Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-412 (naca651412-il)
Reynolds number: 50,000
Max Cl/Cd: 30.71 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651412-il-50000-n5.txt
Download as CSV file: xf-naca651412-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-412                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4292   0.10970   0.10229  -0.0463   1.0000   0.0657
 -10.500  -0.4275   0.10574   0.09837  -0.0472   1.0000   0.0636
 -10.000  -0.4622   0.09168   0.08453  -0.0586   1.0000   0.0556
  -9.750  -0.4657   0.08770   0.08062  -0.0594   1.0000   0.0552
  -9.500  -0.4749   0.08379   0.07677  -0.0603   1.0000   0.0550
  -9.250  -0.4871   0.08035   0.07341  -0.0603   1.0000   0.0546
  -9.000  -0.5058   0.07747   0.07060  -0.0592   1.0000   0.0543
  -8.750  -0.5249   0.07488   0.06806  -0.0572   1.0000   0.0541
  -8.500  -0.5435   0.07227   0.06547  -0.0550   1.0000   0.0539
  -8.250  -0.5596   0.06976   0.06293  -0.0524   1.0000   0.0537
  -8.000  -0.5750   0.06715   0.06024  -0.0498   1.0000   0.0536
  -7.750  -0.5870   0.06446   0.05742  -0.0474   1.0000   0.0536
  -7.500  -0.5963   0.06161   0.05437  -0.0451   1.0000   0.0538
  -7.250  -0.6009   0.05869   0.05122  -0.0431   1.0000   0.0538
  -7.000  -0.6019   0.05571   0.04795  -0.0413   1.0000   0.0539
  -6.750  -0.5906   0.05215   0.04400  -0.0416   0.9971   0.0537
  -6.500  -0.5671   0.04821   0.03949  -0.0436   0.9909   0.0537
  -6.250  -0.5402   0.04471   0.03540  -0.0456   0.9853   0.0541
  -6.000  -0.5131   0.04191   0.03193  -0.0469   0.9789   0.0558
  -5.750  -0.4849   0.03925   0.02910  -0.0486   0.9741   0.0583
  -5.500  -0.4567   0.03710   0.02661  -0.0494   0.9685   0.0598
  -5.250  -0.4239   0.03510   0.02422  -0.0507   0.9640   0.0613
  -5.000  -0.3954   0.03353   0.02236  -0.0510   0.9583   0.0638
  -4.750  -0.3637   0.03233   0.02077  -0.0517   0.9533   0.0679
  -4.500  -0.3307   0.03095   0.01939  -0.0525   0.9497   0.0714
  -4.250  -0.3065   0.03004   0.01838  -0.0518   0.9433   0.0746
  -4.000  -0.2766   0.02925   0.01739  -0.0521   0.9382   0.0805
  -3.750  -0.2474   0.02836   0.01648  -0.0529   0.9334   0.0889
  -3.500  -0.2238   0.02767   0.01562  -0.0526   0.9267   0.0971
  -3.250  -0.1936   0.02669   0.01471  -0.0540   0.9219   0.1161
  -3.000  -0.1697   0.02518   0.01376  -0.0548   0.9161   0.1909
  -2.750  -0.1654   0.02380   0.01466  -0.0494   0.9098   0.6499
  -2.500  -0.1509   0.02466   0.01560  -0.0438   0.9047   0.7510
  -2.250  -0.1528   0.02548   0.01647  -0.0348   0.8964   0.8139
  -2.000  -0.1349   0.02626   0.01717  -0.0286   0.8922   0.8745
  -1.750  -0.1047   0.02625   0.01688  -0.0294   0.8874   0.8877
  -1.500  -0.0803   0.02620   0.01660  -0.0295   0.8810   0.8985
  -1.250  -0.0435   0.02617   0.01632  -0.0318   0.8769   0.9074
  -1.000  -0.0129   0.02617   0.01613  -0.0331   0.8718   0.9167
  -0.750   0.0149   0.02620   0.01600  -0.0340   0.8659   0.9272
  -0.500   0.0556   0.02623   0.01586  -0.0372   0.8622   0.9352
  -0.250   0.0922   0.02630   0.01580  -0.0398   0.8577   0.9441
   0.000   0.1236   0.02643   0.01584  -0.0416   0.8517   0.9542
   0.250   0.1675   0.02653   0.01584  -0.0456   0.8480   0.9620
   0.500   0.2146   0.02662   0.01585  -0.0500   0.8451   0.9689
   0.750   0.2465   0.02689   0.01610  -0.0523   0.8384   0.9801
   1.000   0.2891   0.02704   0.01623  -0.0562   0.8339   0.9893
   1.250   0.3337   0.02717   0.01636  -0.0603   0.8307   0.9999
   1.750   0.3477   0.02765   0.01683  -0.0550   0.8156   1.0000
   2.000   0.3471   0.02811   0.01726  -0.0514   0.8062   1.0000
   2.250   0.3759   0.02837   0.01753  -0.0523   0.8014   1.0000
   2.500   0.3897   0.02890   0.01806  -0.0511   0.7936   1.0000
   2.750   0.4167   0.02927   0.01849  -0.0518   0.7879   1.0000
   3.000   0.4440   0.02968   0.01894  -0.0524   0.7824   1.0000
   3.250   0.4631   0.03027   0.01958  -0.0520   0.7744   1.0000
   3.500   0.4992   0.03051   0.01994  -0.0537   0.7702   1.0000
   3.750   0.5128   0.03125   0.02075  -0.0524   0.7602   1.0000
   4.000   0.5494   0.03143   0.02108  -0.0540   0.7554   1.0000
   4.250   0.5641   0.03219   0.02196  -0.0528   0.7450   1.0000
   4.750   0.6174   0.03302   0.02312  -0.0532   0.7288   1.0000
   5.000   0.6422   0.03339   0.02368  -0.0529   0.7186   1.0000
   5.250   0.6827   0.03305   0.02364  -0.0540   0.7108   1.0000
   5.500   0.7051   0.03328   0.02410  -0.0531   0.6977   1.0000
   5.750   0.7314   0.03325   0.02434  -0.0523   0.6844   1.0000
   6.000   0.7913   0.02812   0.01953  -0.0494   0.6337   1.0000
   6.250   0.7991   0.02666   0.01808  -0.0435   0.5671   1.0000
   6.500   0.8105   0.02639   0.01784  -0.0397   0.4931   1.0000
   6.750   0.8184   0.02711   0.01672  -0.0344   0.2474   1.0000
   7.000   0.8093   0.02981   0.01861  -0.0308   0.1536   1.0000
   7.250   0.8094   0.03212   0.02055  -0.0284   0.1153   1.0000
   7.500   0.8152   0.03408   0.02234  -0.0265   0.0969   1.0000
   7.750   0.8247   0.03582   0.02406  -0.0249   0.0858   1.0000
   8.000   0.8361   0.03754   0.02576  -0.0235   0.0791   1.0000
   8.250   0.8529   0.03896   0.02731  -0.0223   0.0720   1.0000
   8.500   0.8740   0.04041   0.02878  -0.0214   0.0662   1.0000
   8.750   0.9135   0.04155   0.03016  -0.0215   0.0613   1.0000
   9.000   0.9569   0.04325   0.03184  -0.0228   0.0563   1.0000
   9.250   0.9997   0.04552   0.03447  -0.0242   0.0525   1.0000
   9.500   1.0375   0.04845   0.03782  -0.0254   0.0506   1.0000
   9.750   1.0624   0.05145   0.04119  -0.0254   0.0493   1.0000
  10.000   1.0791   0.05430   0.04434  -0.0247   0.0478   1.0000
  10.250   1.0917   0.05711   0.04737  -0.0238   0.0463   1.0000
  10.500   1.1037   0.06059   0.05099  -0.0232   0.0449   1.0000
  10.750   1.1007   0.06360   0.05437  -0.0207   0.0443   1.0000
  11.000   1.0942   0.06676   0.05790  -0.0182   0.0441   1.0000
  11.250   1.0854   0.07019   0.06170  -0.0161   0.0440   1.0000
  11.500   1.0735   0.07383   0.06564  -0.0143   0.0439   1.0000
  11.750   1.0595   0.07774   0.06982  -0.0131   0.0439   1.0000
  12.000   1.0434   0.08199   0.07432  -0.0125   0.0440   1.0000
  12.250   1.0258   0.08663   0.07919  -0.0127   0.0441   1.0000
  12.500   1.0069   0.09175   0.08451  -0.0136   0.0442   1.0000
  12.750   0.9877   0.09733   0.09027  -0.0153   0.0444   1.0000
  13.000   0.9690   0.10339   0.09647  -0.0179   0.0445   1.0000
  13.250   0.9511   0.10994   0.10311  -0.0211   0.0447   1.0000
  13.500   0.8873   0.12695   0.12038  -0.0344   0.0469   1.0000
<< Back to NACA 65(1)-412 (naca651412-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(1)-412 (naca651412-il)