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NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(2)-615 (naca632615-il)
Reynolds number: 50,000
Max Cl/Cd: 27.78 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca632615-il-50000.txt
Download as CSV file: xf-naca632615-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-615                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2984   0.11049   0.10367  -0.0324   1.0000   0.3395
  -9.250  -0.2949   0.10768   0.10092  -0.0308   1.0000   0.3470
  -9.000  -0.3183   0.10786   0.10126  -0.0278   1.0000   0.3572
  -8.750  -0.3097   0.10453   0.09798  -0.0258   1.0000   0.3625
  -8.500  -0.3173   0.10316   0.09670  -0.0230   1.0000   0.3693
  -8.250  -0.3494   0.10343   0.09715  -0.0191   1.0000   0.3753
  -8.000  -0.5667   0.08350   0.07772  -0.0391   1.0000   0.1785
  -7.750  -0.5592   0.08065   0.07491  -0.0364   1.0000   0.1744
  -7.500  -0.6111   0.07205   0.06618  -0.0413   1.0000   0.1591
  -7.250  -0.6452   0.06314   0.05655  -0.0467   1.0000   0.1465
  -7.000  -0.6412   0.05898   0.05216  -0.0472   1.0000   0.1455
  -6.750  -0.6333   0.05483   0.04766  -0.0481   1.0000   0.1446
  -6.500  -0.6204   0.05075   0.04314  -0.0493   1.0000   0.1435
  -6.250  -0.6031   0.04720   0.03907  -0.0506   1.0000   0.1437
  -6.000  -0.5822   0.04424   0.03544  -0.0520   1.0000   0.1464
  -5.750  -0.5613   0.04161   0.03249  -0.0525   1.0000   0.1494
  -5.500  -0.5410   0.03973   0.03052  -0.0523   1.0000   0.1535
  -5.250  -0.5188   0.03813   0.02856  -0.0525   1.0000   0.1601
  -5.000  -0.4965   0.03649   0.02666  -0.0525   1.0000   0.1658
  -4.750  -0.4759   0.03533   0.02545  -0.0520   1.0000   0.1745
  -4.500  -0.4553   0.03422   0.02431  -0.0514   1.0000   0.1849
  -4.250  -0.4344   0.03330   0.02331  -0.0506   1.0000   0.1972
  -4.000  -0.4147   0.03244   0.02261  -0.0498   1.0000   0.2157
  -3.750  -0.3938   0.03149   0.02187  -0.0493   1.0000   0.2456
  -3.500  -0.3677   0.02972   0.02131  -0.0502   1.0000   0.3516
  -3.250  -0.3586   0.03119   0.02398  -0.0436   0.9968   0.5771
  -3.000  -0.3476   0.03332   0.02611  -0.0377   0.9902   0.6364
  -2.750  -0.3344   0.03505   0.02775  -0.0327   0.9838   0.6793
  -2.500  -0.3267   0.03613   0.02876  -0.0273   0.9779   0.7129
  -2.250  -0.3189   0.03711   0.02967  -0.0220   0.9725   0.7462
  -2.000  -0.3141   0.03778   0.03026  -0.0163   0.9674   0.7786
  -1.750  -0.3134   0.03804   0.03048  -0.0100   0.9630   0.8078
  -1.500  -0.3086   0.03825   0.03061  -0.0049   0.9591   0.8383
  -1.250  -0.2992   0.03837   0.03062  -0.0010   0.9544   0.8686
  -1.000  -0.2894   0.03815   0.03029   0.0019   0.9506   0.8956
  -0.750  -0.2661   0.03822   0.03020   0.0017   0.9460   0.9216
  -0.500  -0.2165   0.03889   0.03064  -0.0037   0.9375   0.9432
  -0.250  -0.1517   0.03984   0.03134  -0.0126   0.9281   0.9617
   0.000  -0.0769   0.04102   0.03229  -0.0238   0.9179   0.9758
   0.250   0.0065   0.04245   0.03347  -0.0365   0.9070   0.9899
   0.500   0.0269   0.04274   0.03368  -0.0387   0.9023   1.0000
   0.750   0.0138   0.04253   0.03345  -0.0352   0.9025   1.0000
   1.000   0.0052   0.04244   0.03331  -0.0326   0.9046   1.0000
   1.250   0.0153   0.04292   0.03371  -0.0332   0.9062   1.0000
   1.500   0.0372   0.04388   0.03457  -0.0358   0.9076   1.0000
   1.750  -0.0722   0.03947   0.03039  -0.0171   1.0000   1.0000
   2.000  -0.0437   0.04066   0.03145  -0.0206   1.0000   1.0000
   2.250  -0.0155   0.04195   0.03263  -0.0241   1.0000   1.0000
   2.500   0.0120   0.04331   0.03390  -0.0273   1.0000   1.0000
   2.750   0.0487   0.04540   0.03587  -0.0322   0.9955   1.0000
   3.000   0.0882   0.04774   0.03811  -0.0376   0.9869   1.0000
   3.250   0.1248   0.05000   0.04029  -0.0423   0.9775   1.0000
   3.500   0.1625   0.05253   0.04275  -0.0471   0.9683   1.0000
   3.750   0.2035   0.05537   0.04552  -0.0523   0.9563   1.0000
   4.000   0.2306   0.05697   0.04710  -0.0550   0.9432   1.0000
   4.250   0.2568   0.05876   0.04887  -0.0574   0.9303   1.0000
   4.500   0.2839   0.06084   0.05093  -0.0600   0.9185   1.0000
   4.750   0.3201   0.06381   0.05388  -0.0640   0.9073   1.0000
   5.000   0.3500   0.06603   0.05612  -0.0667   0.8927   1.0000
   5.250   0.3695   0.06756   0.05766  -0.0679   0.8781   1.0000
   5.500   0.3893   0.06941   0.05956  -0.0691   0.8647   1.0000
   5.750   0.4128   0.07164   0.06182  -0.0708   0.8512   1.0000
   6.000   0.4415   0.07439   0.06461  -0.0733   0.8388   1.0000
   6.250   0.4718   0.07716   0.06744  -0.0759   0.8236   1.0000
   6.500   0.5010   0.07985   0.07019  -0.0781   0.8076   1.0000
   6.750   0.5245   0.08215   0.07257  -0.0795   0.7910   1.0000
   7.000   0.5445   0.08428   0.07480  -0.0804   0.7746   1.0000
   7.250   0.5674   0.08674   0.07733  -0.0817   0.7574   1.0000
   7.500   0.5838   0.08885   0.07953  -0.0822   0.7403   1.0000
   7.750   0.5974   0.09088   0.08166  -0.0824   0.7225   1.0000
   8.000   0.7122   0.08483   0.07577  -0.0807   0.6061   1.0000
   8.250   0.7312   0.08635   0.07742  -0.0805   0.5873   1.0000
   8.500   0.7555   0.08755   0.07877  -0.0804   0.5679   1.0000
   8.750   0.7902   0.08804   0.07942  -0.0802   0.5481   1.0000
   9.000   0.8332   0.08762   0.07921  -0.0798   0.5283   1.0000
   9.250   0.8368   0.08985   0.08155  -0.0790   0.5087   1.0000
   9.500   0.8563   0.09080   0.08266  -0.0782   0.4883   1.0000
   9.750   0.9071   0.08830   0.08044  -0.0764   0.4670   1.0000
  10.000   0.9292   0.08828   0.08060  -0.0749   0.4453   1.0000
  10.250   0.9759   0.08441   0.07703  -0.0719   0.4213   1.0000
  10.500   1.2346   0.04444   0.03744  -0.0572   0.3379   1.0000
  10.750   1.2301   0.04601   0.03847  -0.0535   0.2855   1.0000
  11.000   1.2286   0.04845   0.04031  -0.0507   0.2417   1.0000
  11.250   1.2344   0.05105   0.04253  -0.0487   0.2080   1.0000
  11.500   1.2547   0.05331   0.04448  -0.0474   0.1805   1.0000
  11.750   1.2849   0.05546   0.04647  -0.0469   0.1599   1.0000
  12.000   1.3227   0.05786   0.04873  -0.0471   0.1436   1.0000
  12.250   1.3343   0.06117   0.05236  -0.0461   0.1360   1.0000
  12.500   1.3643   0.06437   0.05554  -0.0464   0.1267   1.0000
  12.750   1.3554   0.06810   0.05971  -0.0446   0.1240   1.0000
  13.000   1.3499   0.07198   0.06391  -0.0433   0.1209   1.0000
  13.250   1.3824   0.07570   0.06753  -0.0438   0.1141   1.0000
  13.500   1.3613   0.08010   0.07231  -0.0423   0.1136   1.0000
  13.750   1.3384   0.08506   0.07762  -0.0415   0.1133   1.0000
  14.000   1.3132   0.09061   0.08348  -0.0415   0.1134   1.0000
  14.250   1.2862   0.09679   0.08994  -0.0423   0.1136   1.0000
  14.500   1.2582   0.10366   0.09705  -0.0440   0.1140   1.0000
  14.750   0.9870   0.16046   0.15413  -0.0819   0.1535   1.0000
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