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NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il)
Reynolds number: 50,000
Max Cl/Cd: 31.91 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n5h10-il-50000-n5.txt
Download as CSV file: xf-n5h10-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 5-H-10 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4877   0.10445   0.09832  -0.0118   1.0000   0.1152
  -9.000  -0.4988   0.10131   0.09530  -0.0170   1.0000   0.1200
  -8.750  -0.5193   0.09832   0.09244  -0.0230   1.0000   0.1211
  -8.500  -0.4914   0.09277   0.08689  -0.0204   1.0000   0.1249
  -8.250  -0.4998   0.08376   0.07781  -0.0291   1.0000   0.0624
  -8.000  -0.4950   0.07956   0.07360  -0.0298   1.0000   0.0595
  -7.750  -0.4954   0.07532   0.06934  -0.0313   1.0000   0.0570
  -7.250  -0.5080   0.06672   0.06032  -0.0328   1.0000   0.0503
  -7.000  -0.5110   0.06389   0.05746  -0.0306   0.9993   0.0498
  -6.750  -0.4957   0.05940   0.05268  -0.0324   0.9777   0.0493
  -6.500  -0.4785   0.05487   0.04768  -0.0342   0.9638   0.0497
  -6.250  -0.4612   0.05077   0.04301  -0.0351   0.9522   0.0510
  -6.000  -0.4388   0.04733   0.03948  -0.0364   0.9436   0.0537
  -5.750  -0.4163   0.04376   0.03540  -0.0369   0.9350   0.0541
  -5.500  -0.3946   0.04072   0.03186  -0.0367   0.9261   0.0550
  -5.250  -0.3698   0.03825   0.02887  -0.0368   0.9189   0.0593
  -5.000  -0.3468   0.03594   0.02592  -0.0360   0.9105   0.0623
  -4.750  -0.3186   0.03370   0.02297  -0.0357   0.9040   0.0639
  -4.500  -0.2939   0.03177   0.02095  -0.0357   0.8965   0.0691
  -4.250  -0.2631   0.03023   0.01898  -0.0360   0.8908   0.0752
  -4.000  -0.2328   0.02882   0.01712  -0.0360   0.8838   0.0780
  -3.750  -0.1965   0.02730   0.01552  -0.0374   0.8788   0.0843
  -3.500  -0.1611   0.02637   0.01435  -0.0386   0.8730   0.0941
  -3.250  -0.1276   0.02545   0.01331  -0.0395   0.8675   0.1001
  -3.000  -0.0991   0.02481   0.01246  -0.0394   0.8619   0.1077
  -2.500   0.1121   0.02074   0.01090  -0.0643   0.8661   1.0000
  -2.250   0.1353   0.02089   0.01077  -0.0640   0.8589   1.0000
  -2.000   0.1584   0.02105   0.01067  -0.0635   0.8524   1.0000
  -1.750   0.1812   0.02125   0.01065  -0.0631   0.8456   1.0000
  -1.500   0.2039   0.02145   0.01067  -0.0626   0.8395   1.0000
  -1.250   0.2266   0.02169   0.01076  -0.0622   0.8333   1.0000
  -1.000   0.2491   0.02193   0.01086  -0.0617   0.8274   1.0000
  -0.750   0.2717   0.02220   0.01100  -0.0612   0.8220   1.0000
  -0.500   0.2935   0.02250   0.01124  -0.0607   0.8157   1.0000
  -0.250   0.3158   0.02278   0.01143  -0.0601   0.8108   1.0000
   0.000   0.3375   0.02315   0.01176  -0.0597   0.8051   1.0000
   0.250   0.3598   0.02350   0.01207  -0.0593   0.7997   1.0000
   0.500   0.3822   0.02381   0.01234  -0.0586   0.7954   1.0000
   0.750   0.4021   0.02430   0.01285  -0.0581   0.7892   1.0000
   1.000   0.4233   0.02470   0.01326  -0.0574   0.7843   1.0000
   1.250   0.4443   0.02511   0.01369  -0.0566   0.7796   1.0000
   1.500   0.4627   0.02567   0.01432  -0.0558   0.7735   1.0000
   1.750   0.4834   0.02611   0.01480  -0.0549   0.7689   1.0000
   2.000   0.5018   0.02667   0.01542  -0.0539   0.7634   1.0000
   2.250   0.5195   0.02720   0.01604  -0.0528   0.7569   1.0000
   2.500   0.5403   0.02755   0.01648  -0.0515   0.7513   1.0000
   2.750   0.5556   0.02807   0.01709  -0.0498   0.7420   1.0000
   3.000   0.5730   0.02838   0.01751  -0.0480   0.7327   1.0000
   3.250   0.5941   0.02849   0.01775  -0.0463   0.7245   1.0000
   3.500   0.6080   0.02904   0.01843  -0.0444   0.7146   1.0000
   3.750   0.6303   0.02923   0.01877  -0.0431   0.7093   1.0000
   4.000   0.6416   0.02998   0.01968  -0.0411   0.6996   1.0000
   4.250   0.6604   0.03033   0.02025  -0.0396   0.6928   1.0000
   4.500   0.6768   0.03066   0.02077  -0.0375   0.6831   1.0000
   4.750   0.6926   0.03081   0.02111  -0.0351   0.6709   1.0000
   5.000   0.7123   0.03043   0.02094  -0.0325   0.6564   1.0000
   5.250   0.7359   0.02948   0.02023  -0.0295   0.6395   1.0000
   5.500   0.7542   0.02848   0.01944  -0.0258   0.6157   1.0000
   5.750   0.7734   0.02721   0.01836  -0.0218   0.5867   1.0000
   6.000   0.7891   0.02620   0.01752  -0.0177   0.5499   1.0000
   6.250   0.7928   0.02612   0.01757  -0.0134   0.4903   1.0000
   6.500   0.8056   0.02525   0.01571  -0.0077   0.3331   1.0000
   6.750   0.8002   0.02687   0.01676  -0.0032   0.2301   1.0000
   7.000   0.7893   0.02893   0.01817   0.0012   0.1704   1.0000
   7.250   0.7825   0.03080   0.01974   0.0051   0.1414   1.0000
   7.500   0.7783   0.03256   0.02134   0.0088   0.1221   1.0000
   7.750   0.7774   0.03417   0.02288   0.0121   0.1084   1.0000
   8.000   0.7815   0.03568   0.02438   0.0147   0.0966   1.0000
   8.250   0.7892   0.03711   0.02583   0.0170   0.0853   1.0000
   8.500   0.8016   0.03852   0.02721   0.0190   0.0780   1.0000
   8.750   0.8217   0.03976   0.02863   0.0206   0.0691   1.0000
   9.000   0.8535   0.04115   0.03028   0.0215   0.0606   1.0000
   9.250   0.8847   0.04293   0.03209   0.0218   0.0543   1.0000
   9.500   0.9179   0.04551   0.03512   0.0218   0.0489   1.0000
   9.750   0.9391   0.04821   0.03811   0.0226   0.0459   1.0000
  10.000   0.9537   0.05092   0.04087   0.0234   0.0431   1.0000
  10.250   0.9576   0.05399   0.04439   0.0254   0.0414   1.0000
  10.500   0.9564   0.05716   0.04797   0.0276   0.0404   1.0000
  10.750   0.9511   0.06040   0.05154   0.0297   0.0400   1.0000
  11.000   0.9415   0.06383   0.05526   0.0313   0.0397   1.0000
  11.250   0.9287   0.06751   0.05921   0.0325   0.0395   1.0000
  11.500   0.9134   0.07150   0.06343   0.0330   0.0395   1.0000
  11.750   0.8963   0.07585   0.06800   0.0328   0.0395   1.0000
  12.000   0.8779   0.08066   0.07299   0.0317   0.0397   1.0000
  12.250   0.8577   0.08609   0.07857   0.0298   0.0399   1.0000
  12.500   0.8388   0.09190   0.08450   0.0272   0.0404   1.0000
  12.750   0.8177   0.09876   0.09144   0.0236   0.0407   1.0000
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