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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 200,000
Max Cl/Cd: 87.4 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n6409-il-200000-n5.txt
Download as CSV file: xf-n6409-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2185   0.10530   0.10173  -0.0605   0.9816   0.0286
  -9.000  -0.2076   0.10160   0.09804  -0.0645   0.9768   0.0287
  -8.750  -0.1934   0.09740   0.09384  -0.0689   0.9733   0.0287
  -8.250  -0.1720   0.08756   0.08398  -0.0742   0.9636   0.0229
  -7.750  -0.1381   0.08078   0.07718  -0.0796   0.9565   0.0221
  -7.500  -0.1306   0.07697   0.07338  -0.0830   0.9478   0.0222
  -7.000  -0.0972   0.06681   0.06320  -0.0969   0.9330   0.0233
  -6.500  -0.0542   0.05500   0.05125  -0.1130   0.9174   0.0230
  -6.250  -0.0324   0.05010   0.04627  -0.1192   0.9092   0.0233
  -6.000  -0.0059   0.04660   0.04267  -0.1241   0.9027   0.0238
  -5.750   0.0205   0.04329   0.03925  -0.1284   0.8963   0.0250
  -5.500   0.0495   0.03566   0.03131  -0.1363   0.8884   0.0261
  -5.250   0.0758   0.02239   0.01663  -0.1445   0.8806   0.0269
  -5.000   0.1032   0.01982   0.01343  -0.1454   0.8744   0.0280
  -4.750   0.1340   0.01829   0.01154  -0.1465   0.8698   0.0296
  -4.500   0.1589   0.01748   0.01058  -0.1461   0.8618   0.0308
  -4.250   0.1900   0.01650   0.00937  -0.1468   0.8566   0.0320
  -4.000   0.2159   0.01572   0.00840  -0.1465   0.8486   0.0334
  -3.750   0.2462   0.01495   0.00742  -0.1469   0.8424   0.0353
  -3.500   0.2726   0.01437   0.00675  -0.1466   0.8342   0.0377
  -3.250   0.3024   0.01394   0.00623  -0.1469   0.8274   0.0409
  -3.000   0.3290   0.01350   0.00568  -0.1466   0.8186   0.0442
  -2.750   0.3585   0.01303   0.00514  -0.1468   0.8110   0.0487
  -2.500   0.3850   0.01278   0.00481  -0.1464   0.8015   0.0556
  -2.250   0.4129   0.01250   0.00451  -0.1464   0.7929   0.0651
  -2.000   0.4407   0.01226   0.00424  -0.1463   0.7836   0.0757
  -1.750   0.4675   0.01210   0.00406  -0.1460   0.7734   0.0891
  -1.500   0.4951   0.01194   0.00387  -0.1458   0.7636   0.1037
  -1.250   0.5223   0.01181   0.00371  -0.1456   0.7535   0.1198
  -1.000   0.5488   0.01171   0.00360  -0.1453   0.7427   0.1379
  -0.750   0.5756   0.01162   0.00349  -0.1450   0.7319   0.1577
  -0.500   0.6023   0.01155   0.00342  -0.1447   0.7210   0.1808
  -0.250   0.6285   0.01149   0.00337  -0.1443   0.7095   0.2073
   0.000   0.6544   0.01145   0.00336  -0.1439   0.6982   0.2372
   0.250   0.6804   0.01141   0.00335  -0.1434   0.6870   0.2738
   0.500   0.7060   0.01135   0.00335  -0.1430   0.6758   0.3217
   0.750   0.7307   0.01117   0.00339  -0.1425   0.6644   0.4133
   1.250   0.7890   0.01032   0.00348  -0.1427   0.6426   1.0000
   1.500   0.8146   0.01049   0.00352  -0.1422   0.6320   1.0000
   1.750   0.8399   0.01065   0.00359  -0.1416   0.6212   1.0000
   2.000   0.8652   0.01083   0.00367  -0.1411   0.6112   1.0000
   2.250   0.8905   0.01102   0.00377  -0.1406   0.6018   1.0000
   2.500   0.9156   0.01120   0.00390  -0.1400   0.5920   1.0000
   2.750   0.9408   0.01139   0.00403  -0.1395   0.5833   1.0000
   3.000   0.9659   0.01160   0.00418  -0.1389   0.5746   1.0000
   3.250   0.9909   0.01180   0.00436  -0.1384   0.5663   1.0000
   3.500   1.0159   0.01202   0.00453  -0.1379   0.5586   1.0000
   3.750   1.0409   0.01222   0.00474  -0.1373   0.5508   1.0000
   4.000   1.0658   0.01246   0.00494  -0.1368   0.5436   1.0000
   4.250   1.0905   0.01267   0.00518  -0.1362   0.5363   1.0000
   4.500   1.1152   0.01291   0.00541  -0.1357   0.5294   1.0000
   4.750   1.1399   0.01314   0.00568  -0.1351   0.5226   1.0000
   5.000   1.1643   0.01339   0.00595  -0.1345   0.5159   1.0000
   5.250   1.1887   0.01364   0.00623  -0.1339   0.5094   1.0000
   5.500   1.2128   0.01389   0.00653  -0.1333   0.5025   1.0000
   5.750   1.2369   0.01417   0.00685  -0.1326   0.4961   1.0000
   6.000   1.2603   0.01442   0.00719  -0.1319   0.4885   1.0000
   6.250   1.2823   0.01470   0.00750  -0.1308   0.4785   1.0000
   6.500   1.3006   0.01498   0.00780  -0.1290   0.4609   1.0000
   6.750   1.3159   0.01533   0.00808  -0.1267   0.4380   1.0000
   7.000   1.3310   0.01567   0.00841  -0.1243   0.4124   1.0000
   7.250   1.3443   0.01611   0.00878  -0.1217   0.3827   1.0000
   7.500   1.3533   0.01670   0.00922  -0.1184   0.3442   1.0000
   7.750   1.3577   0.01750   0.00982  -0.1144   0.3014   1.0000
   8.000   1.3578   0.01865   0.01067  -0.1099   0.2497   1.0000
   8.250   1.3554   0.02010   0.01180  -0.1054   0.1932   1.0000
   8.500   1.3524   0.02174   0.01312  -0.1010   0.1406   1.0000
   8.750   1.3515   0.02334   0.01449  -0.0973   0.1007   1.0000
   9.000   1.3524   0.02490   0.01590  -0.0939   0.0730   1.0000
   9.250   1.3558   0.02635   0.01729  -0.0910   0.0556   1.0000
   9.500   1.3603   0.02778   0.01871  -0.0884   0.0449   1.0000
   9.750   1.3650   0.02926   0.02023  -0.0859   0.0380   1.0000
  10.000   1.3697   0.03079   0.02181  -0.0836   0.0331   1.0000
  10.250   1.3737   0.03244   0.02354  -0.0814   0.0302   1.0000
  10.500   1.3788   0.03407   0.02529  -0.0794   0.0281   1.0000
  10.750   1.3824   0.03590   0.02721  -0.0775   0.0264   1.0000
  11.000   1.3834   0.03802   0.02941  -0.0756   0.0250   1.0000
  11.250   1.3841   0.04026   0.03175  -0.0739   0.0239   1.0000
  11.500   1.3869   0.04240   0.03405  -0.0725   0.0230   1.0000
  11.750   1.3894   0.04464   0.03640  -0.0712   0.0220   1.0000
  12.000   1.3912   0.04701   0.03888  -0.0701   0.0211   1.0000
  12.250   1.3927   0.04951   0.04148  -0.0691   0.0203   1.0000
  12.500   1.3928   0.05225   0.04432  -0.0682   0.0198   1.0000
  12.750   1.3913   0.05526   0.04741  -0.0674   0.0192   1.0000
  13.000   1.3889   0.05844   0.05066  -0.0667   0.0188   1.0000
  13.250   1.3914   0.06113   0.05348  -0.0661   0.0185   1.0000
  13.500   1.3941   0.06385   0.05634  -0.0656   0.0181   1.0000
  13.750   1.3970   0.06657   0.05919  -0.0651   0.0177   1.0000
  14.000   1.4003   0.06929   0.06204  -0.0647   0.0172   1.0000
  14.250   1.4038   0.07204   0.06491  -0.0644   0.0167   1.0000
  14.500   1.4070   0.07486   0.06785  -0.0643   0.0162   1.0000
  14.750   1.4098   0.07778   0.07087  -0.0643   0.0157   1.0000
  15.000   1.4121   0.08080   0.07399  -0.0644   0.0152   1.0000
  15.250   1.4147   0.08380   0.07708  -0.0644   0.0149   1.0000
  15.500   1.4172   0.08682   0.08019  -0.0644   0.0146   1.0000
  15.750   1.4203   0.08978   0.08326  -0.0642   0.0143   1.0000
  16.000   1.4215   0.09318   0.08686  -0.0645   0.0141   1.0000
  16.250   1.4213   0.09689   0.09079  -0.0651   0.0139   1.0000
  16.500   1.4194   0.10091   0.09503  -0.0659   0.0136   1.0000
  16.750   1.4161   0.10523   0.09957  -0.0671   0.0133   1.0000
  17.000   1.4114   0.10984   0.10440  -0.0686   0.0130   1.0000
  17.250   1.4057   0.11471   0.10947  -0.0704   0.0128   1.0000
  17.500   1.3993   0.11979   0.11476  -0.0725   0.0125   1.0000
  17.750   1.3918   0.12520   0.12035  -0.0749   0.0123   1.0000
  18.000   1.3835   0.13085   0.12620  -0.0778   0.0121   1.0000
  18.250   1.3739   0.13693   0.13248  -0.0810   0.0120   1.0000
  18.500   1.3633   0.14339   0.13913  -0.0846   0.0118   1.0000
  18.750   1.3513   0.15039   0.14633  -0.0888   0.0118   1.0000
  19.000   1.3376   0.15808   0.15422  -0.0936   0.0117   1.0000
  19.250   1.3209   0.16694   0.16329  -0.0994   0.0117   1.0000
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