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NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il)
Reynolds number: 100,000
Max Cl/Cd: 48.87 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n5h10-il-100000-n5.txt
Download as CSV file: xf-n5h10-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3909   0.10574   0.10165  -0.0123   1.0000   0.0465
 -10.000  -0.3915   0.10162   0.09755  -0.0147   0.9634   0.0478
  -9.750  -0.4008   0.09716   0.09310  -0.0205   0.9365   0.0500
  -9.250  -0.3908   0.08581   0.08165  -0.0222   0.9151   0.0347
  -9.000  -0.3926   0.08111   0.07693  -0.0239   0.9064   0.0330
  -8.000  -0.4987   0.06916   0.06451  -0.0355   0.8975   0.0264
  -7.750  -0.4984   0.06515   0.06036  -0.0354   0.8885   0.0260
  -7.500  -0.4969   0.06109   0.05613  -0.0351   0.8799   0.0258
  -7.250  -0.4933   0.05706   0.05188  -0.0346   0.8722   0.0257
  -7.000  -0.4884   0.05301   0.04755  -0.0336   0.8652   0.0256
  -6.750  -0.4810   0.04903   0.04327  -0.0324   0.8581   0.0257
  -6.500  -0.4719   0.04517   0.03893  -0.0306   0.8518   0.0262
  -6.250  -0.4624   0.04140   0.03474  -0.0290   0.8453   0.0274
  -6.000  -0.4475   0.03959   0.03283  -0.0281   0.8394   0.0293
  -5.750  -0.4315   0.03689   0.02976  -0.0267   0.8336   0.0303
  -5.500  -0.4142   0.03410   0.02652  -0.0251   0.8276   0.0311
  -5.250  -0.3951   0.03171   0.02364  -0.0234   0.8226   0.0330
  -5.000  -0.3729   0.02964   0.02104  -0.0222   0.8165   0.0362
  -4.750  -0.3495   0.02783   0.01864  -0.0208   0.8116   0.0379
  -4.500  -0.3257   0.02573   0.01635  -0.0204   0.8066   0.0408
  -4.250  -0.3004   0.02472   0.01515  -0.0200   0.8011   0.0454
  -4.000  -0.2736   0.02339   0.01352  -0.0194   0.7967   0.0482
  -3.750  -0.2468   0.02229   0.01224  -0.0192   0.7914   0.0525
  -3.500  -0.2207   0.02138   0.01129  -0.0189   0.7863   0.0564
  -3.250  -0.1950   0.02056   0.01036  -0.0183   0.7823   0.0592
  -3.000  -0.1695   0.01991   0.00961  -0.0179   0.7773   0.0624
  -2.750  -0.1453   0.01931   0.00900  -0.0174   0.7722   0.0681
  -2.500  -0.1213   0.01882   0.00841  -0.0165   0.7682   0.0727
  -2.250  -0.0963   0.01843   0.00790  -0.0160   0.7634   0.0773
  -2.000  -0.0711   0.01799   0.00746  -0.0156   0.7585   0.0861
  -1.750  -0.0453   0.01750   0.00706  -0.0151   0.7548   0.1144
  -1.500   0.1608   0.01597   0.00797  -0.0460   0.7576   1.0000
  -1.250   0.1841   0.01596   0.00780  -0.0453   0.7536   1.0000
  -1.000   0.2084   0.01598   0.00771  -0.0450   0.7487   1.0000
  -0.750   0.2327   0.01600   0.00765  -0.0447   0.7439   1.0000
  -0.500   0.2565   0.01603   0.00758  -0.0441   0.7402   1.0000
  -0.250   0.2804   0.01607   0.00754  -0.0436   0.7366   1.0000
   0.250   0.3291   0.01621   0.00761  -0.0430   0.7274   1.0000
   0.500   0.3527   0.01624   0.00760  -0.0424   0.7243   1.0000
   0.750   0.3774   0.01638   0.00775  -0.0422   0.7198   1.0000
   1.000   0.4016   0.01648   0.00786  -0.0419   0.7150   1.0000
   1.250   0.4249   0.01650   0.00787  -0.0411   0.7110   1.0000
   1.500   0.4487   0.01659   0.00799  -0.0406   0.7055   1.0000
   1.750   0.4724   0.01666   0.00810  -0.0400   0.7000   1.0000
   2.000   0.4956   0.01667   0.00813  -0.0392   0.6961   1.0000
   2.250   0.5194   0.01682   0.00837  -0.0388   0.6902   1.0000
   2.500   0.5429   0.01690   0.00851  -0.0381   0.6850   1.0000
   2.750   0.5660   0.01690   0.00856  -0.0372   0.6812   1.0000
   3.000   0.5895   0.01709   0.00890  -0.0368   0.6745   1.0000
   3.250   0.6122   0.01703   0.00890  -0.0356   0.6683   1.0000
   3.500   0.6343   0.01693   0.00889  -0.0344   0.6573   1.0000
   3.750   0.6559   0.01671   0.00873  -0.0328   0.6450   1.0000
   4.000   0.6774   0.01644   0.00854  -0.0311   0.6297   1.0000
   4.250   0.6983   0.01609   0.00821  -0.0291   0.6101   1.0000
   4.500   0.7192   0.01594   0.00814  -0.0275   0.5855   1.0000
   4.750   0.7403   0.01588   0.00815  -0.0261   0.5598   1.0000
   5.000   0.7614   0.01591   0.00832  -0.0248   0.5347   1.0000
   5.250   0.7809   0.01598   0.00840  -0.0231   0.4807   1.0000
   5.500   0.7928   0.01663   0.00831  -0.0202   0.3508   1.0000
   5.750   0.8031   0.01790   0.00914  -0.0180   0.2612   1.0000
   6.250   0.8168   0.02076   0.01117  -0.0129   0.1110   1.0000
   6.500   0.8261   0.02175   0.01209  -0.0103   0.0848   1.0000
   6.750   0.8351   0.02264   0.01295  -0.0076   0.0692   1.0000
   7.000   0.8433   0.02349   0.01383  -0.0047   0.0616   1.0000
   7.250   0.8503   0.02434   0.01468  -0.0017   0.0547   1.0000
   7.500   0.8568   0.02521   0.01561   0.0014   0.0500   1.0000
   7.750   0.8626   0.02615   0.01661   0.0045   0.0464   1.0000
   8.000   0.8650   0.02738   0.01779   0.0078   0.0426   1.0000
   8.250   0.8728   0.02844   0.01898   0.0105   0.0391   1.0000
   8.500   0.8806   0.02964   0.02028   0.0132   0.0367   1.0000
   8.750   0.8892   0.03109   0.02171   0.0156   0.0338   1.0000
   9.000   0.9052   0.03274   0.02347   0.0171   0.0307   1.0000
   9.250   0.9269   0.03454   0.02549   0.0181   0.0287   1.0000
   9.500   0.9444   0.03637   0.02751   0.0193   0.0265   1.0000
   9.750   0.9561   0.03810   0.02933   0.0208   0.0244   1.0000
  10.000   0.9737   0.04146   0.03280   0.0212   0.0227   1.0000
  10.250   0.9815   0.04364   0.03535   0.0233   0.0221   1.0000
  10.500   0.9848   0.04612   0.03818   0.0257   0.0217   1.0000
  10.750   0.9835   0.04875   0.04115   0.0280   0.0213   1.0000
  11.000   0.9781   0.05156   0.04429   0.0301   0.0208   1.0000
  11.250   0.9697   0.05462   0.04772   0.0319   0.0204   1.0000
  11.500   0.9589   0.05788   0.05126   0.0332   0.0199   1.0000
  11.750   0.9460   0.06154   0.05518   0.0340   0.0197   1.0000
  12.000   0.9318   0.06535   0.05923   0.0341   0.0192   1.0000
  12.250   0.9145   0.06995   0.06405   0.0336   0.0193   1.0000
  12.500   0.8969   0.07488   0.06918   0.0323   0.0195   1.0000
  12.750   0.8763   0.08057   0.07499   0.0301   0.0193   1.0000
  13.000   0.8550   0.08708   0.08166   0.0270   0.0198   1.0000
  13.250   0.8334   0.09439   0.08910   0.0228   0.0200   1.0000
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