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

ONERA HOR20 AIRFOIL (hor20-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR20 AIRFOIL (hor20-il)
Reynolds number: 500,000
Max Cl/Cd: 91.14 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor20-il-500000.txt
Download as CSV file: xf-hor20-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR20 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -1.0704   0.10329   0.09915  -0.0292   1.0000   0.0624
 -18.250  -1.0803   0.09820   0.09396  -0.0321   1.0000   0.0636
 -18.000  -1.0917   0.09296   0.08860  -0.0350   1.0000   0.0647
 -17.750  -1.0869   0.09040   0.08610  -0.0361   1.0000   0.0658
 -17.500  -1.0914   0.08632   0.08200  -0.0383   1.0000   0.0669
 -17.250  -1.0966   0.08213   0.07775  -0.0406   1.0000   0.0681
 -17.000  -1.1047   0.07752   0.07304  -0.0431   1.0000   0.0693
 -16.750  -1.1139   0.07279   0.06819  -0.0458   1.0000   0.0704
 -16.500  -1.1128   0.06984   0.06529  -0.0471   1.0000   0.0716
 -16.250  -1.1173   0.06597   0.06139  -0.0492   1.0000   0.0727
 -16.000  -1.1216   0.06216   0.05753  -0.0513   1.0000   0.0739
 -15.750  -1.1284   0.05820   0.05348  -0.0534   1.0000   0.0751
 -15.500  -1.1360   0.05421   0.04937  -0.0556   1.0000   0.0762
 -15.250  -1.1404   0.05086   0.04600  -0.0573   1.0000   0.0773
 -15.000  -1.1457   0.04735   0.04248  -0.0591   1.0000   0.0784
 -14.750  -1.1503   0.04383   0.03891  -0.0611   1.0000   0.0795
 -14.500  -1.1533   0.04045   0.03547  -0.0631   1.0000   0.0806
 -14.250  -1.1542   0.03720   0.03214  -0.0651   1.0000   0.0818
 -14.000  -1.1525   0.03410   0.02893  -0.0673   1.0000   0.0829
 -13.750  -1.1549   0.03056   0.02536  -0.0700   1.0000   0.0840
 -13.500  -1.1527   0.02684   0.02156  -0.0743   1.0000   0.0852
 -13.250  -1.1384   0.02528   0.01994  -0.0754   1.0000   0.0867
 -13.000  -1.1207   0.02417   0.01876  -0.0758   1.0000   0.0882
 -12.750  -1.1008   0.02329   0.01780  -0.0759   1.0000   0.0897
 -12.500  -1.0830   0.02226   0.01676  -0.0759   1.0000   0.0913
 -12.250  -1.0638   0.02142   0.01593  -0.0757   1.0000   0.0929
 -12.000  -1.0427   0.02078   0.01527  -0.0755   0.9990   0.0947
 -11.750  -1.0059   0.02014   0.01456  -0.0780   0.9867   0.0969
 -11.500  -0.9711   0.01932   0.01373  -0.0803   0.9718   0.0993
 -11.250  -0.9392   0.01869   0.01309  -0.0817   0.9555   0.1016
 -11.000  -0.9133   0.01827   0.01259  -0.0816   0.9341   0.1039
 -10.750  -0.8894   0.01791   0.01211  -0.0809   0.9119   0.1059
 -10.500  -0.8670   0.01733   0.01151  -0.0803   0.8913   0.1083
 -10.250  -0.8422   0.01694   0.01105  -0.0798   0.8727   0.1108
 -10.000  -0.8163   0.01664   0.01062  -0.0795   0.8552   0.1133
  -9.500  -0.7638   0.01585   0.00972  -0.0792   0.8235   0.1192
  -9.250  -0.7363   0.01561   0.00937  -0.0791   0.8103   0.1224
  -9.000  -0.7088   0.01525   0.00896  -0.0791   0.7973   0.1257
  -8.750  -0.6811   0.01494   0.00861  -0.0791   0.7854   0.1291
  -8.500  -0.6524   0.01471   0.00831  -0.0792   0.7734   0.1326
  -8.250  -0.6243   0.01441   0.00795  -0.0792   0.7626   0.1363
  -8.000  -0.5953   0.01413   0.00766  -0.0794   0.7522   0.1405
  -7.750  -0.5662   0.01399   0.00741  -0.0794   0.7412   0.1444
  -7.500  -0.5374   0.01364   0.00709  -0.0797   0.7309   0.1492
  -7.250  -0.5081   0.01347   0.00685  -0.0798   0.7200   0.1540
  -7.000  -0.4788   0.01324   0.00658  -0.0799   0.7102   0.1587
  -6.750  -0.4493   0.01302   0.00635  -0.0802   0.6997   0.1638
  -6.250  -0.3900   0.01265   0.00592  -0.0805   0.6789   0.1741
  -6.000  -0.3601   0.01255   0.00573  -0.0807   0.6685   0.1795
  -5.750  -0.3302   0.01238   0.00555  -0.0809   0.6587   0.1849
  -5.500  -0.3002   0.01224   0.00540  -0.0811   0.6480   0.1906
  -5.250  -0.2700   0.01220   0.00525  -0.0813   0.6381   0.1957
  -5.000  -0.2399   0.01202   0.00511  -0.0816   0.6284   0.2018
  -4.750  -0.2098   0.01199   0.00500  -0.0817   0.6187   0.2078
  -4.500  -0.1794   0.01189   0.00489  -0.0820   0.6098   0.2137
  -4.250  -0.1492   0.01183   0.00482  -0.0822   0.6003   0.2203
  -4.000  -0.1188   0.01186   0.00475  -0.0824   0.5917   0.2260
  -3.750  -0.0884   0.01172   0.00465  -0.0827   0.5838   0.2321
  -3.500  -0.0581   0.01168   0.00458  -0.0829   0.5758   0.2378
  -3.250  -0.0276   0.01172   0.00452  -0.0831   0.5682   0.2429
  -3.000   0.0028   0.01158   0.00441  -0.0834   0.5608   0.2487
  -2.750   0.0331   0.01153   0.00434  -0.0836   0.5533   0.2543
  -2.500   0.0634   0.01156   0.00430  -0.0838   0.5464   0.2596
  -2.250   0.0940   0.01149   0.00423  -0.0841   0.5402   0.2647
  -2.000   0.1243   0.01140   0.00416  -0.0843   0.5332   0.2710
  -1.750   0.1544   0.01144   0.00412  -0.0845   0.5260   0.2768
  -1.500   0.1851   0.01144   0.00409  -0.0847   0.5203   0.2816
  -1.250   0.2154   0.01133   0.00404  -0.0850   0.5140   0.2891
  -1.000   0.2455   0.01134   0.00402  -0.0852   0.5077   0.2956
  -0.750   0.2758   0.01141   0.00402  -0.0853   0.5017   0.3012
  -0.500   0.3063   0.01132   0.00402  -0.0856   0.4966   0.3092
  -0.250   0.3366   0.01132   0.00402  -0.0858   0.4908   0.3169
   0.000   0.3667   0.01137   0.00403  -0.0860   0.4850   0.3244
   0.250   0.3968   0.01140   0.00409  -0.0862   0.4798   0.3334
   0.500   0.4274   0.01140   0.00411  -0.0864   0.4749   0.3421
   0.750   0.4576   0.01138   0.00414  -0.0866   0.4694   0.3522
   1.000   0.4876   0.01145   0.00417  -0.0868   0.4638   0.3624
   1.250   0.5175   0.01151   0.00426  -0.0869   0.4586   0.3734
   1.500   0.5480   0.01153   0.00431  -0.0871   0.4538   0.3844
   1.750   0.5780   0.01155   0.00438  -0.0873   0.4484   0.3949
   2.000   0.6077   0.01166   0.00445  -0.0874   0.4428   0.4054
   2.250   0.6374   0.01176   0.00455  -0.0875   0.4377   0.4150
   2.500   0.6675   0.01180   0.00465  -0.0876   0.4330   0.4245
   2.750   0.6974   0.01191   0.00473  -0.0877   0.4277   0.4321
   3.000   0.7266   0.01200   0.00482  -0.0878   0.4222   0.4408
   3.250   0.7561   0.01213   0.00495  -0.0878   0.4168   0.4489
   3.500   0.7859   0.01221   0.00504  -0.0879   0.4116   0.4554
   3.750   0.8151   0.01227   0.00513  -0.0880   0.4060   0.4630
   4.000   0.8438   0.01245   0.00527  -0.0879   0.4001   0.4704
   4.250   0.8733   0.01256   0.00539  -0.0880   0.3952   0.4771
   4.500   0.9025   0.01261   0.00549  -0.0880   0.3896   0.4840
   4.750   0.9310   0.01274   0.00562  -0.0880   0.3840   0.4907
   5.000   0.9593   0.01295   0.00578  -0.0879   0.3784   0.4974
   5.250   0.9884   0.01302   0.00591  -0.0879   0.3736   0.5041
   5.500   1.0169   0.01312   0.00605  -0.0879   0.3682   0.5112
   5.750   1.0445   0.01333   0.00622  -0.0877   0.3624   0.5181
   6.000   1.0728   0.01348   0.00638  -0.0876   0.3569   0.5242
   6.250   1.1009   0.01356   0.00653  -0.0875   0.3508   0.5318
   6.500   1.1279   0.01376   0.00671  -0.0873   0.3450   0.5394
   6.750   1.1552   0.01397   0.00691  -0.0870   0.3395   0.5472
   7.000   1.1828   0.01407   0.00710  -0.0869   0.3339   0.5569
   7.250   1.2094   0.01428   0.00731  -0.0866   0.3283   0.5672
   7.500   1.2351   0.01452   0.00758  -0.0862   0.3229   0.5789
   8.000   1.2879   0.01483   0.00804  -0.0855   0.3113   0.6154
   8.250   1.3120   0.01504   0.00837  -0.0849   0.3051   0.6565
   8.500   1.3300   0.01462   0.00864  -0.0826   0.3001   0.8889
   8.750   1.3562   0.01488   0.00887  -0.0824   0.2940   1.0000
   9.000   1.3792   0.01529   0.00922  -0.0816   0.2884   1.0000
   9.250   1.4044   0.01555   0.00951  -0.0811   0.2836   1.0000
   9.500   1.4275   0.01591   0.00985  -0.0803   0.2782   1.0000
   9.750   1.4475   0.01641   0.01028  -0.0791   0.2727   1.0000
  10.000   1.4706   0.01672   0.01063  -0.0784   0.2682   1.0000
  10.250   1.4911   0.01713   0.01104  -0.0772   0.2631   1.0000
  10.500   1.5077   0.01767   0.01154  -0.0755   0.2582   1.0000
  10.750   1.5233   0.01817   0.01205  -0.0736   0.2539   1.0000
  11.000   1.5405   0.01865   0.01257  -0.0721   0.2495   1.0000
  11.250   1.5550   0.01931   0.01322  -0.0703   0.2450   1.0000
  11.500   1.5657   0.02022   0.01409  -0.0683   0.2403   1.0000
  11.750   1.5838   0.02079   0.01473  -0.0672   0.2362   1.0000
  12.000   1.5981   0.02160   0.01557  -0.0658   0.2314   1.0000
  12.250   1.6083   0.02272   0.01666  -0.0643   0.2267   1.0000
  12.500   1.6222   0.02368   0.01766  -0.0631   0.2225   1.0000
  12.750   1.6356   0.02471   0.01873  -0.0621   0.2177   1.0000
  13.000   1.6445   0.02612   0.02013  -0.0609   0.2130   1.0000
  13.250   1.6543   0.02752   0.02156  -0.0599   0.2085   1.0000
  13.500   1.6660   0.02884   0.02293  -0.0591   0.2040   1.0000
  13.750   1.6727   0.03058   0.02467  -0.0582   0.1996   1.0000
  14.000   1.6779   0.03251   0.02661  -0.0573   0.1955   1.0000
  14.250   1.6876   0.03409   0.02826  -0.0567   0.1913   1.0000
  14.500   1.6918   0.03618   0.03038  -0.0559   0.1871   1.0000
  14.750   1.6908   0.03878   0.03297  -0.0551   0.1832   1.0000
  15.000   1.6982   0.04064   0.03491  -0.0546   0.1797   1.0000
  15.250   1.7011   0.04295   0.03727  -0.0541   0.1761   1.0000
  15.500   1.6990   0.04578   0.04012  -0.0535   0.1727   1.0000
  15.750   1.6972   0.04866   0.04303  -0.0531   0.1694   1.0000
  16.000   1.7008   0.05106   0.04551  -0.0529   0.1660   1.0000
  16.250   1.6990   0.05408   0.04857  -0.0527   0.1624   1.0000
  16.500   1.6928   0.05762   0.05212  -0.0526   0.1592   1.0000
  16.750   1.6932   0.06048   0.05505  -0.0525   0.1562   1.0000
  17.000   1.6929   0.06347   0.05812  -0.0525   0.1531   1.0000
  17.250   1.6886   0.06695   0.06163  -0.0527   0.1501   1.0000
  17.500   1.6819   0.07071   0.06540  -0.0529   0.1473   1.0000
  17.750   1.6812   0.07385   0.06863  -0.0531   0.1447   1.0000
  18.000   1.6803   0.07700   0.07184  -0.0533   0.1418   1.0000
  18.250   1.6750   0.08073   0.07562  -0.0538   0.1390   1.0000
  18.500   1.6675   0.08473   0.07963  -0.0543   0.1364   1.0000
  18.750   1.6657   0.08808   0.08306  -0.0547   0.1339   1.0000
  19.000   1.6633   0.09153   0.08658  -0.0553   0.1312   1.0000
  19.250   1.6577   0.09540   0.09049  -0.0560   0.1286   1.0000
<< Back to ONERA HOR20 AIRFOIL (hor20-il)

Polar data table (+)

Polar graphs


<< Back to ONERA HOR20 AIRFOIL (hor20-il)