   0.0241
  -3.750   0.2855   0.00800   0.00265  -0.1537   0.8065   0.0257
  -3.500   0.3120   0.00781   0.00240  -0.1534   0.7975   0.0273
  -3.250   0.3388   0.00766   0.00220  -0.1531   0.7878   0.0290
  -3.000   0.3655   0.00757   0.00204  -0.1527   0.7784   0.0307
  -2.750   0.3917   0.00736   0.00178  -0.1523   0.7685   0.0353
  -2.500   0.4184   0.00723   0.00162  -0.1520   0.7585   0.0410
  -2.250   0.4448   0.00716   0.00152  -0.1516   0.7481   0.0488
  -2.000   0.4709   0.00710   0.00144  -0.1512   0.7370   0.0585
  -1.750   0.4972   0.00704   0.00137  -0.1508   0.7254   0.0692
  -1.500   0.5236   0.00700   0.00132  -0.1504   0.7141   0.0800
  -1.250   0.5497   0.00698   0.00127  -0.1500   0.7025   0.0918
  -1.000   0.5756   0.00697   0.00125  -0.1496   0.6904   0.1065
  -0.750   0.6014   0.00697   0.00124  -0.1491   0.6777   0.1245
  -0.500   0.6273   0.00698   0.00124  -0.1487   0.6649   0.1449
  -0.250   0.6532   0.00697   0.00126  -0.1483   0.6522   0.1678
   0.000   0.6790   0.00700   0.00128  -0.1479   0.6394   0.1905
   0.250   0.7047   0.00702   0.00132  -0.1474   0.6267   0.2167
   0.500   0.7302   0.00705   0.00136  -0.1470   0.6144   0.2467
   0.750   0.7556   0.00709   0.00142  -0.1465   0.6020   0.2795
   1.000   0.7810   0.00710   0.00149  -0.1460   0.5899   0.3263
   1.250   0.8058   0.00693   0.00158  -0.1456   0.5787   0.4537
   1.500   0.8374   0.00603   0.00179  -0.1467   0.5679   1.0000
   1.750   0.8626   0.00617   0.00185  -0.1461   0.5577   1.0000
   2.000   0.8884   0.00629   0.00192  -0.1457   0.5478   1.0000
   2.250   0.9141   0.00642   0.00199  -0.1452   0.5392   1.0000
   2.500   0.9394   0.00656   0.00208  -0.1447   0.5305   1.0000
   2.750   0.9653   0.00667   0.00216  -0.1443   0.5230   1.0000
   3.000   0.9905   0.00682   0.00226  -0.1438   0.5154   1.0000
   3.250   1.0165   0.00693   0.00236  -0.1435   0.5088   1.0000
   3.500   1.0418   0.00707   0.00247  -0.1430   0.5020   1.0000
   3.750   1.0673   0.00720   0.00258  -0.1426   0.4960   1.0000
   4.000   1.0930   0.00733   0.00270  -0.1421   0.4899   1.0000
   4.250   1.1176   0.00750   0.00284  -0.1416   0.4837   1.0000
   4.500   1.1436   0.00760   0.00295  -0.1412   0.4780   1.0000
   4.750   1.1678   0.00778   0.00311  -0.1406   0.4701   1.0000
   5.000   1.1928   0.00790   0.00323  -0.1401   0.4601   1.0000
   5.250   1.2157   0.00813   0.00338  -0.1392   0.4421   1.0000
   5.500   1.2384   0.00837   0.00354  -0.1382   0.4243   1.0000
   5.750   1.2619   0.00857   0.00371  -0.1375   0.4099   1.0000
   6.000   1.2848   0.00880   0.00390  -0.1366   0.3940   1.0000
   6.250   1.3071   0.00905   0.00410  -0.1356   0.3749   1.0000
   6.500   1.3272   0.00943   0.00436  -0.1343   0.3492   1.0000
   6.750   1.3446   0.00995   0.00472  -0.1325   0.3123   1.0000
   7.000   1.3575   0.01074   0.00523  -0.1299   0.2632   1.0000
   7.250   1.3652   0.01174   0.00589  -0.1264   0.2029   1.0000
   7.500   1.3682   0.01286   0.00666  -0.1221   0.1421   1.0000
   7.750   1.3721   0.01394   0.00744  -0.1179   0.0927   1.0000
   8.000   1.3795   0.01484   0.00816  -0.1145   0.0613   1.0000
   8.250   1.3899   0.01559   0.00881  -0.1117   0.0428   1.0000
   8.500   1.4009   0.01632   0.00947  -0.1090   0.0296   1.0000
   8.750   1.4131   0.01700   0.01013  -0.1065   0.0232   1.0000
   9.000   1.4243   0.01774   0.01087  -0.1040   0.0195   1.0000
   9.250   1.4382   0.01835   0.01153  -0.1019   0.0182   1.0000
   9.500   1.4515   0.01899   0.01221  -0.0998   0.0170   1.0000
   9.750   1.4633   0.01975   0.01300  -0.0976   0.0160   1.0000
  10.000   1.4709   0.02077   0.01408  -0.0948   0.0148   1.0000
  10.250   1.4809   0.02168   0.01506  -0.0925   0.0142   1.0000
  10.500   1.4921   0.02254   0.01598  -0.0905   0.0139   1.0000
  10.750   1.5026   0.02346   0.01697  -0.0885   0.0134   1.0000
  11.000   1.5116   0.02453   0.01810  -0.0864   0.0130   1.0000
  11.250   1.5200   0.02567   0.01930  -0.0843   0.0125   1.0000
  11.500   1.5275   0.02691   0.02060  -0.0823   0.0122   1.0000
  11.750   1.5328   0.02838   0.02212  -0.0802   0.0118   1.0000
  12.000   1.5346   0.03018   0.02400  -0.0779   0.0114   1.0000
  12.250   1.5279   0.03277   0.02672  -0.0751   0.0109   1.0000
  12.500   1.5299   0.03478   0.02883  -0.0733   0.0108   1.0000
  12.750   1.5365   0.03642   0.03054  -0.0720   0.0106   1.0000
  13.000   1.5418   0.03824   0.03244  -0.0707   0.0104   1.0000
  13.250   1.5450   0.04035   0.03463  -0.0695   0.0103   1.0000
  13.500   1.5482   0.04253   0.03690  -0.0684   0.0101   1.0000
  13.750   1.5501   0.04492   0.03938  -0.0674   0.0099   1.0000
  14.000   1.5532   0.04726   0.04180  -0.0665   0.0096   1.0000
  14.250   1.5568   0.04962   0.04423  -0.0659   0.0094   1.0000
  14.500   1.5584   0.05228   0.04698  -0.0653   0.0092   1.0000
  14.750   1.5603   0.05495   0.04972  -0.0649   0.0089   1.0000
  15.000   1.5608   0.05789   0.05273  -0.0646   0.0088   1.0000
  15.250   1.5595   0.06111   0.05603  -0.0645   0.0085   1.0000
  15.500   1.5544   0.06492   0.05993  -0.0644   0.0083   1.0000
  15.750   1.5449   0.06932   0.06444  -0.0643   0.0081   1.0000
  16.000   1.5378   0.07352   0.06877  -0.0643   0.0079   1.0000
  16.250   1.5390   0.07678   0.07213  -0.0647   0.0079   1.0000
  16.500   1.5403   0.08008   0.07553  -0.0653   0.0078   1.0000
  16.750   1.5408   0.08353   0.07908  -0.0659   0.0077   1.0000
  17.000   1.5398   0.08725   0.08291  -0.0666   0.0076   1.0000
  17.250   1.5386   0.09107   0.08683  -0.0675   0.0074   1.0000
  17.500   1.5368   0.09504   0.09091  -0.0685   0.0073   1.0000
  17.750   1.5344   0.09916   0.09514  -0.0696   0.0072   1.0000
  18.000   1.5319   0.10337   0.09945  -0.0710   0.0070   1.0000
  18.250   1.5286   0.10774   0.10393  -0.0725   0.0069   1.0000
  18.500   1.5254   0.11216   0.10845  -0.0741   0.0068   1.0000
  18.750   1.5229   0.11655   0.11293  -0.0759   0.0066   1.0000
  19.000   1.5201   0.12102   0.11749  -0.0778   0.0065   1.0000
  19.250   1.5156   0.12579   0.12236  -0.0799   0.0064   1.0000
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