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ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR12 AIRFOIL (hor12-il)
Reynolds number: 100,000
Max Cl/Cd: 57.79 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor12-il-100000-n5.txt
Download as CSV file: xf-hor12-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4733   0.10211   0.09672  -0.0206   1.0005   0.0493
 -10.000  -0.4669   0.09909   0.09372  -0.0218   1.0005   0.0499
  -9.500  -0.6214   0.04843   0.04271  -0.0699   1.0005   0.0489
  -9.250  -0.6089   0.04381   0.03786  -0.0754   1.0005   0.0496
  -9.000  -0.5902   0.04098   0.03488  -0.0785   1.0005   0.0507
  -8.750  -0.5695   0.03814   0.03181  -0.0816   1.0005   0.0523
  -8.500  -0.5470   0.03486   0.02814  -0.0851   1.0005   0.0543
  -8.250  -0.5224   0.03173   0.02454  -0.0879   1.0005   0.0561
  -8.000  -0.4966   0.02929   0.02169  -0.0898   1.0005   0.0576
  -7.750  -0.4720   0.02817   0.02060  -0.0903   1.0005   0.0594
  -7.500  -0.4471   0.02713   0.01949  -0.0908   1.0005   0.0617
  -7.250  -0.4223   0.02587   0.01806  -0.0913   1.0005   0.0641
  -7.000  -0.3980   0.02456   0.01653  -0.0916   1.0005   0.0664
  -6.750  -0.3749   0.02353   0.01541  -0.0916   1.0005   0.0686
  -6.500  -0.3443   0.02275   0.01463  -0.0929   0.9962   0.0722
  -6.250  -0.3035   0.02172   0.01337  -0.0961   0.9871   0.0783
  -6.000  -0.2636   0.02087   0.01252  -0.0991   0.9773   0.0847
  -5.750  -0.2236   0.02001   0.01155  -0.1019   0.9674   0.0934
  -5.500  -0.1850   0.01938   0.01080  -0.1044   0.9561   0.1038
  -5.250  -0.1474   0.01887   0.01026  -0.1065   0.9441   0.1138
  -5.000  -0.1118   0.01846   0.00978  -0.1082   0.9303   0.1244
  -4.750  -0.0784   0.01815   0.00939  -0.1093   0.9149   0.1367
  -4.500  -0.0463   0.01789   0.00902  -0.1100   0.8991   0.1491
  -4.250  -0.0158   0.01763   0.00873  -0.1104   0.8833   0.1600
  -4.000   0.0138   0.01737   0.00841  -0.1106   0.8677   0.1700
  -3.750   0.0429   0.01715   0.00813  -0.1105   0.8524   0.1820
  -3.500   0.0716   0.01698   0.00786  -0.1104   0.8376   0.1950
  -3.250   0.1001   0.01681   0.00766  -0.1103   0.8233   0.2082
  -3.000   0.1285   0.01664   0.00744  -0.1101   0.8098   0.2216
  -2.750   0.1569   0.01646   0.00721  -0.1099   0.7966   0.2348
  -2.500   0.1856   0.01630   0.00701  -0.1099   0.7833   0.2493
  -2.250   0.2142   0.01616   0.00685  -0.1098   0.7706   0.2653
  -2.000   0.2426   0.01604   0.00672  -0.1096   0.7586   0.2820
  -1.750   0.2710   0.01596   0.00662  -0.1094   0.7472   0.3005
  -1.500   0.2998   0.01590   0.00657  -0.1094   0.7346   0.3212
  -1.250   0.3285   0.01587   0.00654  -0.1094   0.7228   0.3433
  -1.000   0.3570   0.01586   0.00654  -0.1092   0.7117   0.3662
  -0.750   0.3857   0.01587   0.00655  -0.1091   0.7001   0.3914
  -0.500   0.4144   0.01588   0.00659  -0.1090   0.6884   0.4160
  -0.250   0.4429   0.01592   0.00660  -0.1089   0.6776   0.4410
   0.000   0.4713   0.01594   0.00662  -0.1087   0.6669   0.4649
   0.250   0.5000   0.01597   0.00666  -0.1086   0.6555   0.4891
   0.500   0.5283   0.01599   0.00668  -0.1085   0.6452   0.5127
   0.750   0.5566   0.01600   0.00670  -0.1083   0.6346   0.5373
   1.000   0.5848   0.01600   0.00676  -0.1081   0.6235   0.5632
   1.250   0.6126   0.01599   0.00682  -0.1078   0.6136   0.5923
   1.500   0.6400   0.01595   0.00689  -0.1074   0.6029   0.6287
   2.000   0.6871   0.01558   0.00700  -0.1046   0.5832   0.7996
   2.250   0.7122   0.01543   0.00694  -0.1036   0.5723   0.9995
   2.500   0.7415   0.01566   0.00707  -0.1038   0.5619   0.9995
   2.750   0.7704   0.01588   0.00718  -0.1039   0.5524   0.9995
   3.000   0.7993   0.01612   0.00738  -0.1040   0.5412   0.9995
   3.250   0.8279   0.01637   0.00757  -0.1041   0.5311   0.9995
   3.500   0.8563   0.01662   0.00775  -0.1040   0.5213   0.9995
   3.750   0.8847   0.01689   0.00801  -0.1041   0.5106   0.9995
   4.000   0.9128   0.01716   0.00823  -0.1040   0.5009   0.9995
   4.250   0.9407   0.01744   0.00850  -0.1039   0.4907   0.9995
   4.500   0.9685   0.01775   0.00880  -0.1038   0.4800   0.9995
   4.750   0.9961   0.01805   0.00906  -0.1037   0.4702   0.9995
   5.000   1.0236   0.01837   0.00942  -0.1036   0.4594   0.9995
   5.250   1.0509   0.01871   0.00978  -0.1034   0.4491   0.9995
   5.500   1.0779   0.01905   0.01009  -0.1032   0.4397   0.9995
   5.750   1.1048   0.01941   0.01051  -0.1030   0.4285   0.9995
   6.000   1.1314   0.01977   0.01092  -0.1027   0.4178   0.9995
   6.250   1.1576   0.02015   0.01128  -0.1024   0.4074   0.9995
   6.500   1.1836   0.02054   0.01174  -0.1020   0.3957   0.9995
   6.750   1.2093   0.02095   0.01223  -0.1017   0.3839   0.9995
   7.000   1.2344   0.02136   0.01267  -0.1012   0.3715   0.9995
   7.250   1.2589   0.02179   0.01312  -0.1007   0.3577   0.9995
   7.500   1.2825   0.02222   0.01359  -0.1000   0.3404   0.9995
   7.750   1.3050   0.02270   0.01409  -0.0992   0.3204   0.9995
   8.000   1.3265   0.02326   0.01460  -0.0984   0.2997   0.9995
   8.250   1.3479   0.02387   0.01524  -0.0975   0.2797   0.9995
   8.500   1.3688   0.02454   0.01595  -0.0966   0.2618   0.9995
   8.750   1.3887   0.02529   0.01672  -0.0956   0.2436   0.9995
   9.000   1.4070   0.02614   0.01756  -0.0945   0.2250   0.9995
   9.250   1.4239   0.02708   0.01850  -0.0932   0.2060   0.9995
   9.500   1.4390   0.02815   0.01956  -0.0917   0.1855   0.9995
   9.750   1.4507   0.02942   0.02080  -0.0899   0.1652   0.9995
  10.000   1.4601   0.03083   0.02218  -0.0878   0.1454   0.9995
  10.250   1.4660   0.03240   0.02372  -0.0855   0.1280   0.9995
  10.500   1.4672   0.03410   0.02541  -0.0826   0.1146   0.9995
  10.750   1.4660   0.03605   0.02737  -0.0798   0.1045   0.9995
  11.000   1.4643   0.03829   0.02963  -0.0775   0.0962   0.9995
  11.250   1.4632   0.04068   0.03212  -0.0758   0.0898   0.9995
  11.500   1.4601   0.04344   0.03494  -0.0744   0.0845   0.9995
  11.750   1.4564   0.04646   0.03802  -0.0734   0.0804   0.9995
  12.000   1.4548   0.04942   0.04112  -0.0727   0.0764   0.9995
  12.250   1.4508   0.05275   0.04453  -0.0722   0.0732   0.9995
  12.500   1.4444   0.05645   0.04827  -0.0720   0.0707   0.9995
  12.750   1.4424   0.05971   0.05166  -0.0717   0.0682   0.9995
  13.000   1.4403   0.06306   0.05514  -0.0715   0.0658   0.9995
  13.250   1.4372   0.06654   0.05873  -0.0715   0.0638   0.9995
  13.500   1.4334   0.07017   0.06246  -0.0716   0.0619   0.9995
  13.750   1.4288   0.07385   0.06617  -0.0717   0.0602   0.9995
  14.000   1.4271   0.07722   0.06964  -0.0717   0.0585   0.9995
  14.250   1.4257   0.08069   0.07327  -0.0719   0.0567   0.9995
  14.500   1.4243   0.08423   0.07694  -0.0722   0.0550   0.9995
  14.750   1.4225   0.08787   0.08068  -0.0726   0.0534   0.9995
  15.000   1.4204   0.09155   0.08444  -0.0732   0.0520   0.9995
  15.250   1.4196   0.09498   0.08789  -0.0736   0.0506   0.9995
  15.500   1.4191   0.09849   0.09151  -0.0740   0.0493   0.9995
  15.750   1.4166   0.10258   0.09582  -0.0750   0.0481   0.9995
  16.000   1.4132   0.10684   0.10026  -0.0763   0.0468   0.9995
  16.250   1.4099   0.11116   0.10472  -0.0777   0.0456   0.9995
  16.500   1.4073   0.11536   0.10903  -0.0791   0.0444   0.9995
  16.750   1.4058   0.11935   0.11311  -0.0805   0.0434   0.9995
  17.000   1.4073   0.12265   0.11643  -0.0814   0.0423   0.9995
  17.250   1.4057   0.12667   0.12054  -0.0828   0.0414   0.9995
  17.500   1.3946   0.13313   0.12726  -0.0863   0.0407   0.9995
  17.750   1.3822   0.14007   0.13446  -0.0904   0.0400   0.9995
  18.000   1.3681   0.14765   0.14228  -0.0951   0.0393   0.9995
  18.250   1.3512   0.15626   0.15113  -0.1008   0.0388   0.9995
  18.500   1.3278   0.16709   0.16220  -0.1083   0.0384   0.9995
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