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ONERA HOR20 AIRFOIL (hor20-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR20 AIRFOIL (hor20-il)
Reynolds number: 100,000
Max Cl/Cd: 44.88 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor20-il-100000-n5.txt
Download as CSV file: xf-hor20-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5676   0.08999   0.08353  -0.0424   1.0000   0.1146
 -12.000  -0.7950   0.05283   0.04566  -0.0674   1.0000   0.1227
 -11.750  -0.8144   0.04749   0.04021  -0.0714   1.0000   0.1246
 -11.500  -0.8054   0.04588   0.03867  -0.0721   1.0000   0.1265
 -11.250  -0.8179   0.04237   0.03509  -0.0743   1.0000   0.1284
 -11.000  -0.8271   0.03960   0.03219  -0.0750   1.0000   0.1305
 -10.750  -0.8350   0.03734   0.02976  -0.0743   1.0000   0.1328
 -10.500  -0.8148   0.03612   0.02852  -0.0755   0.9894   0.1353
 -10.250  -0.7818   0.03508   0.02750  -0.0783   0.9735   0.1385
 -10.000  -0.7523   0.03340   0.02561  -0.0815   0.9582   0.1427
  -9.750  -0.7220   0.03225   0.02437  -0.0837   0.9426   0.1462
  -9.500  -0.6932   0.03150   0.02361  -0.0849   0.9250   0.1494
  -9.250  -0.6681   0.03044   0.02240  -0.0857   0.9075   0.1532
  -9.000  -0.6443   0.02943   0.02122  -0.0861   0.8907   0.1569
  -8.750  -0.6190   0.02894   0.02074  -0.0860   0.8748   0.1601
  -8.500  -0.5949   0.02826   0.01994  -0.0858   0.8602   0.1642
  -8.250  -0.5721   0.02743   0.01891  -0.0857   0.8447   0.1687
  -8.000  -0.5471   0.02707   0.01858  -0.0852   0.8312   0.1723
  -7.750  -0.5225   0.02657   0.01798  -0.0849   0.8177   0.1769
  -7.500  -0.4977   0.02593   0.01715  -0.0848   0.8050   0.1822
  -7.250  -0.4720   0.02566   0.01688  -0.0844   0.7928   0.1862
  -7.000  -0.4460   0.02524   0.01636  -0.0842   0.7808   0.1916
  -6.750  -0.4200   0.02477   0.01574  -0.0841   0.7690   0.1970
  -6.500  -0.3931   0.02453   0.01550  -0.0838   0.7581   0.2016
  -6.250  -0.3660   0.02415   0.01499  -0.0838   0.7464   0.2075
  -6.000  -0.3390   0.02381   0.01452  -0.0837   0.7365   0.2128
  -5.750  -0.3113   0.02359   0.01432  -0.0836   0.7249   0.2180
  -5.500  -0.2838   0.02326   0.01379  -0.0835   0.7155   0.2245
  -5.250  -0.2559   0.02299   0.01350  -0.0835   0.7048   0.2299
  -5.000  -0.2281   0.02279   0.01326  -0.0834   0.6947   0.2356
  -4.750  -0.1998   0.02250   0.01278  -0.0834   0.6859   0.2425
  -4.500  -0.1716   0.02228   0.01259  -0.0835   0.6754   0.2480
  -4.250  -0.1434   0.02211   0.01235  -0.0833   0.6669   0.2541
  -4.000  -0.1146   0.02188   0.01196  -0.0835   0.6577   0.2614
  -3.750  -0.0862   0.02170   0.01182  -0.0834   0.6484   0.2670
  -3.500  -0.0578   0.02156   0.01161  -0.0833   0.6410   0.2735
  -3.250  -0.0285   0.02139   0.01132  -0.0836   0.6319   0.2810
  -3.000  -0.0001   0.02126   0.01125  -0.0835   0.6234   0.2867
  -2.750   0.0287   0.02117   0.01107  -0.0834   0.6167   0.2935
  -2.500   0.0581   0.02105   0.01087  -0.0836   0.6080   0.3012
  -2.250   0.0867   0.02098   0.01087  -0.0836   0.6003   0.3071
  -2.000   0.1157   0.02093   0.01073  -0.0835   0.5939   0.3143
  -1.750   0.1451   0.02086   0.01060  -0.0837   0.5859   0.3222
  -1.500   0.1738   0.02084   0.01064  -0.0837   0.5785   0.3283
  -1.250   0.2029   0.02082   0.01054  -0.0836   0.5724   0.3359
  -1.000   0.2322   0.02079   0.01046  -0.0838   0.5656   0.3439
  -0.750   0.2609   0.02082   0.01055  -0.0837   0.5582   0.3507
  -0.500   0.2901   0.02083   0.01049  -0.0837   0.5518   0.3593
  -0.250   0.3193   0.02085   0.01044  -0.0837   0.5461   0.3674
   0.000   0.3479   0.02093   0.01061  -0.0837   0.5388   0.3753
   0.250   0.3771   0.02097   0.01056  -0.0838   0.5321   0.3854
   0.500   0.4058   0.02102   0.01061  -0.0836   0.5265   0.3930
   0.750   0.4345   0.02114   0.01074  -0.0837   0.5201   0.4025
   1.000   0.4632   0.02122   0.01083  -0.0837   0.5132   0.4118
   1.250   0.4917   0.02132   0.01092  -0.0835   0.5074   0.4207
   1.500   0.5211   0.02144   0.01090  -0.0836   0.5022   0.4315
   1.750   0.5487   0.02158   0.01118  -0.0834   0.4954   0.4395
   2.000   0.5771   0.02172   0.01131  -0.0833   0.4891   0.4498
   2.250   0.6058   0.02182   0.01136  -0.0832   0.4839   0.4590
   2.500   0.6338   0.02199   0.01155  -0.0831   0.4783   0.4680
   2.750   0.6617   0.02219   0.01177  -0.0831   0.4717   0.4783
   3.000   0.6892   0.02231   0.01195  -0.0828   0.4660   0.4866
   3.250   0.7177   0.02245   0.01200  -0.0827   0.4611   0.4967
   3.500   0.7447   0.02265   0.01229  -0.0825   0.4550   0.5053
   3.750   0.7716   0.02283   0.01253  -0.0822   0.4487   0.5145
   4.000   0.7995   0.02299   0.01264  -0.0821   0.4434   0.5245
   4.250   0.8271   0.02310   0.01274  -0.0818   0.4388   0.5336
   4.500   0.8528   0.02338   0.01313  -0.0815   0.4322   0.5436
   4.750   0.8790   0.02356   0.01338  -0.0811   0.4263   0.5528
   5.000   0.9064   0.02371   0.01350  -0.0808   0.4214   0.5635
   5.250   0.9328   0.02394   0.01377  -0.0805   0.4161   0.5742
   5.500   0.9576   0.02423   0.01418  -0.0800   0.4096   0.5868
   5.750   0.9834   0.02440   0.01441  -0.0795   0.4039   0.6009
   6.000   1.0105   0.02454   0.01452  -0.0792   0.3993   0.6177
   6.250   1.0332   0.02489   0.01508  -0.0785   0.3928   0.6351
   6.500   1.0569   0.02513   0.01545  -0.0777   0.3868   0.6555
   6.750   1.0815   0.02526   0.01566  -0.0770   0.3818   0.6827
   7.000   1.1034   0.02544   0.01604  -0.0758   0.3765   0.7276
   7.250   1.1212   0.02538   0.01643  -0.0738   0.3704   1.0000
   7.500   1.1457   0.02579   0.01678  -0.0734   0.3650   1.0000
   7.750   1.1723   0.02612   0.01695  -0.0732   0.3605   1.0000
   8.000   1.1913   0.02682   0.01775  -0.0722   0.3543   1.0000
   8.250   1.2124   0.02736   0.01829  -0.0713   0.3486   1.0000
   8.500   1.2356   0.02775   0.01860  -0.0706   0.3437   1.0000
   8.750   1.2546   0.02840   0.01926  -0.0696   0.3382   1.0000
   9.000   1.2714   0.02910   0.02002  -0.0682   0.3322   1.0000
   9.250   1.2906   0.02964   0.02052  -0.0671   0.3272   1.0000
   9.500   1.3107   0.03017   0.02098  -0.0661   0.3226   1.0000
   9.750   1.3209   0.03114   0.02208  -0.0641   0.3169   1.0000
  10.000   1.3324   0.03191   0.02288  -0.0621   0.3119   1.0000
  10.250   1.3489   0.03250   0.02340  -0.0607   0.3075   1.0000
  10.500   1.3574   0.03358   0.02454  -0.0587   0.3028   1.0000
  10.750   1.3626   0.03488   0.02594  -0.0567   0.2975   1.0000
  11.000   1.3734   0.03590   0.02697  -0.0552   0.2927   1.0000
  11.250   1.3904   0.03660   0.02758  -0.0542   0.2886   1.0000
  11.500   1.3875   0.03869   0.02985  -0.0524   0.2833   1.0000
  11.750   1.3919   0.04036   0.03159  -0.0511   0.2783   1.0000
  12.000   1.4045   0.04143   0.03263  -0.0501   0.2741   1.0000
  12.250   1.4089   0.04327   0.03451  -0.0491   0.2696   1.0000
  12.500   1.4041   0.04598   0.03738  -0.0481   0.2646   1.0000
  12.750   1.4092   0.04786   0.03929  -0.0473   0.2602   1.0000
  13.000   1.4265   0.04861   0.03995  -0.0466   0.2565   1.0000
  13.250   1.4124   0.05251   0.04405  -0.0461   0.2516   1.0000
  13.500   1.4051   0.05587   0.04753  -0.0458   0.2468   1.0000
  13.750   1.4128   0.05763   0.04929  -0.0453   0.2429   1.0000
  14.000   1.4237   0.05908   0.05071  -0.0447   0.2393   1.0000
  14.250   1.3908   0.06564   0.05754  -0.0455   0.2339   1.0000
  14.500   1.3856   0.06912   0.06109  -0.0456   0.2295   1.0000
  14.750   1.4032   0.06977   0.06168  -0.0450   0.2263   1.0000
  15.000   1.3678   0.07737   0.06951  -0.0466   0.2211   1.0000
  15.250   1.3353   0.08502   0.07734  -0.0486   0.2154   1.0000
  15.500   1.3543   0.08543   0.07771  -0.0479   0.2125   1.0000
  15.750   1.3860   0.08405   0.07622  -0.0465   0.2104   1.0000
  16.000   1.2565   0.10694   0.09961  -0.0552   0.1992   1.0000
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