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ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR12 AIRFOIL (hor12-il)
Reynolds number: 50,000
Max Cl/Cd: 37.96 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor12-il-50000-n5.txt
Download as CSV file: xf-hor12-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR12 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4182   0.11060   0.10300  -0.0197   1.0005   0.0818
  -9.500  -0.4189   0.10590   0.09834  -0.0223   1.0005   0.0811
  -9.250  -0.4183   0.10146   0.09394  -0.0246   1.0005   0.0809
  -9.000  -0.4130   0.09810   0.09062  -0.0259   1.0005   0.0822
  -8.750  -0.4098   0.09453   0.08710  -0.0276   1.0005   0.0837
  -8.500  -0.4099   0.09052   0.08315  -0.0297   1.0005   0.0848
  -8.250  -0.4130   0.08618   0.07888  -0.0320   1.0005   0.0855
  -8.000  -0.4169   0.08136   0.07415  -0.0352   1.0005   0.0857
  -7.750  -0.4200   0.07550   0.06835  -0.0403   1.0005   0.0860
  -7.500  -0.4238   0.06759   0.06048  -0.0485   1.0005   0.0863
  -7.250  -0.4296   0.05361   0.04621  -0.0653   1.0005   0.0879
  -7.000  -0.4154   0.04300   0.03476  -0.0782   1.0005   0.0919
  -6.750  -0.3965   0.04170   0.03350  -0.0781   1.0005   0.0947
  -6.500  -0.3749   0.03864   0.03016  -0.0804   1.0005   0.0983
  -6.250  -0.3494   0.03464   0.02552  -0.0840   1.0005   0.1036
  -6.000  -0.3286   0.03316   0.02397  -0.0842   1.0005   0.1078
  -5.750  -0.3077   0.03193   0.02260  -0.0845   1.0005   0.1145
  -5.500  -0.2865   0.03074   0.02126  -0.0849   1.0005   0.1224
  -5.250  -0.2650   0.02974   0.02004  -0.0852   1.0005   0.1318
  -5.000  -0.2236   0.02887   0.01906  -0.0888   0.9910   0.1450
  -4.750  -0.1791   0.02813   0.01807  -0.0931   0.9809   0.1638
  -4.500  -0.1369   0.02758   0.01744  -0.0966   0.9701   0.1803
  -4.250  -0.0944   0.02689   0.01662  -0.0999   0.9596   0.1957
  -4.000  -0.0508   0.02621   0.01579  -0.1034   0.9501   0.2109
  -3.750  -0.0086   0.02557   0.01508  -0.1064   0.9402   0.2255
  -3.500   0.0294   0.02502   0.01448  -0.1085   0.9275   0.2404
  -3.250   0.0665   0.02451   0.01390  -0.1104   0.9145   0.2554
  -3.000   0.1027   0.02408   0.01341  -0.1120   0.9015   0.2726
  -2.750   0.1382   0.02370   0.01298  -0.1133   0.8888   0.2905
  -2.500   0.1729   0.02339   0.01264  -0.1143   0.8765   0.3101
  -2.250   0.2045   0.02319   0.01244  -0.1148   0.8626   0.3298
  -2.000   0.2350   0.02304   0.01227  -0.1150   0.8487   0.3518
  -1.750   0.2652   0.02292   0.01213  -0.1151   0.8351   0.3749
  -1.500   0.2946   0.02284   0.01205  -0.1150   0.8220   0.3990
  -1.250   0.3242   0.02275   0.01191  -0.1148   0.8097   0.4249
  -1.000   0.3529   0.02267   0.01181  -0.1145   0.7971   0.4516
  -0.750   0.3805   0.02262   0.01178  -0.1141   0.7838   0.4788
  -0.500   0.4082   0.02257   0.01172  -0.1136   0.7711   0.5076
  -0.250   0.4357   0.02248   0.01164  -0.1131   0.7592   0.5377
   0.000   0.4627   0.02236   0.01157  -0.1123   0.7477   0.5692
   0.250   0.4884   0.02231   0.01163  -0.1116   0.7347   0.6024
   0.500   0.5136   0.02222   0.01168  -0.1106   0.7226   0.6398
   0.750   0.5377   0.02207   0.01169  -0.1091   0.7117   0.6867
   1.000   0.5585   0.02185   0.01172  -0.1070   0.7002   0.7575
   1.250   0.5794   0.02153   0.01160  -0.1049   0.6880   0.9995
   1.500   0.6106   0.02184   0.01170  -0.1056   0.6766   0.9995
   1.750   0.6410   0.02211   0.01178  -0.1059   0.6661   0.9995
   2.000   0.6698   0.02250   0.01206  -0.1062   0.6537   0.9995
   2.250   0.6985   0.02286   0.01233  -0.1063   0.6424   0.9995
   2.500   0.7276   0.02312   0.01245  -0.1061   0.6326   0.9995
   2.750   0.7552   0.02355   0.01284  -0.1061   0.6204   0.9995
   3.000   0.7829   0.02396   0.01322  -0.1061   0.6091   0.9995
   3.250   0.8113   0.02426   0.01343  -0.1058   0.5993   0.9995
   3.500   0.8383   0.02471   0.01388  -0.1057   0.5877   0.9995
   3.750   0.8652   0.02518   0.01436  -0.1055   0.5765   0.9995
   4.000   0.8931   0.02551   0.01464  -0.1052   0.5668   0.9995
   4.250   0.9195   0.02600   0.01516  -0.1049   0.5555   0.9995
   4.500   0.9457   0.02651   0.01573  -0.1046   0.5443   0.9995
   4.750   0.9732   0.02686   0.01605  -0.1042   0.5349   0.9995
   5.000   0.9988   0.02740   0.01666  -0.1038   0.5234   0.9995
   5.250   1.0242   0.02797   0.01730  -0.1034   0.5122   0.9995
   5.500   1.0510   0.02835   0.01769  -0.1029   0.5024   0.9995
   5.750   1.0762   0.02889   0.01830  -0.1024   0.4911   0.9995
   6.250   1.1263   0.03000   0.01957  -0.1013   0.4694   0.9995
   6.500   1.1511   0.03054   0.02020  -0.1007   0.4582   0.9995
   6.750   1.1740   0.03127   0.02106  -0.1000   0.4463   0.9995
   7.000   1.1978   0.03186   0.02176  -0.0993   0.4348   0.9995
   7.250   1.2233   0.03223   0.02215  -0.0985   0.4241   0.9995
   7.500   1.2447   0.03296   0.02304  -0.0976   0.4111   0.9995
   7.750   1.2657   0.03369   0.02392  -0.0966   0.3980   0.9995
   8.000   1.2866   0.03435   0.02472  -0.0955   0.3847   0.9995
   8.250   1.3071   0.03495   0.02543  -0.0943   0.3709   0.9995
   8.500   1.3262   0.03557   0.02615  -0.0929   0.3561   0.9995
   8.750   1.3434   0.03624   0.02692  -0.0914   0.3402   0.9995
   9.000   1.3581   0.03698   0.02778  -0.0897   0.3230   0.9995
   9.250   1.3706   0.03781   0.02869  -0.0877   0.3049   0.9995
   9.500   1.3807   0.03876   0.02970  -0.0856   0.2866   0.9995
   9.750   1.3881   0.03988   0.03083  -0.0833   0.2685   0.9995
  10.000   1.3912   0.04139   0.03241  -0.0809   0.2506   0.9995
  10.250   1.3897   0.04313   0.03423  -0.0781   0.2339   0.9995
  10.500   1.3857   0.04522   0.03635  -0.0756   0.2178   0.9995
  10.750   1.3812   0.04770   0.03886  -0.0737   0.2022   0.9995
  11.000   1.3765   0.05051   0.04170  -0.0724   0.1878   0.9995
  11.250   1.3713   0.05363   0.04481  -0.0715   0.1749   0.9995
  11.500   1.3654   0.05699   0.04816  -0.0708   0.1634   0.9995
  11.750   1.3597   0.06064   0.05190  -0.0705   0.1521   0.9995
  12.000   1.3542   0.06437   0.05566  -0.0702   0.1425   0.9995
  12.250   1.3489   0.06800   0.05921  -0.0699   0.1348   0.9995
  12.500   1.3438   0.07197   0.06333  -0.0700   0.1266   0.9995
  13.000   1.3352   0.07965   0.07114  -0.0700   0.1139   0.9995
  13.250   1.3328   0.08314   0.07459  -0.0700   0.1087   0.9995
  13.500   1.3289   0.08721   0.07880  -0.0703   0.1039   0.9995
  13.750   1.3255   0.09125   0.08299  -0.0708   0.0997   0.9995
  14.000   1.3271   0.09433   0.08607  -0.0706   0.0962   0.9995
  14.250   1.3270   0.09792   0.08975  -0.0707   0.0931   0.9995
  14.500   1.3182   0.10338   0.09550  -0.0723   0.0905   0.9995
  14.750   1.3095   0.10887   0.10121  -0.0741   0.0879   0.9995
  15.000   1.3041   0.11372   0.10618  -0.0757   0.0854   0.9995
  15.250   1.3174   0.11462   0.10697  -0.0745   0.0822   0.9995
  15.500   1.2979   0.12283   0.11548  -0.0786   0.0810   0.9995
  15.750   1.2705   0.13335   0.12630  -0.0847   0.0802   0.9995
  16.000   1.2244   0.14986   0.14310  -0.0953   0.0800   0.9995
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