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NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 200,000
Max Cl/Cd: 79.01 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a410-il-200000.txt
Download as CSV file: xf-naca64a410-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A410                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4418   0.08761   0.08425  -0.0479   1.0000   0.0447
  -8.500  -0.4619   0.08524   0.08198  -0.0468   1.0000   0.0447
  -8.250  -0.4820   0.08249   0.07926  -0.0465   1.0000   0.0447
  -8.000  -0.4981   0.07976   0.07651  -0.0459   1.0000   0.0448
  -7.750  -0.5109   0.07698   0.07367  -0.0453   1.0000   0.0449
  -7.500  -0.5205   0.07409   0.07069  -0.0447   1.0000   0.0450
  -7.250  -0.5266   0.07109   0.06754  -0.0440   1.0000   0.0451
  -7.000  -0.5338   0.06380   0.06038  -0.0435   1.0000   0.0463
  -6.750  -0.5131   0.06010   0.05670  -0.0457   0.9972   0.0478
  -6.500  -0.4878   0.05600   0.05248  -0.0500   0.9936   0.0502
  -6.250  -0.4608   0.05105   0.04723  -0.0551   0.9884   0.0546
  -6.000  -0.4315   0.04492   0.04059  -0.0609   0.9842   0.0601
  -5.750  -0.4052   0.04236   0.03797  -0.0628   0.9798   0.0646
  -5.500  -0.3763   0.03930   0.03465  -0.0657   0.9750   0.0756
  -5.250  -0.3427   0.03660   0.03171  -0.0689   0.9718   0.0877
  -5.000  -0.3125   0.03419   0.02907  -0.0710   0.9675   0.1005
  -4.750  -0.2835   0.03188   0.02653  -0.0725   0.9621   0.1144
  -4.500  -0.2336   0.02425   0.01703  -0.0714   0.9603   0.0452
  -4.250  -0.1958   0.02191   0.01435  -0.0734   0.9581   0.0450
  -4.000  -0.1569   0.01978   0.01198  -0.0756   0.9564   0.0456
  -3.750  -0.1292   0.01805   0.01023  -0.0757   0.9510   0.0481
  -3.500  -0.0947   0.01710   0.00929  -0.0773   0.9468   0.0533
  -3.250  -0.0560   0.01623   0.00833  -0.0795   0.9440   0.0574
  -3.000  -0.0159   0.01520   0.00733  -0.0823   0.9419   0.0687
  -2.750   0.0111   0.01474   0.00701  -0.0822   0.9345   0.0938
  -2.500   0.0450   0.01271   0.00648  -0.0849   0.9314   0.4596
  -2.250   0.0787   0.01228   0.00657  -0.0857   0.9283   0.6350
  -2.000   0.1042   0.01225   0.00663  -0.0850   0.9210   0.6853
  -1.750   0.1357   0.01213   0.00653  -0.0852   0.9159   0.7258
  -1.500   0.1663   0.01198   0.00641  -0.0851   0.9107   0.7633
  -1.250   0.1913   0.01182   0.00629  -0.0839   0.9025   0.7943
  -1.000   0.2222   0.01150   0.00601  -0.0838   0.8984   0.8208
  -0.750   0.2435   0.01136   0.00592  -0.0820   0.8889   0.8453
  -0.500   0.2728   0.01109   0.00569  -0.0816   0.8845   0.8692
  -0.250   0.2976   0.01100   0.00564  -0.0806   0.8761   0.8972
   0.000   0.3339   0.01075   0.00539  -0.0818   0.8711   0.9271
   0.250   0.3762   0.01059   0.00523  -0.0847   0.8639   0.9636
   0.500   0.4215   0.01041   0.00501  -0.0884   0.8580   1.0000
   0.750   0.4471   0.01040   0.00495  -0.0882   0.8498   1.0000
   1.000   0.4750   0.01033   0.00482  -0.0883   0.8423   1.0000
   1.250   0.5007   0.01035   0.00480  -0.0879   0.8328   1.0000
   1.500   0.5299   0.01025   0.00465  -0.0879   0.8261   1.0000
   1.750   0.5550   0.01026   0.00468  -0.0874   0.8153   1.0000
   2.000   0.5815   0.01023   0.00463  -0.0869   0.8049   1.0000
   2.250   0.6095   0.01017   0.00455  -0.0867   0.7963   1.0000
   2.500   0.6360   0.01018   0.00459  -0.0864   0.7858   1.0000
   2.750   0.6624   0.01016   0.00456  -0.0858   0.7733   1.0000
   3.000   0.6887   0.01009   0.00447  -0.0851   0.7578   1.0000
   3.250   0.7148   0.01005   0.00438  -0.0843   0.7396   1.0000
   3.500   0.7396   0.01009   0.00444  -0.0835   0.7195   1.0000
   3.750   0.7650   0.01015   0.00445  -0.0826   0.6979   1.0000
   4.000   0.7891   0.01025   0.00455  -0.0816   0.6730   1.0000
   4.250   0.8131   0.01039   0.00466  -0.0806   0.6455   1.0000
   4.500   0.8359   0.01058   0.00479  -0.0794   0.6097   1.0000
   4.750   0.8561   0.01093   0.00494  -0.0776   0.5529   1.0000
   5.000   0.8699   0.01170   0.00521  -0.0749   0.4409   1.0000
   5.250   0.8701   0.01378   0.00611  -0.0706   0.2337   1.0000
   5.500   0.8786   0.01556   0.00716  -0.0680   0.1214   1.0000
   5.750   0.8946   0.01674   0.00799  -0.0661   0.0654   1.0000
   6.000   0.9095   0.01799   0.00919  -0.0640   0.0536   1.0000
   6.250   0.9244   0.01923   0.01051  -0.0618   0.0483   1.0000
   6.500   0.9414   0.02032   0.01164  -0.0601   0.0435   1.0000
   6.750   0.9563   0.02188   0.01318  -0.0582   0.0404   1.0000
   7.000   0.9761   0.02390   0.01523  -0.0569   0.0386   1.0000
   7.250   1.0004   0.02516   0.01660  -0.0562   0.0375   1.0000
   7.500   1.0264   0.02675   0.01831  -0.0557   0.0365   1.0000
   7.750   1.0514   0.02829   0.02001  -0.0551   0.0349   1.0000
   8.000   1.0755   0.02993   0.02181  -0.0545   0.0333   1.0000
   8.250   1.1002   0.03222   0.02438  -0.0539   0.0329   1.0000
   8.500   1.1223   0.03506   0.02758  -0.0527   0.0332   1.0000
   8.750   1.1398   0.03879   0.03179  -0.0509   0.0345   1.0000
   9.000   1.1520   0.04346   0.03691  -0.0487   0.0366   1.0000
  14.250   0.6741   0.15100   0.14782  -0.0448   0.0586   1.0000
  14.500   0.6721   0.15414   0.15095  -0.0462   0.0559   1.0000
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