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NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M15 AIRFOIL (m15-il)
Reynolds number: 200,000
Max Cl/Cd: 72.32 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m15-il-200000-n5.txt
Download as CSV file: xf-m15-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M15 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3893   0.09027   0.08673  -0.0373   1.0000   0.0387
  -9.000  -0.3822   0.08760   0.08409  -0.0373   1.0000   0.0378
  -8.750  -0.3823   0.08378   0.08031  -0.0393   1.0000   0.0370
  -8.500  -0.3807   0.07828   0.07482  -0.0454   0.9699   0.0361
  -8.250  -0.3800   0.07206   0.06853  -0.0523   0.9400   0.0355
  -8.000  -0.3767   0.06675   0.06310  -0.0566   0.9169   0.0358
  -7.750  -0.3738   0.06160   0.05779  -0.0595   0.8971   0.0360
  -7.500  -0.3706   0.05617   0.05215  -0.0614   0.8797   0.0358
  -7.250  -0.3668   0.05033   0.04602  -0.0626   0.8640   0.0353
  -7.000  -0.3615   0.04426   0.03956  -0.0629   0.8497   0.0350
  -6.750  -0.3536   0.03873   0.03357  -0.0623   0.8367   0.0350
  -6.500  -0.3400   0.03508   0.02952  -0.0614   0.8248   0.0357
  -6.250  -0.3252   0.03154   0.02551  -0.0602   0.8143   0.0363
  -6.000  -0.3080   0.02838   0.02185  -0.0591   0.8037   0.0365
  -5.750  -0.2880   0.02598   0.01900  -0.0580   0.7943   0.0367
  -5.500  -0.2658   0.02413   0.01673  -0.0572   0.7848   0.0371
  -5.250  -0.2421   0.02263   0.01488  -0.0565   0.7757   0.0375
  -5.000  -0.2175   0.02141   0.01333  -0.0559   0.7669   0.0379
  -4.750  -0.1920   0.02042   0.01207  -0.0554   0.7567   0.0385
  -4.500  -0.1661   0.01971   0.01106  -0.0549   0.7467   0.0392
  -4.250  -0.1403   0.01875   0.00996  -0.0545   0.7364   0.0399
  -4.000  -0.1140   0.01801   0.00912  -0.0543   0.7276   0.0404
  -3.750  -0.0874   0.01738   0.00839  -0.0540   0.7203   0.0410
  -3.500  -0.0606   0.01683   0.00776  -0.0537   0.7135   0.0416
  -3.250  -0.0337   0.01633   0.00720  -0.0535   0.7065   0.0424
  -3.000  -0.0071   0.01589   0.00666  -0.0532   0.7006   0.0432
  -2.750   0.0199   0.01547   0.00621  -0.0530   0.6938   0.0442
  -2.500   0.0466   0.01511   0.00578  -0.0527   0.6878   0.0452
  -2.250   0.0735   0.01482   0.00542  -0.0525   0.6819   0.0467
  -2.000   0.1001   0.01446   0.00508  -0.0523   0.6754   0.0488
  -1.750   0.1269   0.01422   0.00480  -0.0520   0.6698   0.0511
  -1.500   0.1539   0.01400   0.00455  -0.0519   0.6639   0.0536
  -1.250   0.1810   0.01379   0.00431  -0.0516   0.6576   0.0568
  -1.000   0.2078   0.01359   0.00409  -0.0514   0.6521   0.0629
  -0.750   0.2348   0.01338   0.00396  -0.0513   0.6455   0.0760
  -0.500   0.2616   0.01318   0.00385  -0.0511   0.6396   0.1053
  -0.250   0.2880   0.01297   0.00376  -0.0509   0.6338   0.1463
   0.000   0.3142   0.01271   0.00372  -0.0507   0.6269   0.2079
   0.250   0.3371   0.01208   0.00363  -0.0500   0.6209   0.3796
   0.750   0.4594   0.01117   0.00424  -0.0624   0.6056   0.9902
   1.000   0.5113   0.01123   0.00421  -0.0676   0.5972   1.0000
   1.250   0.5365   0.01128   0.00417  -0.0672   0.5899   1.0000
   1.500   0.5617   0.01132   0.00416  -0.0667   0.5823   1.0000
   1.750   0.5867   0.01138   0.00414  -0.0662   0.5741   1.0000
   2.000   0.6117   0.01143   0.00416  -0.0657   0.5658   1.0000
   2.250   0.6365   0.01150   0.00417  -0.0652   0.5574   1.0000
   2.500   0.6613   0.01158   0.00422  -0.0646   0.5484   1.0000
   2.750   0.6857   0.01167   0.00424  -0.0640   0.5396   1.0000
   3.000   0.7103   0.01175   0.00432  -0.0635   0.5296   1.0000
   3.250   0.7346   0.01186   0.00438  -0.0628   0.5204   1.0000
   3.500   0.7587   0.01198   0.00446  -0.0621   0.5105   1.0000
   3.750   0.7828   0.01211   0.00457  -0.0615   0.5008   1.0000
   4.000   0.8066   0.01226   0.00467  -0.0608   0.4920   1.0000
   4.250   0.8304   0.01242   0.00481  -0.0601   0.4826   1.0000
   4.500   0.8539   0.01260   0.00496  -0.0593   0.4742   1.0000
   4.750   0.8774   0.01279   0.00512  -0.0586   0.4657   1.0000
   5.000   0.9005   0.01299   0.00531  -0.0578   0.4560   1.0000
   5.250   0.9231   0.01324   0.00549  -0.0568   0.4457   1.0000
   5.500   0.9459   0.01347   0.00571  -0.0560   0.4353   1.0000
   5.750   0.9688   0.01371   0.00596  -0.0552   0.4274   1.0000
   6.000   0.9917   0.01396   0.00621  -0.0544   0.4200   1.0000
   6.250   1.0144   0.01422   0.00648  -0.0535   0.4131   1.0000
   6.500   1.0373   0.01447   0.00678  -0.0527   0.4062   1.0000
   6.750   1.0597   0.01477   0.00707  -0.0519   0.3999   1.0000
   7.000   1.0826   0.01501   0.00740  -0.0511   0.3924   1.0000
   7.250   1.1048   0.01532   0.00772  -0.0502   0.3852   1.0000
   7.500   1.1274   0.01559   0.00808  -0.0494   0.3781   1.0000
   7.750   1.1487   0.01591   0.00842  -0.0484   0.3689   1.0000
   8.000   1.1695   0.01621   0.00878  -0.0473   0.3559   1.0000
   8.250   1.1892   0.01655   0.00914  -0.0461   0.3409   1.0000
   8.500   1.2078   0.01693   0.00953  -0.0447   0.3238   1.0000
   8.750   1.2247   0.01740   0.00996  -0.0431   0.3013   1.0000
   9.000   1.2386   0.01801   0.01048  -0.0411   0.2735   1.0000
   9.250   1.2505   0.01875   0.01110  -0.0389   0.2456   1.0000
   9.500   1.2606   0.01959   0.01185  -0.0365   0.2193   1.0000
   9.750   1.2679   0.02052   0.01268  -0.0338   0.1952   1.0000
  10.250   1.2752   0.02272   0.01472  -0.0276   0.1543   1.0000
  10.500   1.2783   0.02407   0.01600  -0.0250   0.1332   1.0000
  10.750   1.2791   0.02571   0.01753  -0.0225   0.1071   1.0000
  11.250   1.2751   0.02988   0.02148  -0.0183   0.0658   1.0000
  11.500   1.2757   0.03197   0.02357  -0.0169   0.0559   1.0000
  11.750   1.2767   0.03415   0.02577  -0.0156   0.0491   1.0000
  12.000   1.2789   0.03632   0.02800  -0.0147   0.0436   1.0000
  12.250   1.2803   0.03863   0.03037  -0.0138   0.0395   1.0000
  12.500   1.2813   0.04106   0.03287  -0.0131   0.0361   1.0000
  12.750   1.2808   0.04370   0.03558  -0.0126   0.0336   1.0000
  13.000   1.2816   0.04626   0.03826  -0.0121   0.0315   1.0000
  13.250   1.2804   0.04909   0.04118  -0.0118   0.0299   1.0000
  13.500   1.2763   0.05230   0.04446  -0.0116   0.0286   1.0000
  13.750   1.2749   0.05530   0.04757  -0.0115   0.0273   1.0000
  14.000   1.2732   0.05843   0.05082  -0.0115   0.0262   1.0000
  14.250   1.2709   0.06171   0.05420  -0.0117   0.0251   1.0000
  14.500   1.2672   0.06524   0.05782  -0.0120   0.0242   1.0000
  14.750   1.2617   0.06911   0.06176  -0.0125   0.0235   1.0000
  15.000   1.2582   0.07280   0.06557  -0.0131   0.0228   1.0000
  15.250   1.2556   0.07640   0.06930  -0.0136   0.0221   1.0000
  15.500   1.2527   0.08012   0.07312  -0.0143   0.0215   1.0000
  15.750   1.2499   0.08387   0.07698  -0.0150   0.0210   1.0000
  16.000   1.2471   0.08766   0.08086  -0.0159   0.0205   1.0000
  16.250   1.2442   0.09149   0.08477  -0.0168   0.0200   1.0000
  16.500   1.2411   0.09536   0.08871  -0.0177   0.0195   1.0000
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