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CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CLARK YM-15 AIRFOIL (clarym15-il)
Reynolds number: 100,000
Max Cl/Cd: 47.56 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarym15-il-100000.txt
Download as CSV file: xf-clarym15-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3523   0.10319   0.09832  -0.0331   1.0000   0.1651
  -8.750  -0.4163   0.10297   0.09830  -0.0319   1.0000   0.1688
  -8.500  -0.4759   0.10229   0.09781  -0.0296   1.0000   0.1693
  -8.250  -0.4210   0.09778   0.09324  -0.0265   1.0000   0.1722
  -8.000  -0.4194   0.09616   0.09165  -0.0235   1.0000   0.1746
  -7.750  -0.4315   0.09469   0.09025  -0.0207   1.0000   0.1773
  -7.500  -0.4572   0.09326   0.08892  -0.0180   1.0000   0.1804
  -7.250  -0.5917   0.05963   0.05422  -0.0440   0.9886   0.1090
  -7.000  -0.5683   0.05478   0.04922  -0.0469   0.9832   0.1057
  -6.750  -0.5685   0.04423   0.03703  -0.0493   0.9756   0.0976
  -6.500  -0.5374   0.04127   0.03394  -0.0518   0.9705   0.0994
  -6.250  -0.5081   0.03936   0.03188  -0.0533   0.9643   0.1012
  -6.000  -0.4777   0.03710   0.02924  -0.0548   0.9580   0.1025
  -5.750  -0.4386   0.03502   0.02674  -0.0577   0.9538   0.1046
  -5.500  -0.4149   0.03356   0.02494  -0.0574   0.9456   0.1071
  -5.250  -0.3768   0.03203   0.02302  -0.0597   0.9405   0.1115
  -5.000  -0.3463   0.03107   0.02208  -0.0607   0.9339   0.1163
  -4.750  -0.3132   0.03011   0.02089  -0.0618   0.9272   0.1223
  -4.500  -0.2711   0.02902   0.01986  -0.0647   0.9229   0.1317
  -4.250  -0.2472   0.02835   0.01914  -0.0642   0.9144   0.1418
  -4.000  -0.2102   0.02763   0.01847  -0.0661   0.9087   0.1574
  -3.750  -0.1749   0.02714   0.01808  -0.0677   0.9029   0.1768
  -3.500  -0.1487   0.02683   0.01784  -0.0677   0.8942   0.1969
  -3.250  -0.1073   0.02636   0.01750  -0.0703   0.8896   0.2269
  -3.000  -0.0865   0.02625   0.01746  -0.0693   0.8801   0.2557
  -2.750  -0.0493   0.02567   0.01715  -0.0711   0.8743   0.3019
  -2.500  -0.0195   0.02518   0.01694  -0.0715   0.8667   0.3537
  -2.250   0.0137   0.02459   0.01663  -0.0723   0.8584   0.4106
  -2.000   0.0652   0.02356   0.01598  -0.0757   0.8542   0.4914
  -1.500   0.1288   0.02191   0.01540  -0.0741   0.8374   0.7292
  -1.250   0.1520   0.02194   0.01573  -0.0712   0.8262   0.8553
  -1.000   0.2456   0.02170   0.01538  -0.0809   0.8246   0.9565
  -0.750   0.3746   0.02098   0.01439  -0.0988   0.8244   0.9931
  -0.500   0.4335   0.02023   0.01345  -0.1044   0.8197   1.0000
  -0.250   0.4426   0.02034   0.01348  -0.1015   0.8066   1.0000
   0.000   0.4649   0.02016   0.01318  -0.1003   0.7974   1.0000
   0.250   0.4881   0.01995   0.01287  -0.0993   0.7876   1.0000
   0.500   0.5055   0.01996   0.01279  -0.0973   0.7763   1.0000
   0.750   0.5376   0.01952   0.01222  -0.0974   0.7684   1.0000
   1.000   0.5531   0.01961   0.01225  -0.0950   0.7557   1.0000
   1.250   0.5829   0.01929   0.01183  -0.0947   0.7470   1.0000
   1.500   0.6046   0.01923   0.01169  -0.0932   0.7352   1.0000
   1.750   0.6248   0.01923   0.01163  -0.0915   0.7228   1.0000
   2.000   0.6564   0.01889   0.01117  -0.0914   0.7130   1.0000
   2.250   0.6789   0.01881   0.01101  -0.0899   0.6995   1.0000
   2.500   0.7001   0.01879   0.01094  -0.0883   0.6852   1.0000
   2.750   0.7237   0.01873   0.01080  -0.0870   0.6710   1.0000
   3.000   0.7489   0.01866   0.01064  -0.0859   0.6568   1.0000
   3.250   0.7746   0.01859   0.01046  -0.0850   0.6419   1.0000
   3.500   0.7994   0.01858   0.01033  -0.0839   0.6260   1.0000
   3.750   0.8230   0.01864   0.01029  -0.0827   0.6092   1.0000
   4.000   0.8464   0.01877   0.01030  -0.0815   0.5924   1.0000
   4.250   0.8706   0.01896   0.01036  -0.0805   0.5765   1.0000
   4.500   0.8921   0.01927   0.01059  -0.0792   0.5606   1.0000
   4.750   0.9132   0.01963   0.01088  -0.0779   0.5455   1.0000
   5.000   0.9347   0.02003   0.01122  -0.0766   0.5318   1.0000
   5.250   0.9587   0.02043   0.01155  -0.0759   0.5200   1.0000
   5.500   0.9843   0.02081   0.01182  -0.0754   0.5092   1.0000
   5.750   1.0039   0.02133   0.01238  -0.0740   0.4980   1.0000
   6.000   1.0304   0.02175   0.01269  -0.0737   0.4888   1.0000
   6.250   1.0504   0.02226   0.01324  -0.0724   0.4786   1.0000
   6.500   1.0742   0.02275   0.01369  -0.0717   0.4696   1.0000
   6.750   1.0965   0.02321   0.01416  -0.0708   0.4602   1.0000
   7.000   1.1184   0.02374   0.01470  -0.0698   0.4513   1.0000
   7.250   1.1422   0.02414   0.01506  -0.0691   0.4420   1.0000
   7.500   1.1608   0.02468   0.01565  -0.0677   0.4323   1.0000
   7.750   1.1889   0.02500   0.01583  -0.0676   0.4229   1.0000
   8.000   1.2027   0.02559   0.01658  -0.0654   0.4131   1.0000
   8.250   1.2292   0.02602   0.01690  -0.0652   0.4043   1.0000
   8.500   1.2447   0.02662   0.01765  -0.0633   0.3951   1.0000
   8.750   1.2693   0.02714   0.01811  -0.0629   0.3865   1.0000
   9.000   1.2858   0.02773   0.01880  -0.0612   0.3772   1.0000
   9.250   1.3072   0.02834   0.01942  -0.0603   0.3683   1.0000
   9.500   1.3262   0.02889   0.01999  -0.0590   0.3586   1.0000
   9.750   1.3419   0.02961   0.02080  -0.0572   0.3491   1.0000
  10.000   1.3682   0.03010   0.02116  -0.0570   0.3389   1.0000
  10.250   1.3740   0.03092   0.02221  -0.0538   0.3288   1.0000
  10.500   1.3937   0.03155   0.02279  -0.0527   0.3182   1.0000
  10.750   1.4069   0.03216   0.02344  -0.0506   0.3071   1.0000
  11.000   1.4122   0.03303   0.02445  -0.0475   0.2962   1.0000
  11.250   1.4279   0.03367   0.02503  -0.0458   0.2850   1.0000
  11.500   1.4311   0.03439   0.02583  -0.0423   0.2742   1.0000
  11.750   1.4302   0.03537   0.02691  -0.0385   0.2640   1.0000
  12.000   1.4422   0.03601   0.02745  -0.0364   0.2536   1.0000
  12.250   1.4367   0.03720   0.02882  -0.0324   0.2440   1.0000
  12.500   1.4408   0.03832   0.02997  -0.0299   0.2351   1.0000
  12.750   1.4468   0.03935   0.03099  -0.0276   0.2264   1.0000
  13.000   1.4464   0.04094   0.03271  -0.0250   0.2187   1.0000
  13.250   1.4561   0.04199   0.03371  -0.0234   0.2112   1.0000
  13.500   1.4563   0.04381   0.03566  -0.0212   0.2047   1.0000
  13.750   1.4624   0.04528   0.03719  -0.0196   0.1984   1.0000
  14.000   1.4760   0.04665   0.03852  -0.0185   0.1928   1.0000
  14.250   1.4708   0.04903   0.04114  -0.0165   0.1881   1.0000
  14.500   1.4854   0.05018   0.04224  -0.0156   0.1827   1.0000
  14.750   1.4914   0.05212   0.04426  -0.0144   0.1781   1.0000
  15.000   1.4800   0.05507   0.04747  -0.0126   0.1744   1.0000
  15.250   1.4888   0.05656   0.04896  -0.0117   0.1695   1.0000
  15.500   1.5015   0.05809   0.05045  -0.0110   0.1647   1.0000
  15.750   1.4813   0.06196   0.05464  -0.0095   0.1620   1.0000
  16.000   1.4686   0.06540   0.05827  -0.0086   0.1587   1.0000
  16.250   1.5051   0.06464   0.05721  -0.0083   0.1518   1.0000
  16.500   1.4775   0.06946   0.06237  -0.0075   0.1500   1.0000
  16.750   1.4494   0.07483   0.06804  -0.0074   0.1481   1.0000
  17.000   1.4205   0.08081   0.07429  -0.0080   0.1463   1.0000
  17.250   1.3901   0.08750   0.08121  -0.0094   0.1445   1.0000
  17.500   1.3600   0.09464   0.08855  -0.0114   0.1427   1.0000
  17.750   1.3267   0.10282   0.09690  -0.0143   0.1411   1.0000
  18.000   1.2904   0.11216   0.10639  -0.0181   0.1396   1.0000
  18.500   1.3737   0.10427   0.09828  -0.0131   0.1262   1.0000
  18.750   0.9207   0.21962   0.21379  -0.0820   0.1834   1.0000
  19.000   0.9367   0.22378   0.21801  -0.0820   0.1794   1.0000
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