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NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 200,000
Max Cl/Cd: 54.36 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca641112-il-200000.txt
Download as CSV file: xf-naca641112-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-112                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6188   0.09354   0.09002  -0.0198   1.0000   0.0683
 -10.500  -0.6215   0.08853   0.08503  -0.0225   1.0000   0.0698
 -10.250  -0.6429   0.07995   0.07647  -0.0296   1.0000   0.0706
 -10.000  -0.6725   0.07275   0.06923  -0.0351   1.0000   0.0707
  -9.750  -0.6992   0.06777   0.06417  -0.0374   1.0000   0.0708
  -9.500  -0.7204   0.06426   0.06057  -0.0369   1.0000   0.0715
  -9.250  -0.7347   0.06087   0.05702  -0.0363   1.0000   0.0735
  -8.250  -0.7598   0.03769   0.03132  -0.0274   1.0000   0.0423
  -8.000  -0.7443   0.03339   0.02681  -0.0265   1.0000   0.0412
  -7.750  -0.7285   0.03186   0.02496  -0.0248   1.0000   0.0418
  -7.500  -0.7145   0.02950   0.02229  -0.0230   1.0000   0.0423
  -7.250  -0.7003   0.02708   0.01966  -0.0211   1.0000   0.0426
  -7.000  -0.6870   0.02502   0.01745  -0.0188   1.0000   0.0430
  -6.750  -0.6748   0.02339   0.01574  -0.0165   1.0000   0.0437
  -6.500  -0.6631   0.02223   0.01454  -0.0141   1.0000   0.0446
  -6.250  -0.6330   0.02103   0.01328  -0.0151   0.9965   0.0466
  -6.000  -0.5941   0.01997   0.01215  -0.0177   0.9909   0.0502
  -5.750  -0.5544   0.01895   0.01101  -0.0202   0.9855   0.0526
  -5.500  -0.5196   0.01724   0.00941  -0.0223   0.9795   0.0571
  -5.250  -0.4802   0.01647   0.00858  -0.0251   0.9736   0.0640
  -5.000  -0.4439   0.01530   0.00748  -0.0276   0.9673   0.0737
  -4.750  -0.4088   0.01432   0.00655  -0.0296   0.9596   0.0933
  -4.500  -0.3887   0.01177   0.00531  -0.0303   0.9487   0.3259
  -4.250  -0.3643   0.01094   0.00535  -0.0300   0.9394   0.5423
  -4.000  -0.3355   0.01095   0.00539  -0.0298   0.9298   0.5868
  -3.750  -0.3088   0.01102   0.00544  -0.0292   0.9197   0.6157
  -3.500  -0.2815   0.01110   0.00546  -0.0286   0.9110   0.6372
  -3.250  -0.2565   0.01121   0.00552  -0.0276   0.9006   0.6574
  -3.000  -0.2325   0.01144   0.00580  -0.0261   0.8910   0.6804
  -2.750  -0.2087   0.01171   0.00605  -0.0243   0.8828   0.7037
  -2.500  -0.1845   0.01186   0.00620  -0.0231   0.8726   0.7188
  -2.250  -0.1588   0.01188   0.00618  -0.0222   0.8642   0.7270
  -2.000  -0.1327   0.01182   0.00603  -0.0218   0.8551   0.7348
  -1.750  -0.1066   0.01182   0.00600  -0.0212   0.8466   0.7420
  -1.500  -0.0801   0.01177   0.00588  -0.0208   0.8388   0.7502
  -1.250  -0.0538   0.01177   0.00586  -0.0204   0.8300   0.7567
  -1.000  -0.0269   0.01171   0.00572  -0.0201   0.8227   0.7645
  -0.750  -0.0005   0.01170   0.00573  -0.0197   0.8138   0.7708
  -0.500   0.0267   0.01167   0.00561  -0.0195   0.8071   0.7791
  -0.250   0.0531   0.01168   0.00566  -0.0192   0.7987   0.7851
   0.000   0.0804   0.01166   0.00559  -0.0190   0.7922   0.7941
   0.250   0.1065   0.01169   0.00567  -0.0185   0.7840   0.8005
   0.500   0.1337   0.01168   0.00562  -0.0184   0.7774   0.8095
   0.750   0.1598   0.01172   0.00572  -0.0179   0.7701   0.8163
   1.000   0.1868   0.01174   0.00573  -0.0177   0.7635   0.8254
   1.250   0.2126   0.01179   0.00583  -0.0171   0.7569   0.8333
   1.500   0.2389   0.01182   0.00590  -0.0168   0.7498   0.8424
   1.750   0.2649   0.01186   0.00596  -0.0162   0.7440   0.8514
   2.000   0.2902   0.01189   0.00607  -0.0156   0.7354   0.8600
   2.250   0.3163   0.01191   0.00609  -0.0150   0.7292   0.8703
   2.500   0.3405   0.01196   0.00625  -0.0142   0.7209   0.8795
   2.750   0.3659   0.01197   0.00629  -0.0133   0.7150   0.8895
   3.000   0.3899   0.01194   0.00634  -0.0123   0.7041   0.9008
   3.250   0.4133   0.01172   0.00614  -0.0107   0.6886   0.9114
   3.500   0.4371   0.01142   0.00578  -0.0090   0.6687   0.9223
   3.750   0.4615   0.01119   0.00559  -0.0077   0.6460   0.9343
   4.000   0.4892   0.01104   0.00546  -0.0073   0.6265   0.9462
   4.250   0.5202   0.01095   0.00541  -0.0077   0.6045   0.9578
   4.500   0.5572   0.01089   0.00540  -0.0094   0.5742   0.9666
   4.750   0.5941   0.01093   0.00534  -0.0111   0.5176   0.9756
   5.000   0.6184   0.01287   0.00583  -0.0122   0.2197   0.9877
   5.250   0.6463   0.01515   0.00723  -0.0144   0.0841   1.0000
   5.500   0.6506   0.01573   0.00779  -0.0109   0.0744   1.0000
   5.750   0.6616   0.01661   0.00857  -0.0086   0.0662   1.0000
   6.000   0.6817   0.01729   0.00930  -0.0077   0.0603   1.0000
   6.250   0.6999   0.01840   0.01033  -0.0066   0.0557   1.0000
   6.500   0.7210   0.01945   0.01141  -0.0058   0.0522   1.0000
   6.750   0.7438   0.02032   0.01231  -0.0052   0.0486   1.0000
   7.000   0.7666   0.02146   0.01340  -0.0047   0.0459   1.0000
   7.250   0.7921   0.02392   0.01581  -0.0046   0.0438   1.0000
   7.500   0.8175   0.02514   0.01721  -0.0042   0.0430   1.0000
   7.750   0.8424   0.02652   0.01877  -0.0037   0.0417   1.0000
   8.000   0.8662   0.02797   0.02041  -0.0032   0.0400   1.0000
   8.250   0.8894   0.02993   0.02260  -0.0027   0.0392   1.0000
   8.500   0.9106   0.03243   0.02540  -0.0019   0.0391   1.0000
   8.750   0.9285   0.03556   0.02894  -0.0007   0.0396   1.0000
   9.000   0.9420   0.03939   0.03317   0.0008   0.0409   1.0000
   9.250   0.9514   0.04362   0.03775   0.0023   0.0421   1.0000
   9.500   0.9695   0.04711   0.04145   0.0032   0.0453   1.0000
  12.000   0.7934   0.10495   0.10148   0.0025   0.0664   1.0000
  12.250   0.7638   0.11367   0.11024  -0.0049   0.0662   1.0000
  12.500   0.7170   0.12912   0.12562  -0.0207   0.0641   1.0000
  12.750   0.7114   0.13530   0.13177  -0.0249   0.0614   1.0000
  13.000   0.7131   0.13990   0.13637  -0.0271   0.0592   1.0000
  13.250   0.7201   0.14334   0.13981  -0.0281   0.0574   1.0000
  13.500   0.7314   0.14606   0.14255  -0.0280   0.0561   1.0000
  13.750   0.5744   0.14627   0.14313  -0.0288   0.0591   1.0000
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