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CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: CLARK YM-15 AIRFOIL (clarym15-il)
Reynolds number: 100,000
Max Cl/Cd: 48.7 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarym15-il-100000-n5.txt
Download as CSV file: xf-clarym15-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YM-15 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5093   0.07339   0.06781  -0.0684   1.0000   0.0528
 -10.750  -0.5701   0.06415   0.05854  -0.0730   1.0000   0.0523
 -10.500  -0.6172   0.06074   0.05511  -0.0703   1.0000   0.0521
 -10.250  -0.6593   0.05843   0.05275  -0.0652   0.9995   0.0519
 -10.000  -0.6731   0.05107   0.04481  -0.0698   0.9883   0.0521
  -9.750  -0.6721   0.04587   0.03899  -0.0720   0.9800   0.0525
  -9.500  -0.6582   0.04270   0.03546  -0.0731   0.9729   0.0531
  -9.250  -0.6327   0.04106   0.03373  -0.0746   0.9682   0.0540
  -9.000  -0.6118   0.03946   0.03197  -0.0750   0.9612   0.0550
  -8.750  -0.5855   0.03753   0.02977  -0.0766   0.9567   0.0563
  -8.500  -0.5662   0.03567   0.02762  -0.0765   0.9494   0.0574
  -8.250  -0.5406   0.03368   0.02528  -0.0773   0.9441   0.0585
  -8.000  -0.5096   0.03179   0.02300  -0.0789   0.9406   0.0598
  -7.750  -0.4892   0.03060   0.02169  -0.0782   0.9325   0.0608
  -7.500  -0.4580   0.02957   0.02062  -0.0794   0.9279   0.0622
  -7.250  -0.4241   0.02857   0.01951  -0.0811   0.9247   0.0644
  -7.000  -0.4029   0.02773   0.01850  -0.0802   0.9162   0.0666
  -6.750  -0.3722   0.02669   0.01729  -0.0809   0.9114   0.0690
  -6.500  -0.3387   0.02579   0.01641  -0.0823   0.9079   0.0714
  -6.250  -0.3179   0.02515   0.01572  -0.0812   0.8991   0.0740
  -6.000  -0.2870   0.02434   0.01475  -0.0818   0.8942   0.0779
  -5.750  -0.2554   0.02358   0.01405  -0.0828   0.8901   0.0824
  -5.500  -0.2340   0.02310   0.01348  -0.0816   0.8813   0.0880
  -5.250  -0.2039   0.02239   0.01280  -0.0822   0.8765   0.0945
  -5.000  -0.1771   0.02185   0.01220  -0.0820   0.8703   0.1024
  -4.750  -0.1521   0.02135   0.01172  -0.0816   0.8631   0.1113
  -4.500  -0.1212   0.02077   0.01117  -0.0822   0.8585   0.1228
  -4.250  -0.0976   0.02041   0.01084  -0.0814   0.8508   0.1351
  -4.000  -0.0700   0.01999   0.01049  -0.0814   0.8446   0.1520
  -3.750  -0.0382   0.01953   0.01009  -0.0821   0.8403   0.1759
  -3.500  -0.0167   0.01928   0.00997  -0.0810   0.8314   0.1995
  -3.250   0.0125   0.01892   0.00967  -0.0811   0.8258   0.2289
  -3.000   0.0402   0.01861   0.00944  -0.0810   0.8197   0.2589
  -2.750   0.0650   0.01838   0.00926  -0.0804   0.8114   0.2867
  -2.500   0.0966   0.01798   0.00890  -0.0807   0.8059   0.3180
  -2.250   0.1190   0.01777   0.00879  -0.0796   0.7955   0.3468
  -2.000   0.1498   0.01733   0.00843  -0.0797   0.7885   0.3841
  -1.750   0.1722   0.01708   0.00833  -0.0785   0.7772   0.4256
  -1.500   0.2007   0.01664   0.00806  -0.0782   0.7690   0.4844
  -1.250   0.2232   0.01626   0.00800  -0.0767   0.7577   0.5648
  -1.000   0.2467   0.01585   0.00800  -0.0750   0.7479   0.6759
  -0.750   0.2746   0.01563   0.00805  -0.0737   0.7387   0.7811
  -0.500   0.3083   0.01563   0.00811  -0.0739   0.7297   0.8493
  -0.250   0.3482   0.01563   0.00805  -0.0755   0.7210   0.8934
   0.000   0.3869   0.01570   0.00804  -0.0773   0.7113   0.9264
   0.250   0.4282   0.01569   0.00790  -0.0795   0.7023   0.9522
   0.500   0.4722   0.01575   0.00786  -0.0827   0.6907   0.9720
   0.750   0.5196   0.01572   0.00771  -0.0866   0.6798   0.9879
   1.000   0.5640   0.01570   0.00757  -0.0900   0.6683   1.0000
   1.250   0.5833   0.01578   0.00758  -0.0884   0.6565   1.0000
   1.500   0.6044   0.01583   0.00752  -0.0871   0.6453   1.0000
   1.750   0.6258   0.01589   0.00748  -0.0858   0.6334   1.0000
   2.000   0.6453   0.01600   0.00752  -0.0842   0.6200   1.0000
   2.250   0.6657   0.01611   0.00754  -0.0828   0.6068   1.0000
   2.500   0.6866   0.01623   0.00757  -0.0813   0.5935   1.0000
   2.750   0.7079   0.01636   0.00758  -0.0800   0.5804   1.0000
   3.000   0.7279   0.01652   0.00768  -0.0784   0.5663   1.0000
   3.250   0.7479   0.01671   0.00779  -0.0769   0.5516   1.0000
   3.500   0.7681   0.01691   0.00790  -0.0754   0.5366   1.0000
   3.750   0.7883   0.01714   0.00804  -0.0739   0.5213   1.0000
   4.000   0.8086   0.01739   0.00819  -0.0724   0.5062   1.0000
   4.250   0.8291   0.01766   0.00837  -0.0710   0.4918   1.0000
   4.750   0.8702   0.01826   0.00882  -0.0683   0.4645   1.0000
   5.000   0.8907   0.01860   0.00909  -0.0670   0.4517   1.0000
   5.250   0.9117   0.01895   0.00937  -0.0658   0.4402   1.0000
   5.500   0.9329   0.01931   0.00967  -0.0647   0.4298   1.0000
   5.750   0.9541   0.01969   0.01002  -0.0636   0.4200   1.0000
   6.000   0.9758   0.02009   0.01033  -0.0626   0.4116   1.0000
   6.250   0.9969   0.02049   0.01075  -0.0615   0.4026   1.0000
   6.500   1.0188   0.02092   0.01109  -0.0606   0.3951   1.0000
   6.750   1.0395   0.02135   0.01155  -0.0595   0.3867   1.0000
   7.000   1.0608   0.02180   0.01194  -0.0585   0.3792   1.0000
   7.250   1.0810   0.02226   0.01243  -0.0574   0.3712   1.0000
   7.500   1.1013   0.02273   0.01286  -0.0563   0.3634   1.0000
   7.750   1.1202   0.02322   0.01338  -0.0550   0.3550   1.0000
   8.000   1.1386   0.02372   0.01384  -0.0536   0.3465   1.0000
   8.250   1.1562   0.02423   0.01439  -0.0521   0.3381   1.0000
   8.500   1.1734   0.02475   0.01492  -0.0506   0.3303   1.0000
   8.750   1.1907   0.02529   0.01548  -0.0491   0.3233   1.0000
   9.000   1.2060   0.02584   0.01611  -0.0474   0.3162   1.0000
   9.250   1.2242   0.02641   0.01663  -0.0461   0.3098   1.0000
   9.500   1.2373   0.02703   0.01740  -0.0441   0.3027   1.0000
   9.750   1.2517   0.02765   0.01808  -0.0424   0.2957   1.0000
  10.000   1.2657   0.02832   0.01881  -0.0407   0.2889   1.0000
  10.250   1.2772   0.02905   0.01965  -0.0387   0.2813   1.0000
  10.500   1.2898   0.02978   0.02039  -0.0370   0.2744   1.0000
  10.750   1.2991   0.03064   0.02144  -0.0350   0.2661   1.0000
  11.000   1.3092   0.03149   0.02229  -0.0331   0.2589   1.0000
  11.250   1.3169   0.03252   0.02351  -0.0312   0.2497   1.0000
  11.500   1.3242   0.03359   0.02462  -0.0293   0.2415   1.0000
  11.750   1.3304   0.03481   0.02598  -0.0276   0.2319   1.0000
  12.000   1.3360   0.03614   0.02739  -0.0259   0.2226   1.0000
  12.250   1.3398   0.03762   0.02891  -0.0242   0.2137   1.0000
  12.500   1.3435   0.03926   0.03065  -0.0228   0.2037   1.0000
  12.750   1.3456   0.04107   0.03250  -0.0213   0.1949   1.0000
  13.000   1.3464   0.04307   0.03452  -0.0200   0.1864   1.0000
  13.250   1.3472   0.04519   0.03670  -0.0189   0.1786   1.0000
  13.500   1.3464   0.04750   0.03902  -0.0178   0.1719   1.0000
  13.750   1.3466   0.04985   0.04144  -0.0169   0.1657   1.0000
  14.000   1.3458   0.05235   0.04400  -0.0161   0.1602   1.0000
  14.250   1.3447   0.05492   0.04656  -0.0154   0.1556   1.0000
  14.500   1.3449   0.05756   0.04934  -0.0149   0.1507   1.0000
  14.750   1.3438   0.06032   0.05218  -0.0146   0.1464   1.0000
  15.000   1.3443   0.06288   0.05471  -0.0141   0.1428   1.0000
  15.250   1.3438   0.06581   0.05779  -0.0140   0.1390   1.0000
  15.500   1.3426   0.06884   0.06094  -0.0140   0.1353   1.0000
  15.750   1.3420   0.07177   0.06394  -0.0141   0.1320   1.0000
  16.000   1.3457   0.07405   0.06616  -0.0138   0.1289   1.0000
  16.250   1.3408   0.07784   0.07017  -0.0144   0.1258   1.0000
  16.500   1.3363   0.08157   0.07406  -0.0150   0.1225   1.0000
  16.750   1.3330   0.08511   0.07767  -0.0157   0.1193   1.0000
  17.000   1.3367   0.08748   0.07998  -0.0158   0.1160   1.0000
  17.250   1.3264   0.09236   0.08509  -0.0173   0.1134   1.0000
  17.500   1.3176   0.09706   0.08997  -0.0188   0.1105   1.0000
  17.750   1.3120   0.10126   0.09427  -0.0201   0.1077   1.0000
  18.000   1.3118   0.10449   0.09753  -0.0211   0.1050   1.0000
  18.250   1.3090   0.10824   0.10135  -0.0223   0.1025   1.0000
  18.500   1.2940   0.11437   0.10772  -0.0250   0.1002   1.0000
  18.750   1.2813   0.12019   0.11371  -0.0277   0.0978   1.0000
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