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NACA 1410 (naca1410-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 1410 (naca1410-il)
Reynolds number: 200,000
Max Cl/Cd: 56.59 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1410-il-200000.txt
Download as CSV file: xf-naca1410-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1410                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.7100   0.07275   0.06906  -0.0326   1.0000   0.0439
 -10.250  -0.7278   0.06615   0.06242  -0.0369   1.0000   0.0431
 -10.000  -0.7513   0.06061   0.05676  -0.0389   1.0000   0.0424
  -9.750  -0.7729   0.05498   0.05090  -0.0392   1.0000   0.0418
  -9.500  -0.7885   0.04923   0.04481  -0.0387   1.0000   0.0416
  -9.250  -0.7967   0.04395   0.03908  -0.0373   1.0000   0.0417
  -9.000  -0.7977   0.03935   0.03397  -0.0355   1.0000   0.0422
  -8.750  -0.7920   0.03563   0.02974  -0.0335   1.0000   0.0430
  -8.500  -0.7808   0.03353   0.02712  -0.0315   1.0000   0.0445
  -8.250  -0.7694   0.02983   0.02324  -0.0302   1.0000   0.0467
  -8.000  -0.7510   0.02851   0.02182  -0.0290   1.0000   0.0489
  -7.750  -0.7327   0.02690   0.01995  -0.0276   1.0000   0.0511
  -7.500  -0.7135   0.02571   0.01845  -0.0261   1.0000   0.0539
  -7.250  -0.6950   0.02370   0.01614  -0.0247   1.0000   0.0561
  -7.000  -0.6745   0.02228   0.01470  -0.0236   1.0000   0.0588
  -6.750  -0.6533   0.02147   0.01382  -0.0225   1.0000   0.0620
  -6.500  -0.6316   0.02057   0.01275  -0.0213   1.0000   0.0647
  -6.250  -0.6095   0.01991   0.01190  -0.0201   1.0000   0.0669
  -6.000  -0.5886   0.01836   0.01036  -0.0191   1.0000   0.0704
  -5.750  -0.5668   0.01761   0.00961  -0.0180   1.0000   0.0735
  -5.500  -0.5448   0.01692   0.00886  -0.0168   1.0000   0.0768
  -5.250  -0.5227   0.01635   0.00819  -0.0157   1.0000   0.0804
  -5.000  -0.5017   0.01544   0.00737  -0.0146   1.0000   0.0857
  -4.750  -0.4796   0.01490   0.00681  -0.0135   1.0000   0.0919
  -4.500  -0.4580   0.01418   0.00617  -0.0125   1.0000   0.1015
  -4.250  -0.4357   0.01356   0.00561  -0.0116   1.0000   0.1215
  -4.000  -0.4134   0.01285   0.00519  -0.0109   1.0000   0.1622
  -3.750  -0.3904   0.01232   0.00491  -0.0104   1.0000   0.2141
  -3.500  -0.3667   0.01193   0.00475  -0.0100   1.0000   0.2669
  -3.250  -0.3427   0.01158   0.00457  -0.0096   1.0000   0.3167
  -3.000  -0.3188   0.01112   0.00447  -0.0094   1.0000   0.3835
  -2.750  -0.2952   0.01080   0.00452  -0.0089   1.0000   0.4832
  -2.500  -0.2716   0.01053   0.00455  -0.0083   1.0000   0.5594
  -2.250  -0.2434   0.01026   0.00464  -0.0086   0.9983   0.6371
  -2.000  -0.2033   0.01005   0.00473  -0.0109   0.9926   0.7122
  -1.750  -0.1639   0.00992   0.00479  -0.0130   0.9859   0.7760
  -1.500  -0.1275   0.00983   0.00488  -0.0141   0.9781   0.8374
  -1.250  -0.0875   0.00986   0.00500  -0.0157   0.9721   0.8957
  -1.000  -0.0419   0.00992   0.00507  -0.0187   0.9657   0.9375
  -0.750   0.0144   0.00996   0.00507  -0.0241   0.9626   0.9632
  -0.500   0.0743   0.00995   0.00502  -0.0305   0.9596   0.9797
  -0.250   0.1355   0.00986   0.00490  -0.0372   0.9544   0.9925
   0.000   0.1946   0.00966   0.00468  -0.0435   0.9479   1.0000
   0.250   0.2309   0.00943   0.00443  -0.0451   0.9319   1.0000
   0.500   0.2590   0.00925   0.00421  -0.0449   0.9111   1.0000
   0.750   0.2851   0.00909   0.00402  -0.0442   0.8898   1.0000
   1.000   0.3094   0.00898   0.00385  -0.0431   0.8677   1.0000
   1.250   0.3328   0.00892   0.00372  -0.0417   0.8437   1.0000
   1.500   0.3560   0.00890   0.00363  -0.0404   0.8182   1.0000
   1.750   0.3794   0.00893   0.00356  -0.0391   0.7917   1.0000
   2.000   0.4029   0.00899   0.00351  -0.0379   0.7643   1.0000
   2.250   0.4265   0.00909   0.00351  -0.0367   0.7359   1.0000
   2.500   0.4500   0.00922   0.00354  -0.0355   0.7069   1.0000
   2.750   0.4734   0.00937   0.00358  -0.0344   0.6759   1.0000
   3.000   0.4966   0.00956   0.00364  -0.0332   0.6442   1.0000
   3.250   0.5200   0.00976   0.00373  -0.0321   0.6140   1.0000
   3.500   0.5430   0.01000   0.00383  -0.0309   0.5812   1.0000
   3.750   0.5655   0.01025   0.00396  -0.0297   0.5422   1.0000
   4.000   0.5876   0.01055   0.00408  -0.0285   0.5002   1.0000
   4.250   0.6101   0.01086   0.00425  -0.0273   0.4602   1.0000
   4.500   0.6329   0.01119   0.00447  -0.0263   0.4219   1.0000
   4.750   0.6553   0.01158   0.00471  -0.0253   0.3796   1.0000
   5.000   0.6774   0.01203   0.00499  -0.0243   0.3303   1.0000
   5.250   0.6986   0.01262   0.00534  -0.0232   0.2733   1.0000
   5.500   0.7185   0.01342   0.00581  -0.0220   0.2047   1.0000
   5.750   0.7367   0.01456   0.00650  -0.0207   0.1343   1.0000
   6.000   0.7553   0.01572   0.00737  -0.0193   0.1011   1.0000
   6.250   0.7760   0.01660   0.00820  -0.0181   0.0886   1.0000
   6.500   0.7975   0.01743   0.00907  -0.0169   0.0820   1.0000
   6.750   0.8191   0.01824   0.00987  -0.0159   0.0768   1.0000
   7.000   0.8397   0.01937   0.01098  -0.0148   0.0726   1.0000
   7.250   0.8627   0.02017   0.01186  -0.0139   0.0693   1.0000
   7.500   0.8854   0.02106   0.01281  -0.0131   0.0662   1.0000
   7.750   0.9073   0.02220   0.01391  -0.0123   0.0628   1.0000
   8.000   0.9298   0.02371   0.01551  -0.0115   0.0603   1.0000
   8.250   0.9528   0.02466   0.01663  -0.0107   0.0577   1.0000
   8.500   0.9749   0.02563   0.01771  -0.0099   0.0546   1.0000
   8.750   0.9966   0.02692   0.01903  -0.0092   0.0519   1.0000
   9.000   1.0165   0.02940   0.02169  -0.0083   0.0493   1.0000
   9.250   1.0360   0.03055   0.02313  -0.0071   0.0470   1.0000
   9.500   1.0546   0.03219   0.02499  -0.0059   0.0447   1.0000
   9.750   1.0726   0.03356   0.02647  -0.0048   0.0425   1.0000
  10.000   1.0863   0.03710   0.03012  -0.0039   0.0402   1.0000
  10.250   1.0951   0.03919   0.03267  -0.0017   0.0390   1.0000
  10.500   1.1010   0.04192   0.03583   0.0006   0.0379   1.0000
  10.750   1.1024   0.04501   0.03932   0.0030   0.0369   1.0000
  11.000   1.1004   0.04808   0.04272   0.0055   0.0359   1.0000
  11.250   1.0968   0.05084   0.04574   0.0077   0.0350   1.0000
  11.500   1.0937   0.05292   0.04795   0.0101   0.0341   1.0000
  11.750   1.0992   0.05447   0.04949   0.0114   0.0330   1.0000
  12.000   1.0874   0.05764   0.05283   0.0131   0.0327   1.0000
  12.250   1.0654   0.06199   0.05744   0.0139   0.0327   1.0000
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