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ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR07 AIRFOIL (hor07-il)
Reynolds number: 100,000
Max Cl/Cd: 61.13 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor07-il-100000.txt
Download as CSV file: xf-hor07-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR07 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4276   0.11625   0.11139  -0.0024   1.0000   0.0711
  -8.500  -0.4318   0.11542   0.11064  -0.0074   1.0000   0.0719
  -8.250  -0.4329   0.11398   0.10928  -0.0132   1.0000   0.0722
  -8.000  -0.4100   0.10554   0.10081  -0.0071   1.0000   0.0741
  -7.750  -0.3984   0.10187   0.09716  -0.0069   1.0000   0.0764
  -7.500  -0.3909   0.09885   0.09416  -0.0080   1.0000   0.0790
  -7.250  -0.3860   0.09614   0.09151  -0.0102   1.0000   0.0821
  -7.000  -0.3745   0.09482   0.09023  -0.0259   1.0000   0.0852
  -6.750  -0.3663   0.08944   0.08492  -0.0231   1.0000   0.0866
  -6.500  -0.3551   0.08583   0.08134  -0.0188   1.0000   0.0900
  -6.250  -0.3406   0.08272   0.07826  -0.0223   1.0000   0.0954
  -6.000  -0.3147   0.07869   0.07421  -0.0371   1.0000   0.1001
  -5.750  -0.3071   0.07508   0.07067  -0.0324   1.0000   0.1022
  -5.500  -0.2920   0.07197   0.06760  -0.0331   1.0000   0.1062
  -5.250  -0.2549   0.06760   0.06313  -0.0484   1.0000   0.1146
  -5.000  -0.2502   0.06462   0.06026  -0.0445   1.0000   0.1164
  -4.750  -0.2160   0.06254   0.05796  -0.0559   1.0000   0.1280
  -4.500  -0.2229   0.06009   0.05565  -0.0525   1.0000   0.1289
  -4.250  -0.2278   0.05823   0.05389  -0.0486   1.0000   0.1300
  -4.000  -0.1916   0.05445   0.05009  -0.0524   0.9940   0.1364
  -3.750  -0.1154   0.04968   0.04483  -0.0697   0.9869   0.1576
  -3.500  -0.0388   0.03436   0.02859  -0.0857   0.9847   0.0876
  -3.250   0.0207   0.02699   0.02021  -0.0940   0.9803   0.0762
  -3.000   0.0731   0.02296   0.01532  -0.0993   0.9743   0.0766
  -2.750   0.1250   0.02079   0.01262  -0.1040   0.9696   0.0872
  -2.500   0.1694   0.01941   0.01109  -0.1072   0.9600   0.1031
  -2.250   0.2138   0.01842   0.00998  -0.1104   0.9510   0.1310
  -2.000   0.2562   0.01765   0.00920  -0.1130   0.9411   0.1741
  -1.750   0.2920   0.01725   0.00889  -0.1144   0.9282   0.2234
  -1.500   0.3248   0.01698   0.00856  -0.1151   0.9142   0.2609
  -1.250   0.3540   0.01678   0.00836  -0.1149   0.8994   0.2934
  -1.000   0.3811   0.01651   0.00810  -0.1142   0.8845   0.3231
  -0.750   0.4071   0.01621   0.00782  -0.1133   0.8700   0.3503
  -0.500   0.4324   0.01599   0.00770  -0.1122   0.8563   0.3820
  -0.250   0.4582   0.01569   0.00752  -0.1114   0.8436   0.4289
   0.000   0.4812   0.01476   0.00745  -0.1099   0.8318   0.6325
   0.500   0.5302   0.01458   0.00718  -0.1070   0.8069   1.0000
   0.750   0.5567   0.01483   0.00726  -0.1064   0.7936   1.0000
   1.000   0.5831   0.01509   0.00738  -0.1057   0.7805   1.0000
   1.250   0.6095   0.01535   0.00752  -0.1051   0.7677   1.0000
   1.500   0.6360   0.01562   0.00769  -0.1044   0.7554   1.0000
   1.750   0.6623   0.01589   0.00784  -0.1037   0.7434   1.0000
   2.000   0.6886   0.01615   0.00802  -0.1029   0.7312   1.0000
   2.250   0.7154   0.01644   0.00827  -0.1025   0.7177   1.0000
   2.500   0.7422   0.01674   0.00854  -0.1020   0.7045   1.0000
   2.750   0.7690   0.01704   0.00883  -0.1016   0.6917   1.0000
   3.000   0.7958   0.01732   0.00912  -0.1012   0.6793   1.0000
   3.250   0.8226   0.01759   0.00936  -0.1006   0.6677   1.0000
   3.500   0.8495   0.01785   0.00961  -0.1001   0.6565   1.0000
   3.750   0.8769   0.01821   0.01008  -0.1000   0.6446   1.0000
   4.000   0.9040   0.01857   0.01050  -0.0998   0.6336   1.0000
   4.250   0.9310   0.01884   0.01080  -0.0993   0.6235   1.0000
   4.500   0.9576   0.01899   0.01096  -0.0986   0.6114   1.0000
   4.750   0.9833   0.01895   0.01100  -0.0976   0.5938   1.0000
   5.000   1.0081   0.01864   0.01067  -0.0961   0.5704   1.0000
   5.250   1.0329   0.01837   0.01040  -0.0947   0.5457   1.0000
   5.500   1.0578   0.01819   0.01020  -0.0934   0.5204   1.0000
   5.750   1.0823   0.01808   0.01019  -0.0923   0.4885   1.0000
   6.000   1.1058   0.01809   0.01019  -0.0909   0.4423   1.0000
   6.250   1.1178   0.01987   0.01070  -0.0885   0.1979   1.0000
   6.500   1.1290   0.02311   0.01309  -0.0870   0.1192   1.0000
   6.750   1.1477   0.02465   0.01459  -0.0858   0.1038   1.0000
   7.000   1.1655   0.02615   0.01611  -0.0844   0.0957   1.0000
   7.250   1.1830   0.02778   0.01772  -0.0828   0.0912   1.0000
   7.500   1.2034   0.02926   0.01923  -0.0814   0.0875   1.0000
   7.750   1.2256   0.03091   0.02086  -0.0803   0.0845   1.0000
   8.000   1.2502   0.03303   0.02286  -0.0796   0.0817   1.0000
   8.250   1.2757   0.03526   0.02521  -0.0790   0.0787   1.0000
   8.500   1.3008   0.03727   0.02748  -0.0781   0.0767   1.0000
   8.750   1.3255   0.03975   0.03025  -0.0773   0.0752   1.0000
   9.000   1.3473   0.04224   0.03301  -0.0763   0.0724   1.0000
   9.250   1.3682   0.04526   0.03615  -0.0757   0.0690   1.0000
   9.500   1.3832   0.05005   0.04131  -0.0746   0.0664   1.0000
   9.750   1.3930   0.05273   0.04462  -0.0722   0.0646   1.0000
  10.000   1.3995   0.05631   0.04875  -0.0698   0.0628   1.0000
  10.250   1.4018   0.06003   0.05294  -0.0674   0.0610   1.0000
  10.500   1.3992   0.06442   0.05778  -0.0649   0.0606   1.0000
  10.750   1.3900   0.06945   0.06325  -0.0622   0.0617   1.0000
  11.000   1.3771   0.07450   0.06865  -0.0597   0.0630   1.0000
  11.250   1.3617   0.07947   0.07387  -0.0574   0.0643   1.0000
  11.500   1.2269   0.07453   0.06921  -0.0416   0.0637   1.0000
  11.750   1.1994   0.07971   0.07459  -0.0406   0.0643   1.0000
  12.000   1.1724   0.08536   0.08040  -0.0404   0.0650   1.0000
  12.250   1.1465   0.09145   0.08662  -0.0408   0.0657   1.0000
  12.500   1.0523   0.10368   0.09931  -0.0477   0.0756   1.0000
  12.750   1.0159   0.11159   0.10730  -0.0513   0.0776   1.0000
  13.000   1.0017   0.11712   0.11284  -0.0519   0.0794   1.0000
  13.250   1.0684   0.17583   0.17126  -0.1119   0.1523   1.0000
  13.500   1.0908   0.17827   0.17378  -0.1082   0.1433   1.0000
  13.750   0.8157   0.16641   0.16200  -0.0860   0.1624   1.0000
  14.000   0.8530   0.17085   0.16655  -0.0826   0.1543   1.0000
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