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ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR12 AIRFOIL (hor12-il)
Reynolds number: 50,000
Max Cl/Cd: 30.72 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor12-il-50000.txt
Download as CSV file: xf-hor12-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3798   0.11852   0.11127  -0.0103   1.0005   0.2429
  -8.750  -0.3550   0.11260   0.10533  -0.0096   1.0005   0.2488
  -8.500  -0.3579   0.11106   0.10386  -0.0109   1.0005   0.2584
  -8.250  -0.3447   0.10676   0.09959  -0.0111   1.0005   0.2641
  -8.000  -0.3399   0.10430   0.09717  -0.0117   1.0005   0.2735
  -7.750  -0.3397   0.10145   0.09441  -0.0128   1.0005   0.2786
  -7.500  -0.3244   0.09790   0.09086  -0.0125   1.0005   0.2873
  -7.250  -0.3360   0.09638   0.08949  -0.0137   1.0005   0.2939
  -7.000  -0.3197   0.09294   0.08606  -0.0130   1.0005   0.3058
  -6.750  -0.3119   0.08974   0.08293  -0.0127   1.0005   0.3141
  -6.500  -0.3336   0.08971   0.08311  -0.0133   1.0005   0.3243
  -6.250  -0.3083   0.08495   0.07834  -0.0112   1.0005   0.3326
  -6.000  -0.3295   0.08439   0.07799  -0.0114   1.0005   0.3415
  -5.750  -0.3148   0.08086   0.07449  -0.0087   1.0005   0.3485
  -5.500  -0.3517   0.06488   0.05834  -0.0437   1.0005   0.2115
  -5.250  -0.3500   0.06446   0.05806  -0.0374   1.0005   0.2152
  -5.000  -0.3038   0.04728   0.03990  -0.0653   1.0005   0.1947
  -4.750  -0.2981   0.04770   0.04058  -0.0608   1.0005   0.2014
  -4.500  -0.2611   0.04171   0.03399  -0.0699   1.0005   0.2132
  -4.250  -0.2304   0.03858   0.03041  -0.0743   1.0005   0.2277
  -4.000  -0.2125   0.03806   0.02988  -0.0740   1.0005   0.2444
  -3.750  -0.1949   0.03770   0.02955  -0.0736   1.0005   0.2614
  -3.500  -0.1702   0.03664   0.02833  -0.0751   1.0005   0.2774
  -3.250  -0.1433   0.03562   0.02710  -0.0771   1.0005   0.2928
  -3.000  -0.1235   0.03531   0.02682  -0.0769   1.0005   0.3043
  -2.750  -0.0997   0.03482   0.02625  -0.0780   1.0005   0.3184
  -2.500  -0.0504   0.03386   0.02498  -0.0840   0.9940   0.3395
  -2.250   0.0028   0.03338   0.02446  -0.0895   0.9825   0.3619
  -2.000   0.0571   0.03284   0.02371  -0.0956   0.9703   0.3896
  -1.750   0.1039   0.03260   0.02350  -0.0996   0.9575   0.4150
  -1.500   0.1513   0.03234   0.02321  -0.1038   0.9445   0.4462
  -1.250   0.1968   0.03209   0.02294  -0.1076   0.9314   0.4799
  -1.000   0.2422   0.03181   0.02262  -0.1112   0.9184   0.5183
  -0.750   0.2875   0.03143   0.02233  -0.1143   0.9062   0.5585
  -0.500   0.3340   0.03100   0.02195  -0.1174   0.8942   0.6047
  -0.250   0.3692   0.03080   0.02184  -0.1186   0.8804   0.6504
   0.000   0.4000   0.03065   0.02184  -0.1187   0.8670   0.6997
   0.250   0.4271   0.03043   0.02183  -0.1177   0.8542   0.7568
   0.500   0.4523   0.02982   0.02150  -0.1156   0.8435   0.8369
   0.750   0.4934   0.02955   0.02122  -0.1188   0.8293   0.9995
   1.000   0.5382   0.03017   0.02151  -0.1235   0.8148   0.9995
   1.250   0.5727   0.03087   0.02198  -0.1253   0.8007   0.9995
   1.500   0.6042   0.03157   0.02251  -0.1263   0.7872   0.9995
   1.750   0.6364   0.03218   0.02299  -0.1270   0.7748   0.9995
   2.000   0.6731   0.03239   0.02307  -0.1276   0.7638   0.9995
   2.250   0.6965   0.03343   0.02405  -0.1274   0.7497   0.9995
   2.500   0.7205   0.03444   0.02502  -0.1271   0.7360   0.9995
   2.750   0.7453   0.03542   0.02595  -0.1268   0.7232   0.9995
   3.000   0.7782   0.03571   0.02620  -0.1266   0.7128   0.9995
   3.250   0.8022   0.03670   0.02717  -0.1261   0.6999   0.9995
   3.500   0.8219   0.03811   0.02860  -0.1256   0.6863   0.9995
   3.750   0.8431   0.03939   0.02989  -0.1251   0.6734   0.9995
   4.000   0.8738   0.03977   0.03028  -0.1244   0.6634   0.9995
   4.250   0.8973   0.04079   0.03132  -0.1238   0.6510   0.9995
   4.500   0.9129   0.04264   0.03324  -0.1232   0.6374   0.9995
   4.750   0.9308   0.04425   0.03492  -0.1224   0.6245   0.9995
   5.000   0.9616   0.04451   0.03520  -0.1215   0.6145   0.9995
   5.250   0.9844   0.04553   0.03628  -0.1206   0.6024   0.9995
   5.500   0.9951   0.04791   0.03876  -0.1198   0.5886   0.9995
   5.750   1.0072   0.05016   0.04111  -0.1190   0.5756   0.9995
   6.000   1.0332   0.05084   0.04186  -0.1179   0.5647   0.9995
   6.250   1.0631   0.05100   0.04210  -0.1166   0.5538   0.9995
   6.500   1.0668   0.05410   0.04531  -0.1157   0.5396   0.9995
   6.750   1.0686   0.05749   0.04880  -0.1149   0.5260   0.9995
   7.000   1.0783   0.05987   0.05130  -0.1137   0.5131   0.9995
   7.250   1.1485   0.05495   0.04646  -0.1112   0.5046   0.9995
   7.500   1.1478   0.05844   0.05008  -0.1100   0.4900   0.9995
   7.750   1.1316   0.06385   0.05560  -0.1092   0.4755   0.9995
   8.000   1.0856   0.07294   0.06469  -0.1097   0.4616   0.9995
   8.250   1.0747   0.07786   0.06966  -0.1094   0.4489   0.9995
   8.500   1.0940   0.07894   0.07088  -0.1076   0.4361   0.9995
   8.750   1.1815   0.07008   0.06229  -0.1018   0.4215   0.9995
   9.000   1.2471   0.06424   0.05666  -0.0982   0.4041   0.9995
   9.250   1.3752   0.04990   0.04215  -0.0949   0.3753   0.9995
   9.500   1.0821   0.09483   0.08705  -0.1055   0.3838   0.9995
   9.750   1.0872   0.09758   0.08988  -0.1045   0.3696   0.9995
  10.000   1.0956   0.09973   0.09213  -0.1031   0.3546   0.9995
  10.250   1.1047   0.10161   0.09411  -0.1015   0.3390   0.9995
  10.500   1.4682   0.04780   0.03962  -0.0813   0.2455   0.9995
  10.750   1.4850   0.04890   0.04036  -0.0791   0.2216   0.9995
  11.000   1.4882   0.05138   0.04289  -0.0764   0.2049   0.9995
  11.250   1.4960   0.05372   0.04518  -0.0742   0.1904   0.9995
  11.500   1.5103   0.05594   0.04729  -0.0726   0.1774   0.9995
  11.750   1.4952   0.05977   0.05159  -0.0693   0.1719   0.9995
  12.000   1.5183   0.06234   0.05401  -0.0686   0.1625   0.9995
  12.250   1.4941   0.06646   0.05856  -0.0650   0.1604   0.9995
  12.500   1.4683   0.07124   0.06369  -0.0627   0.1586   0.9995
  12.750   1.4371   0.07713   0.06990  -0.0617   0.1578   0.9995
  13.000   1.3929   0.08528   0.07837  -0.0629   0.1588   0.9995
  13.250   1.3383   0.09635   0.08966  -0.0669   0.1612   0.9995
  13.500   1.2824   0.10990   0.10334  -0.0732   0.1632   0.9995
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