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NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il)
Reynolds number: 50,000
Max Cl/Cd: 30.76 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n5h10-il-50000.txt
Download as CSV file: xf-n5h10-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5288   0.13128   0.12485   0.0046   1.0000   0.1736
 -10.500  -0.5111   0.12574   0.11932   0.0051   1.0000   0.1818
 -10.250  -0.5239   0.12423   0.11792   0.0017   1.0000   0.1884
 -10.000  -0.5043   0.11885   0.11252   0.0025   1.0000   0.1991
  -9.750  -0.5006   0.11512   0.10882   0.0014   1.0000   0.2082
  -9.500  -0.5138   0.11340   0.10721  -0.0015   1.0000   0.2172
  -9.250  -0.5046   0.10943   0.10328  -0.0016   1.0000   0.2312
  -9.000  -0.5001   0.10584   0.09975  -0.0020   1.0000   0.2458
  -8.750  -0.4998   0.10256   0.09655  -0.0027   1.0000   0.2608
  -8.500  -0.5019   0.09946   0.09354  -0.0035   1.0000   0.2759
  -8.000  -0.4802   0.09172   0.08588  -0.0019   1.0000   0.3190
  -7.750  -0.4629   0.08771   0.08189  -0.0003   1.0000   0.3456
  -7.500  -0.4554   0.08456   0.07880   0.0010   1.0000   0.3756
  -7.250  -0.4623   0.08241   0.07677   0.0026   1.0000   0.4080
  -7.000  -0.4389   0.07927   0.07360   0.0071   1.0000   0.4668
  -6.750  -0.3930   0.07493   0.06917   0.0110   1.0000   0.5377
  -5.750  -0.2736   0.06075   0.05487   0.0126   1.0000   0.7331
  -5.500  -0.3466   0.05983   0.05433   0.0140   1.0000   0.6396
  -5.250  -0.4028   0.05959   0.05436   0.0198   1.0000   0.6102
  -5.000  -0.4529   0.05935   0.05432   0.0275   1.0000   0.6030
  -4.750  -0.4995   0.05867   0.05381   0.0347   1.0000   0.6016
  -4.500  -0.5471   0.05737   0.05265   0.0406   1.0000   0.5995
  -4.250  -0.5406   0.04678   0.03965   0.0026   1.0000   0.2134
  -4.000  -0.5181   0.04285   0.03482   0.0032   1.0000   0.1702
  -3.750  -0.4989   0.03996   0.03130   0.0047   1.0000   0.1538
  -3.500  -0.4786   0.03777   0.02834   0.0064   1.0000   0.1439
  -3.250  -0.4593   0.03592   0.02601   0.0079   1.0000   0.1444
  -3.000  -0.4384   0.03410   0.02379   0.0092   1.0000   0.1442
  -2.750  -0.4156   0.03237   0.02171   0.0102   1.0000   0.1434
  -2.500  -0.3924   0.03107   0.02001   0.0112   1.0000   0.1448
  -2.250  -0.3695   0.02968   0.01859   0.0117   1.0000   0.1523
  -2.000  -0.3425   0.02870   0.01730   0.0121   1.0000   0.1580
  -1.750  -0.1173   0.02436   0.01609  -0.0181   1.0000   1.0000
  -1.500  -0.1068   0.02463   0.01578  -0.0156   1.0000   1.0000
  -1.250  -0.0973   0.02489   0.01570  -0.0132   1.0000   1.0000
  -1.000  -0.0874   0.02516   0.01569  -0.0111   0.9999   1.0000
  -0.750  -0.0604   0.02559   0.01579  -0.0123   0.9953   1.0000
  -0.500  -0.0365   0.02602   0.01598  -0.0129   0.9910   1.0000
  -0.250  -0.0152   0.02647   0.01622  -0.0131   0.9873   1.0000
   0.000   0.0089   0.02704   0.01661  -0.0138   0.9835   1.0000
   0.250   0.0271   0.02750   0.01692  -0.0133   0.9800   1.0000
   0.500   0.0436   0.02797   0.01725  -0.0126   0.9769   1.0000
   0.750   0.0616   0.02851   0.01768  -0.0122   0.9738   1.0000
   1.000   0.0824   0.02917   0.01824  -0.0122   0.9706   1.0000
   1.250   0.0985   0.02976   0.01875  -0.0115   0.9680   1.0000
   1.500   0.1112   0.03027   0.01919  -0.0101   0.9653   1.0000
   1.750   0.1262   0.03087   0.01973  -0.0092   0.9622   1.0000
   2.000   0.1475   0.03166   0.02048  -0.0095   0.9579   1.0000
   2.250   0.1717   0.03249   0.02128  -0.0103   0.9498   1.0000
   2.500   0.2069   0.03357   0.02238  -0.0130   0.9376   1.0000
   2.750   0.2422   0.03469   0.02353  -0.0156   0.9250   1.0000
   3.000   0.2639   0.03556   0.02443  -0.0159   0.9147   1.0000
   3.250   0.2825   0.03649   0.02539  -0.0156   0.9056   1.0000
   3.500   0.3092   0.03765   0.02663  -0.0167   0.8953   1.0000
   3.750   0.3400   0.03895   0.02803  -0.0185   0.8840   1.0000
   4.000   0.3534   0.03988   0.02903  -0.0173   0.8727   1.0000
   4.250   0.3734   0.04104   0.03029  -0.0172   0.8600   1.0000
   4.500   0.3973   0.04233   0.03170  -0.0177   0.8456   1.0000
   4.750   0.4225   0.04367   0.03322  -0.0184   0.8305   1.0000
   5.000   0.4524   0.04513   0.03486  -0.0196   0.8138   1.0000
   5.250   0.4662   0.04637   0.03623  -0.0185   0.7977   1.0000
   5.500   0.4873   0.04755   0.03759  -0.0181   0.7772   1.0000
   5.750   0.5443   0.04818   0.03864  -0.0208   0.7441   1.0000
   6.000   0.5804   0.04801   0.03878  -0.0200   0.7090   1.0000
   6.250   0.8055   0.02898   0.02159  -0.0177   0.5835   1.0000
   6.500   0.7954   0.02586   0.01668  -0.0031   0.2897   1.0000
   6.750   0.7796   0.02849   0.01836   0.0026   0.2135   1.0000
   7.000   0.7770   0.03055   0.01987   0.0069   0.1813   1.0000
   7.250   0.7995   0.03252   0.02153   0.0093   0.1561   1.0000
   7.500   0.8500   0.03503   0.02374   0.0084   0.1329   1.0000
   7.750   0.8843   0.03735   0.02630   0.0088   0.1238   1.0000
   8.000   0.9077   0.03999   0.02919   0.0100   0.1161   1.0000
   8.250   0.9273   0.04259   0.03215   0.0116   0.1117   1.0000
   8.500   0.9455   0.04570   0.03560   0.0133   0.1098   1.0000
   8.750   0.9637   0.04928   0.03931   0.0145   0.1072   1.0000
   9.000   0.9720   0.05286   0.04323   0.0166   0.1055   1.0000
   9.250   0.9742   0.05598   0.04682   0.0192   0.1048   1.0000
   9.500   0.9776   0.05981   0.05099   0.0213   0.1052   1.0000
   9.750   0.9774   0.06352   0.05511   0.0236   0.1070   1.0000
  10.000   0.9495   0.06663   0.05882   0.0272   0.1103   1.0000
  10.250   0.9264   0.07060   0.06310   0.0295   0.1130   1.0000
  10.500   0.9047   0.07449   0.06713   0.0313   0.1152   1.0000
  10.750   0.8887   0.07889   0.07161   0.0320   0.1174   1.0000
  11.000   0.8782   0.08379   0.07662   0.0319   0.1211   1.0000
  11.500   0.7826   0.09958   0.09244   0.0223   0.1315   1.0000
  11.750   0.7637   0.11039   0.10321   0.0163   0.1475   1.0000
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