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NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012 AIRFOILS (n0012-il)
Reynolds number: 200,000
Max Cl/Cd: 47.43 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n0012-il-200000.txt
Download as CSV file: xf-n0012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012 AIRFOILS                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.9628   0.07963   0.07518  -0.0278   1.0000   0.0399
 -13.750  -0.9895   0.07225   0.06762  -0.0322   1.0000   0.0398
 -13.500  -1.0148   0.06593   0.06110  -0.0354   1.0000   0.0397
 -13.250  -1.0382   0.06063   0.05557  -0.0371   1.0000   0.0396
 -13.000  -1.0594   0.05622   0.05090  -0.0373   1.0000   0.0396
 -12.750  -1.0784   0.05255   0.04697  -0.0361   1.0000   0.0397
 -12.500  -1.0955   0.04958   0.04371  -0.0335   1.0000   0.0399
 -12.000  -1.1063   0.04365   0.03734  -0.0286   1.0000   0.0410
 -11.750  -1.0964   0.04195   0.03559  -0.0273   1.0000   0.0420
 -11.500  -1.0857   0.04034   0.03389  -0.0259   1.0000   0.0430
 -11.250  -1.0770   0.03842   0.03176  -0.0241   1.0000   0.0441
 -11.000  -1.0679   0.03635   0.02942  -0.0222   1.0000   0.0451
 -10.750  -1.0569   0.03444   0.02717  -0.0203   1.0000   0.0462
 -10.500  -1.0443   0.03262   0.02503  -0.0186   1.0000   0.0474
 -10.250  -1.0249   0.03076   0.02323  -0.0180   1.0000   0.0492
 -10.000  -1.0066   0.02966   0.02206  -0.0169   1.0000   0.0511
  -9.750  -0.9881   0.02844   0.02068  -0.0156   1.0000   0.0532
  -9.500  -0.9692   0.02734   0.01932  -0.0143   1.0000   0.0550
  -9.250  -0.9491   0.02559   0.01762  -0.0135   1.0000   0.0576
  -9.000  -0.9290   0.02473   0.01674  -0.0124   1.0000   0.0604
  -8.750  -0.9087   0.02387   0.01574  -0.0112   1.0000   0.0635
  -8.500  -0.8890   0.02252   0.01438  -0.0101   1.0000   0.0667
  -8.250  -0.8689   0.02174   0.01362  -0.0089   1.0000   0.0707
  -8.000  -0.8481   0.02113   0.01286  -0.0077   1.0000   0.0749
  -7.750  -0.8300   0.01996   0.01181  -0.0062   1.0000   0.0799
  -7.500  -0.8096   0.01936   0.01114  -0.0049   1.0000   0.0858
  -7.250  -0.7919   0.01844   0.01031  -0.0033   1.0000   0.0925
  -7.000  -0.7726   0.01776   0.00961  -0.0018   1.0000   0.1005
  -6.750  -0.7535   0.01712   0.00900  -0.0003   1.0000   0.1104
  -6.500  -0.7351   0.01641   0.00837   0.0013   1.0000   0.1222
  -6.250  -0.7162   0.01577   0.00781   0.0028   1.0000   0.1373
  -6.000  -0.6971   0.01517   0.00729   0.0043   1.0000   0.1563
  -5.750  -0.6785   0.01455   0.00683   0.0058   1.0000   0.1796
  -5.500  -0.6592   0.01400   0.00643   0.0073   1.0000   0.2077
  -5.250  -0.6396   0.01350   0.00609   0.0086   1.0000   0.2398
  -5.000  -0.6195   0.01306   0.00580   0.0099   1.0000   0.2743
  -4.750  -0.5990   0.01268   0.00556   0.0111   1.0000   0.3101
  -4.500  -0.5783   0.01234   0.00537   0.0123   1.0000   0.3456
  -4.250  -0.5572   0.01203   0.00521   0.0134   1.0000   0.3809
  -4.000  -0.5358   0.01176   0.00508   0.0145   1.0000   0.4160
  -3.750  -0.5139   0.01154   0.00498   0.0155   1.0000   0.4509
  -3.500  -0.4915   0.01134   0.00492   0.0164   1.0000   0.4856
  -3.250  -0.4689   0.01118   0.00489   0.0172   1.0000   0.5202
  -3.000  -0.4463   0.01104   0.00489   0.0180   1.0000   0.5545
  -2.750  -0.4236   0.01094   0.00493   0.0188   1.0000   0.5885
  -2.500  -0.3942   0.01086   0.00497   0.0183   0.9979   0.6248
  -2.250  -0.3513   0.01075   0.00504   0.0152   0.9915   0.6638
  -2.000  -0.3085   0.01066   0.00509   0.0122   0.9843   0.7011
  -1.750  -0.2684   0.01056   0.00512   0.0100   0.9755   0.7357
  -1.500  -0.2255   0.01048   0.00517   0.0072   0.9686   0.7684
  -1.250  -0.1861   0.01040   0.00519   0.0054   0.9593   0.7978
  -1.000  -0.1454   0.01034   0.00519   0.0033   0.9509   0.8255
  -0.750  -0.1048   0.01028   0.00521   0.0015   0.9424   0.8482
  -0.500  -0.0700   0.01025   0.00522   0.0009   0.9304   0.8696
  -0.250  -0.0350   0.01022   0.00521   0.0004   0.9182   0.8886
   0.000   0.0000   0.01020   0.00520   0.0000   0.9046   0.9047
   0.250   0.0350   0.01022   0.00521  -0.0004   0.8886   0.9182
   0.500   0.0700   0.01025   0.00522  -0.0009   0.8696   0.9304
   0.750   0.1048   0.01028   0.00521  -0.0015   0.8482   0.9424
   1.000   0.1454   0.01034   0.00519  -0.0033   0.8255   0.9510
   1.250   0.1861   0.01040   0.00518  -0.0054   0.7978   0.9593
   1.500   0.2255   0.01048   0.00517  -0.0072   0.7684   0.9686
   1.750   0.2684   0.01056   0.00512  -0.0100   0.7357   0.9756
   2.000   0.3085   0.01066   0.00509  -0.0122   0.7012   0.9843
   2.250   0.3513   0.01075   0.00504  -0.0152   0.6637   0.9915
   2.500   0.3942   0.01085   0.00497  -0.0183   0.6249   0.9979
   2.750   0.4235   0.01094   0.00492  -0.0188   0.5886   1.0000
   3.000   0.4462   0.01104   0.00489  -0.0180   0.5545   1.0000
   3.250   0.4689   0.01118   0.00489  -0.0172   0.5202   1.0000
   3.500   0.4915   0.01134   0.00492  -0.0163   0.4857   1.0000
   3.750   0.5138   0.01153   0.00498  -0.0155   0.4509   1.0000
   4.000   0.5357   0.01176   0.00507  -0.0145   0.4160   1.0000
   4.250   0.5571   0.01203   0.00521  -0.0134   0.3810   1.0000
   4.500   0.5782   0.01234   0.00536  -0.0123   0.3456   1.0000
   4.750   0.5990   0.01268   0.00556  -0.0111   0.3101   1.0000
   5.000   0.6195   0.01306   0.00580  -0.0099   0.2744   1.0000
   5.250   0.6395   0.01350   0.00609  -0.0086   0.2398   1.0000
   5.500   0.6591   0.01400   0.00643  -0.0072   0.2077   1.0000
   5.750   0.6784   0.01455   0.00683  -0.0058   0.1796   1.0000
   6.000   0.6971   0.01516   0.00729  -0.0043   0.1563   1.0000
   6.250   0.7161   0.01577   0.00781  -0.0028   0.1374   1.0000
   6.500   0.7351   0.01641   0.00837  -0.0013   0.1223   1.0000
   6.750   0.7535   0.01712   0.00900   0.0003   0.1104   1.0000
   7.000   0.7725   0.01776   0.00961   0.0018   0.1005   1.0000
   7.250   0.7919   0.01844   0.01031   0.0033   0.0925   1.0000
   7.500   0.8096   0.01936   0.01114   0.0049   0.0858   1.0000
   7.750   0.8300   0.01995   0.01181   0.0062   0.0799   1.0000
   8.000   0.8481   0.02112   0.01285   0.0077   0.0749   1.0000
   8.250   0.8690   0.02173   0.01362   0.0089   0.0707   1.0000
   8.500   0.8890   0.02251   0.01438   0.0101   0.0667   1.0000
   8.750   0.9087   0.02387   0.01574   0.0112   0.0635   1.0000
   9.000   0.9291   0.02472   0.01674   0.0124   0.0604   1.0000
   9.250   0.9492   0.02559   0.01762   0.0135   0.0575   1.0000
   9.500   0.9693   0.02734   0.01932   0.0143   0.0550   1.0000
   9.750   0.9882   0.02844   0.02068   0.0156   0.0532   1.0000
  10.000   1.0067   0.02966   0.02206   0.0168   0.0511   1.0000
  10.250   1.0251   0.03077   0.02323   0.0179   0.0492   1.0000
  10.500   1.0445   0.03262   0.02503   0.0185   0.0474   1.0000
  10.750   1.0571   0.03445   0.02718   0.0203   0.0462   1.0000
  11.000   1.0681   0.03636   0.02942   0.0222   0.0451   1.0000
  11.250   1.0773   0.03842   0.03177   0.0241   0.0441   1.0000
  11.500   1.0860   0.04035   0.03390   0.0258   0.0430   1.0000
  11.750   1.0969   0.04194   0.03558   0.0272   0.0419   1.0000
  12.000   1.1068   0.04366   0.03735   0.0286   0.0410   1.0000
  12.250   1.1101   0.04727   0.04108   0.0298   0.0401   1.0000
  12.500   1.0959   0.04960   0.04372   0.0334   0.0399   1.0000
  12.750   1.0790   0.05258   0.04700   0.0360   0.0397   1.0000
  13.000   1.0599   0.05626   0.05095   0.0372   0.0396   1.0000
  13.250   1.0385   0.06069   0.05564   0.0369   0.0396   1.0000
  13.500   1.0150   0.06603   0.06120   0.0352   0.0396   1.0000
  13.750   0.9898   0.07237   0.06774   0.0319   0.0398   1.0000
  14.000   0.9632   0.07976   0.07532   0.0275   0.0399   1.0000
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