Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR12 AIRFOIL (hor12-il)
Reynolds number: 200,000
Max Cl/Cd: 76.18 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor12-il-200000-n5.txt
Download as CSV file: xf-hor12-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5121   0.13457   0.13064  -0.0003   1.0005   0.0285
 -12.250  -0.5250   0.12550   0.12157  -0.0045   1.0005   0.0294
 -11.250  -0.8029   0.04578   0.04116  -0.0634   1.0005   0.0310
 -11.000  -0.7895   0.03934   0.03442  -0.0748   1.0005   0.0315
 -10.750  -0.7713   0.03606   0.03091  -0.0794   1.0005   0.0323
 -10.500  -0.7506   0.03330   0.02789  -0.0828   1.0005   0.0332
 -10.250  -0.7279   0.03087   0.02515  -0.0855   1.0005   0.0341
 -10.000  -0.7033   0.02883   0.02280  -0.0875   1.0005   0.0349
  -9.750  -0.6786   0.02711   0.02099  -0.0889   1.0005   0.0358
  -9.500  -0.6524   0.02593   0.01976  -0.0900   1.0005   0.0368
  -9.250  -0.6255   0.02482   0.01856  -0.0910   1.0005   0.0379
  -9.000  -0.5983   0.02369   0.01729  -0.0920   1.0005   0.0391
  -8.750  -0.5707   0.02258   0.01602  -0.0929   1.0005   0.0401
  -8.500  -0.5429   0.02158   0.01486  -0.0937   1.0005   0.0410
  -8.250  -0.5153   0.02060   0.01383  -0.0944   1.0005   0.0421
  -8.000  -0.4878   0.01984   0.01304  -0.0951   1.0005   0.0435
  -7.750  -0.4607   0.01917   0.01231  -0.0955   1.0005   0.0449
  -7.500  -0.4289   0.01847   0.01151  -0.0968   0.9948   0.0465
  -7.250  -0.3920   0.01776   0.01068  -0.0990   0.9826   0.0481
  -7.000  -0.3556   0.01705   0.00990  -0.1012   0.9698   0.0502
  -6.750  -0.3197   0.01646   0.00926  -0.1031   0.9569   0.0527
  -6.500  -0.2852   0.01594   0.00865  -0.1046   0.9435   0.0555
  -6.250  -0.2533   0.01545   0.00808  -0.1055   0.9276   0.0588
  -6.000  -0.2231   0.01503   0.00762  -0.1059   0.9100   0.0637
  -5.750  -0.1940   0.01467   0.00720  -0.1061   0.8920   0.0705
  -5.500  -0.1655   0.01438   0.00683  -0.1060   0.8737   0.0793
  -5.250  -0.1374   0.01412   0.00651  -0.1059   0.8557   0.0883
  -5.000  -0.1092   0.01390   0.00622  -0.1057   0.8382   0.0964
  -4.750  -0.0809   0.01374   0.00593  -0.1055   0.8216   0.1043
  -4.500  -0.0524   0.01355   0.00569  -0.1055   0.8062   0.1124
  -4.250  -0.0237   0.01342   0.00544  -0.1054   0.7916   0.1198
  -4.000   0.0051   0.01328   0.00523  -0.1055   0.7781   0.1284
  -3.750   0.0341   0.01316   0.00504  -0.1055   0.7649   0.1378
  -3.500   0.0634   0.01305   0.00487  -0.1056   0.7524   0.1471
  -3.250   0.0927   0.01293   0.00471  -0.1058   0.7406   0.1567
  -3.000   0.1220   0.01284   0.00457  -0.1059   0.7293   0.1683
  -2.750   0.1515   0.01276   0.00445  -0.1061   0.7178   0.1813
  -2.500   0.1809   0.01268   0.00435  -0.1062   0.7066   0.1948
  -2.250   0.2103   0.01263   0.00426  -0.1064   0.6961   0.2095
  -2.000   0.2398   0.01257   0.00419  -0.1065   0.6847   0.2255
  -1.750   0.2693   0.01250   0.00412  -0.1067   0.6739   0.2417
  -1.500   0.2987   0.01245   0.00405  -0.1069   0.6636   0.2589
  -1.250   0.3282   0.01239   0.00401  -0.1071   0.6528   0.2765
  -1.000   0.3578   0.01234   0.00398  -0.1073   0.6426   0.2943
  -0.750   0.3871   0.01232   0.00398  -0.1074   0.6328   0.3155
  -0.500   0.4166   0.01230   0.00399  -0.1076   0.6222   0.3391
  -0.250   0.4459   0.01230   0.00402  -0.1078   0.6122   0.3630
   0.000   0.4752   0.01233   0.00406  -0.1078   0.6021   0.3887
   0.250   0.5045   0.01234   0.00412  -0.1080   0.5918   0.4125
   0.500   0.5336   0.01240   0.00416  -0.1080   0.5818   0.4344
   0.750   0.5627   0.01245   0.00422  -0.1081   0.5714   0.4548
   1.000   0.5918   0.01249   0.00428  -0.1082   0.5611   0.4741
   1.250   0.6206   0.01255   0.00434  -0.1082   0.5513   0.4928
   1.500   0.6495   0.01259   0.00442  -0.1083   0.5409   0.5118
   1.750   0.6783   0.01264   0.00450  -0.1083   0.5309   0.5317
   2.000   0.7070   0.01269   0.00459  -0.1083   0.5211   0.5533
   2.250   0.7357   0.01271   0.00470  -0.1084   0.5109   0.5786
   2.500   0.7639   0.01274   0.00482  -0.1083   0.5015   0.6131
   2.750   0.7913   0.01269   0.00497  -0.1080   0.4917   0.6746
   3.000   0.8120   0.01236   0.00503  -0.1059   0.4829   0.8459
   3.250   0.8383   0.01234   0.00502  -0.1053   0.4736   0.9995
   3.500   0.8672   0.01253   0.00519  -0.1054   0.4633   0.9995
   3.750   0.8958   0.01276   0.00535  -0.1055   0.4536   0.9995
   4.000   0.9244   0.01297   0.00552  -0.1056   0.4432   0.9995
   4.250   0.9528   0.01319   0.00573  -0.1056   0.4337   0.9995
   4.750   1.0093   0.01367   0.00616  -0.1056   0.4147   0.9995
   5.000   1.0371   0.01393   0.00640  -0.1056   0.4046   0.9995
   5.250   1.0646   0.01421   0.00664  -0.1055   0.3931   0.9995
   5.500   1.0922   0.01447   0.00690  -0.1054   0.3805   0.9995
   5.750   1.1195   0.01476   0.00719  -0.1053   0.3681   0.9995
   6.000   1.1465   0.01507   0.00748  -0.1051   0.3555   0.9995
   6.250   1.1731   0.01540   0.00778  -0.1049   0.3413   0.9995
   6.500   1.1994   0.01576   0.00810  -0.1047   0.3249   0.9995
   6.750   1.2251   0.01616   0.00847  -0.1044   0.3065   0.9995
   7.000   1.2505   0.01659   0.00885  -0.1041   0.2881   0.9995
   7.250   1.2758   0.01703   0.00927  -0.1038   0.2724   0.9995
   7.500   1.3007   0.01749   0.00972  -0.1034   0.2573   0.9995
   7.750   1.3249   0.01802   0.01021  -0.1029   0.2402   0.9995
   8.000   1.3482   0.01862   0.01076  -0.1024   0.2214   0.9995
   8.250   1.3709   0.01926   0.01135  -0.1017   0.2014   0.9995
   8.500   1.3923   0.02001   0.01204  -0.1010   0.1805   0.9995
   8.750   1.4128   0.02082   0.01278  -0.1001   0.1605   0.9995
   9.000   1.4322   0.02171   0.01359  -0.0991   0.1398   0.9995
   9.250   1.4496   0.02272   0.01452  -0.0979   0.1203   0.9995
   9.500   1.4662   0.02376   0.01551  -0.0965   0.1026   0.9995
   9.750   1.4809   0.02488   0.01658  -0.0949   0.0878   0.9995
  10.000   1.4942   0.02604   0.01772  -0.0932   0.0764   0.9995
  10.250   1.5052   0.02724   0.01892  -0.0911   0.0682   0.9995
  10.500   1.5145   0.02846   0.02018  -0.0889   0.0624   0.9995
  10.750   1.5189   0.02980   0.02157  -0.0860   0.0587   0.9995
  11.000   1.5248   0.03117   0.02304  -0.0836   0.0555   0.9995
  11.250   1.5288   0.03283   0.02477  -0.0814   0.0527   0.9995
  11.500   1.5302   0.03487   0.02686  -0.0795   0.0503   0.9995
  11.750   1.5346   0.03680   0.02891  -0.0781   0.0485   0.9995
  12.000   1.5386   0.03892   0.03114  -0.0770   0.0467   0.9995
  12.250   1.5409   0.04131   0.03365  -0.0761   0.0451   0.9995
  12.500   1.5412   0.04404   0.03647  -0.0755   0.0438   0.9995
  12.750   1.5392   0.04714   0.03965  -0.0750   0.0426   0.9995
  13.000   1.5355   0.05053   0.04313  -0.0747   0.0416   0.9995
  13.250   1.5365   0.05344   0.04619  -0.0745   0.0407   0.9995
  13.500   1.5358   0.05660   0.04948  -0.0744   0.0397   0.9995
  13.750   1.5339   0.05994   0.05295  -0.0744   0.0388   0.9995
  14.000   1.5310   0.06347   0.05660  -0.0745   0.0379   0.9995
  14.250   1.5273   0.06713   0.06037  -0.0747   0.0371   0.9995
  14.500   1.5227   0.07098   0.06434  -0.0751   0.0363   0.9995
  14.750   1.5170   0.07508   0.06852  -0.0757   0.0356   0.9995
  15.000   1.5100   0.07940   0.07292  -0.0764   0.0349   0.9995
  15.250   1.5056   0.08346   0.07708  -0.0770   0.0342   0.9995
  15.500   1.5029   0.08738   0.08114  -0.0778   0.0334   0.9995
  15.750   1.4995   0.09144   0.08533  -0.0786   0.0327   0.9995
  16.000   1.4957   0.09562   0.08962  -0.0796   0.0319   0.9995
  16.250   1.4918   0.09988   0.09399  -0.0808   0.0312   0.9995
  16.500   1.4875   0.10427   0.09847  -0.0821   0.0305   0.9995
  16.750   1.4829   0.10873   0.10300  -0.0835   0.0298   0.9995
<< Back to ONERA HOR12 AIRFOIL (hor12-il)

Polar data table (+)

Polar graphs


<< Back to ONERA HOR12 AIRFOIL (hor12-il)