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ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR12 AIRFOIL (hor12-il)
Reynolds number: 100,000
Max Cl/Cd: 54.73 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor12-il-100000.txt
Download as CSV file: xf-hor12-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3987   0.12081   0.11554  -0.0088   1.0005   0.1261
  -9.750  -0.4016   0.11832   0.11309  -0.0119   1.0005   0.1317
  -9.500  -0.4337   0.11722   0.11212  -0.0206   1.0005   0.1335
  -9.250  -0.3934   0.11074   0.10558  -0.0150   1.0005   0.1361
  -9.000  -0.3787   0.10750   0.10234  -0.0146   1.0005   0.1392
  -8.750  -0.3729   0.10449   0.09935  -0.0159   1.0005   0.1436
  -8.500  -0.4072   0.10291   0.09793  -0.0248   1.0005   0.1485
  -8.250  -0.3854   0.09764   0.09266  -0.0228   1.0005   0.1501
  -8.000  -0.3594   0.09463   0.08962  -0.0202   1.0005   0.1545
  -7.750  -0.3580   0.09196   0.08700  -0.0219   1.0005   0.1607
  -7.500  -0.3864   0.08832   0.08355  -0.0319   1.0005   0.1646
  -7.250  -0.4193   0.05741   0.05242  -0.0633   1.0005   0.1056
  -7.000  -0.4119   0.04909   0.04385  -0.0704   1.0005   0.1026
  -6.750  -0.3944   0.03921   0.03326  -0.0806   1.0005   0.1024
  -6.500  -0.3681   0.03324   0.02632  -0.0866   1.0005   0.1047
  -6.250  -0.3508   0.03087   0.02390  -0.0867   1.0005   0.1069
  -6.000  -0.3338   0.02955   0.02249  -0.0863   1.0005   0.1094
  -5.750  -0.3151   0.02820   0.02094  -0.0864   1.0005   0.1130
  -5.500  -0.2913   0.02654   0.01871  -0.0876   1.0005   0.1191
  -5.250  -0.2691   0.02575   0.01808  -0.0879   0.9995   0.1248
  -5.000  -0.2183   0.02409   0.01616  -0.0931   0.9935   0.1383
  -4.750  -0.1697   0.02309   0.01507  -0.0976   0.9853   0.1559
  -4.500  -0.1208   0.02241   0.01428  -0.1021   0.9773   0.1742
  -4.250  -0.0704   0.02201   0.01371  -0.1068   0.9696   0.1947
  -4.000  -0.0233   0.02149   0.01316  -0.1108   0.9605   0.2117
  -3.750   0.0278   0.02080   0.01246  -0.1153   0.9544   0.2287
  -3.500   0.0707   0.02029   0.01197  -0.1183   0.9436   0.2459
  -3.250   0.1121   0.01978   0.01149  -0.1208   0.9327   0.2638
  -3.000   0.1512   0.01931   0.01105  -0.1227   0.9212   0.2821
  -2.750   0.1873   0.01890   0.01066  -0.1239   0.9093   0.3009
  -2.500   0.2182   0.01863   0.01038  -0.1240   0.8950   0.3201
  -2.250   0.2476   0.01842   0.01017  -0.1238   0.8807   0.3417
  -2.000   0.2753   0.01828   0.01011  -0.1232   0.8667   0.3620
  -1.750   0.3027   0.01820   0.01005  -0.1225   0.8529   0.3850
  -1.500   0.3297   0.01813   0.00999  -0.1216   0.8397   0.4088
  -1.250   0.3561   0.01807   0.00994  -0.1206   0.8272   0.4333
  -1.000   0.3826   0.01802   0.00991  -0.1197   0.8138   0.4591
  -0.750   0.4094   0.01800   0.00989  -0.1190   0.8000   0.4879
  -0.500   0.4360   0.01792   0.00987  -0.1183   0.7870   0.5166
  -0.250   0.4625   0.01781   0.00981  -0.1174   0.7749   0.5474
   0.000   0.4887   0.01767   0.00971  -0.1164   0.7636   0.5800
   0.250   0.5152   0.01760   0.00974  -0.1158   0.7503   0.6153
   0.500   0.5411   0.01752   0.00978  -0.1149   0.7378   0.6524
   0.750   0.5663   0.01743   0.00981  -0.1137   0.7264   0.6966
   1.000   0.5892   0.01723   0.00979  -0.1119   0.7155   0.7553
   1.250   0.6039   0.01670   0.00965  -0.1081   0.7033   0.9292
   1.500   0.6380   0.01694   0.00967  -0.1096   0.6912   0.9995
   1.750   0.6686   0.01717   0.00966  -0.1098   0.6809   0.9995
   2.000   0.6981   0.01746   0.00986  -0.1101   0.6683   0.9995
   2.250   0.7271   0.01778   0.01009  -0.1102   0.6563   0.9995
   2.500   0.7559   0.01805   0.01023  -0.1101   0.6457   0.9995
   2.750   0.7845   0.01831   0.01040  -0.1100   0.6347   0.9995
   3.000   0.8128   0.01865   0.01071  -0.1100   0.6226   0.9995
   3.250   0.8411   0.01896   0.01095  -0.1098   0.6120   0.9995
   3.500   0.8695   0.01921   0.01111  -0.1095   0.6018   0.9995
   3.750   0.8973   0.01959   0.01150  -0.1095   0.5897   0.9995
   4.000   0.9251   0.01992   0.01181  -0.1093   0.5788   0.9995
   4.250   0.9535   0.02016   0.01195  -0.1089   0.5690   0.9995
   4.500   0.9807   0.02055   0.01239  -0.1087   0.5567   0.9995
   4.750   1.0081   0.02092   0.01277  -0.1085   0.5455   0.9995
   5.000   1.0365   0.02116   0.01291  -0.1081   0.5363   0.9995
   5.250   1.0631   0.02159   0.01343  -0.1079   0.5239   0.9995
   5.500   1.0900   0.02201   0.01389  -0.1076   0.5125   0.9995
   5.750   1.1177   0.02231   0.01413  -0.1072   0.5022   0.9995
   6.000   1.1445   0.02265   0.01451  -0.1068   0.4904   0.9995
   6.250   1.1705   0.02310   0.01503  -0.1064   0.4780   0.9995
   6.500   1.1969   0.02349   0.01545  -0.1059   0.4662   0.9995
   6.750   1.2240   0.02378   0.01569  -0.1054   0.4549   0.9995
   7.000   1.2499   0.02407   0.01601  -0.1049   0.4417   0.9995
   7.250   1.2748   0.02435   0.01635  -0.1041   0.4271   0.9995
   7.500   1.2995   0.02448   0.01647  -0.1033   0.4110   0.9995
   7.750   1.3237   0.02454   0.01650  -0.1024   0.3938   0.9995
   8.000   1.3469   0.02472   0.01666  -0.1014   0.3764   0.9995
   8.250   1.3692   0.02503   0.01705  -0.1004   0.3595   0.9995
   8.500   1.3912   0.02542   0.01754  -0.0994   0.3431   0.9995
   8.750   1.4121   0.02586   0.01806  -0.0983   0.3257   0.9995
   9.000   1.4320   0.02637   0.01865  -0.0970   0.3074   0.9995
   9.250   1.4501   0.02693   0.01926  -0.0956   0.2875   0.9995
   9.500   1.4658   0.02763   0.01998  -0.0939   0.2651   0.9995
   9.750   1.4777   0.02856   0.02089  -0.0917   0.2389   0.9995
  10.000   1.4845   0.02990   0.02215  -0.0891   0.2092   0.9995
  10.250   1.4858   0.03173   0.02382  -0.0860   0.1805   0.9995
  10.500   1.4835   0.03386   0.02580  -0.0825   0.1581   0.9995
  10.750   1.4795   0.03598   0.02782  -0.0788   0.1429   0.9995
  11.000   1.4781   0.03820   0.02993  -0.0758   0.1318   0.9995
  11.250   1.4799   0.04036   0.03204  -0.0734   0.1227   0.9995
  11.500   1.4848   0.04253   0.03426  -0.0714   0.1150   0.9995
  11.750   1.4924   0.04456   0.03618  -0.0696   0.1089   0.9995
  12.000   1.5019   0.04668   0.03842  -0.0680   0.1038   0.9995
  12.250   1.5099   0.04874   0.04055  -0.0665   0.0991   0.9995
  12.500   1.5290   0.05066   0.04228  -0.0654   0.0940   0.9995
  12.750   1.5311   0.05311   0.04505  -0.0638   0.0911   0.9995
  13.000   1.5358   0.05552   0.04763  -0.0625   0.0878   0.9995
  13.250   1.5471   0.05759   0.04968  -0.0614   0.0844   0.9995
  13.500   1.5631   0.06024   0.05235  -0.0603   0.0811   0.9995
  13.750   1.5571   0.06343   0.05587  -0.0590   0.0794   0.9995
  14.000   1.5521   0.06680   0.05950  -0.0581   0.0775   0.9995
  14.250   1.5473   0.07028   0.06321  -0.0574   0.0756   0.9995
  14.500   1.5444   0.07375   0.06686  -0.0568   0.0739   0.9995
  14.750   1.5537   0.07649   0.06960  -0.0560   0.0716   0.9995
  15.000   1.5499   0.08111   0.07436  -0.0556   0.0700   0.9995
  15.250   1.5277   0.08640   0.07998  -0.0563   0.0696   0.9995
  15.500   1.5037   0.09233   0.08622  -0.0577   0.0693   0.9995
  15.750   1.4776   0.09896   0.09315  -0.0600   0.0691   0.9995
  16.000   1.4494   0.10635   0.10083  -0.0631   0.0691   0.9995
  16.250   1.4189   0.11475   0.10950  -0.0675   0.0693   0.9995
  16.500   1.3864   0.12434   0.11932  -0.0731   0.0696   0.9995
  16.750   1.3521   0.13531   0.13050  -0.0800   0.0701   0.9995
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