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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 200,000
Max Cl/Cd: 86.97 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3510-il-200000.txt
Download as CSV file: xf-hq3510-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3768   0.09288   0.08980  -0.0335   1.0000   0.0374
  -7.750  -0.3953   0.09178   0.08880  -0.0309   1.0000   0.0375
  -7.500  -0.4162   0.09083   0.08793  -0.0279   1.0000   0.0376
  -7.250  -0.3912   0.08342   0.08048  -0.0451   0.9926   0.0381
  -7.000  -0.3674   0.07685   0.07376  -0.0566   0.9859   0.0383
  -6.750  -0.3552   0.06843   0.06535  -0.0624   0.9824   0.0394
  -6.500  -0.3410   0.06514   0.06208  -0.0630   0.9768   0.0405
  -6.250  -0.3177   0.06117   0.05806  -0.0673   0.9724   0.0423
  -6.000  -0.2906   0.05631   0.05306  -0.0740   0.9678   0.0450
  -5.750  -0.2527   0.05287   0.04881  -0.0831   0.9591   0.0509
  -5.500  -0.2335   0.04560   0.04175  -0.0865   0.9568   0.0541
  -5.250  -0.2115   0.04271   0.03873  -0.0880   0.9504   0.0571
  -4.500  -0.1088   0.02824   0.02252  -0.0961   0.9379   0.0408
  -4.250  -0.0760   0.02466   0.01849  -0.0969   0.9337   0.0331
  -4.000  -0.0380   0.02153   0.01478  -0.0984   0.9313   0.0312
  -3.750   0.0015   0.01965   0.01260  -0.1004   0.9295   0.0325
  -3.500   0.0413   0.01889   0.01160  -0.1024   0.9274   0.0379
  -3.250   0.0643   0.01732   0.00998  -0.1014   0.9203   0.0410
  -3.000   0.1008   0.01608   0.00875  -0.1030   0.9174   0.0535
  -2.750   0.1390   0.01524   0.00797  -0.1051   0.9151   0.0836
  -2.500   0.1647   0.01489   0.00762  -0.1049   0.9082   0.1073
  -2.250   0.1980   0.01394   0.00696  -0.1062   0.9041   0.1682
  -2.000   0.2263   0.01237   0.00699  -0.1066   0.9011   0.6319
  -1.750   0.2488   0.01242   0.00709  -0.1051   0.8933   0.6862
  -1.500   0.2796   0.01232   0.00698  -0.1050   0.8889   0.7281
  -1.250   0.3068   0.01226   0.00692  -0.1042   0.8834   0.7613
  -1.000   0.3298   0.01220   0.00691  -0.1024   0.8764   0.7969
  -0.750   0.3566   0.01195   0.00669  -0.1009   0.8725   0.8334
  -0.500   0.3749   0.01181   0.00658  -0.0984   0.8630   0.8601
  -0.250   0.4049   0.01147   0.00619  -0.0981   0.8574   0.8764
   0.000   0.4290   0.01125   0.00597  -0.0969   0.8480   0.8942
   0.250   0.4571   0.01101   0.00570  -0.0965   0.8403   0.9150
   0.500   0.4933   0.01073   0.00541  -0.0977   0.8329   0.9434
   0.750   0.5371   0.01053   0.00516  -0.1010   0.8240   1.0000
   1.000   0.5697   0.01039   0.00491  -0.1019   0.8165   1.0000
   1.250   0.5973   0.01042   0.00489  -0.1021   0.8062   1.0000
   1.500   0.6264   0.01043   0.00483  -0.1024   0.7975   1.0000
   1.750   0.6566   0.01037   0.00470  -0.1028   0.7893   1.0000
   2.000   0.6836   0.01041   0.00472  -0.1026   0.7784   1.0000
   2.250   0.7113   0.01042   0.00470  -0.1025   0.7681   1.0000
   2.500   0.7395   0.01042   0.00465  -0.1024   0.7577   1.0000
   2.750   0.7674   0.01042   0.00460  -0.1022   0.7463   1.0000
   3.000   0.7944   0.01044   0.00463  -0.1018   0.7336   1.0000
   3.250   0.8210   0.01048   0.00465  -0.1014   0.7197   1.0000
   3.500   0.8472   0.01053   0.00468  -0.1009   0.7042   1.0000
   3.750   0.8727   0.01060   0.00475  -0.1003   0.6863   1.0000
   4.000   0.8984   0.01068   0.00482  -0.0996   0.6668   1.0000
   4.250   0.9233   0.01080   0.00490  -0.0989   0.6441   1.0000
   4.500   0.9475   0.01095   0.00500  -0.0980   0.6173   1.0000
   4.750   0.9706   0.01116   0.00512  -0.0969   0.5837   1.0000
   5.000   0.9922   0.01148   0.00532  -0.0955   0.5422   1.0000
   5.250   1.0118   0.01196   0.00557  -0.0939   0.4938   1.0000
   5.500   1.0300   0.01259   0.00594  -0.0922   0.4447   1.0000
   5.750   1.0484   0.01328   0.00641  -0.0906   0.4038   1.0000
   6.000   1.0677   0.01394   0.00690  -0.0893   0.3721   1.0000
   6.250   1.0880   0.01456   0.00744  -0.0881   0.3467   1.0000
   6.500   1.1084   0.01518   0.00796  -0.0870   0.3265   1.0000
   6.750   1.1295   0.01574   0.00851  -0.0860   0.3087   1.0000
   7.000   1.1505   0.01632   0.00908  -0.0850   0.2932   1.0000
   7.250   1.1713   0.01691   0.00968  -0.0840   0.2785   1.0000
   7.500   1.1910   0.01750   0.01026  -0.0828   0.2618   1.0000
   7.750   1.2088   0.01805   0.01082  -0.0814   0.2409   1.0000
   8.000   1.2261   0.01853   0.01129  -0.0799   0.2172   1.0000
   8.250   1.2448   0.01901   0.01182  -0.0786   0.1960   1.0000
   8.500   1.2618   0.01958   0.01237  -0.0771   0.1710   1.0000
   8.750   1.2763   0.02033   0.01302  -0.0753   0.1395   1.0000
   9.000   1.2853   0.02146   0.01393  -0.0727   0.1010   1.0000
   9.250   1.2786   0.02400   0.01584  -0.0682   0.0375   1.0000
   9.500   1.2794   0.02597   0.01776  -0.0645   0.0234   1.0000
   9.750   1.2810   0.02778   0.01967  -0.0613   0.0200   1.0000
  10.000   1.2830   0.02957   0.02166  -0.0582   0.0184   1.0000
  10.250   1.2869   0.03127   0.02352  -0.0556   0.0174   1.0000
  10.500   1.2898   0.03314   0.02553  -0.0532   0.0167   1.0000
  10.750   1.2924   0.03515   0.02767  -0.0509   0.0159   1.0000
  11.000   1.2950   0.03729   0.02994  -0.0489   0.0154   1.0000
  11.250   1.2977   0.03957   0.03234  -0.0470   0.0149   1.0000
  11.500   1.3013   0.04194   0.03484  -0.0454   0.0146   1.0000
  11.750   1.3059   0.04443   0.03746  -0.0438   0.0143   1.0000
  12.000   1.3114   0.04703   0.04021  -0.0424   0.0142   1.0000
  12.250   1.3169   0.04986   0.04321  -0.0412   0.0140   1.0000
  12.500   1.3213   0.05287   0.04643  -0.0400   0.0140   1.0000
  12.750   1.3231   0.05616   0.04997  -0.0389   0.0140   1.0000
  13.000   1.3213   0.05985   0.05393  -0.0380   0.0141   1.0000
  13.250   1.3159   0.06394   0.05831  -0.0374   0.0143   1.0000
  13.500   1.3069   0.06845   0.06310  -0.0373   0.0144   1.0000
  13.750   1.2954   0.07331   0.06823  -0.0377   0.0145   1.0000
  14.000   1.2816   0.07860   0.07378  -0.0387   0.0145   1.0000
  14.250   1.2667   0.08425   0.07967  -0.0404   0.0145   1.0000
  14.500   1.2501   0.09058   0.08624  -0.0429   0.0146   1.0000
  14.750   1.2258   0.09890   0.09488  -0.0469   0.0151   1.0000
  15.000   1.2049   0.10711   0.10332  -0.0516   0.0153   1.0000
  15.250   1.1801   0.11696   0.11342  -0.0578   0.0157   1.0000
  15.500   1.1563   0.12743   0.12409  -0.0647   0.0160   1.0000
  15.750   1.1330   0.13863   0.13546  -0.0723   0.0164   1.0000
  16.000   1.1091   0.15097   0.14793  -0.0807   0.0167   1.0000
  16.250   1.0812   0.16591   0.16296  -0.0904   0.0172   1.0000
  16.500   1.0578   0.18079   0.17783  -0.0988   0.0181   1.0000
  16.750   1.0495   0.18998   0.18698  -0.1036   0.0189   1.0000
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