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NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-012 (naca16012-il)
Reynolds number: 100,000
Max Cl/Cd: 30.81 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16012-il-100000-n5.txt
Download as CSV file: xf-naca16012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-012                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6483   0.08781   0.08263  -0.0524   1.0000   0.0227
 -11.500  -0.6695   0.08196   0.07673  -0.0545   1.0000   0.0225
 -11.250  -0.6923   0.07712   0.07183  -0.0548   1.0000   0.0224
 -11.000  -0.7161   0.07307   0.06769  -0.0535   1.0000   0.0223
 -10.750  -0.7402   0.06962   0.06414  -0.0506   1.0000   0.0222
 -10.500  -0.7643   0.06668   0.06108  -0.0465   1.0000   0.0221
 -10.250  -0.7887   0.06418   0.05846  -0.0411   1.0000   0.0221
 -10.000  -0.8132   0.06208   0.05623  -0.0347   1.0000   0.0221
  -9.750  -0.8361   0.05990   0.05390  -0.0279   1.0000   0.0221
  -9.500  -0.8546   0.05721   0.05099  -0.0218   1.0000   0.0221
  -9.250  -0.8701   0.05441   0.04792  -0.0157   1.0000   0.0222
  -9.000  -0.8824   0.05154   0.04473  -0.0099   1.0000   0.0223
  -8.750  -0.8911   0.04867   0.04147  -0.0043   1.0000   0.0225
  -8.500  -0.8957   0.04591   0.03829   0.0009   1.0000   0.0228
  -8.250  -0.8968   0.04301   0.03509   0.0053   1.0000   0.0234
  -8.000  -0.8919   0.04127   0.03322   0.0085   1.0000   0.0245
  -7.750  -0.8844   0.03986   0.03162   0.0116   1.0000   0.0259
  -7.500  -0.8750   0.03803   0.02946   0.0147   1.0000   0.0274
  -7.250  -0.8626   0.03579   0.02680   0.0175   1.0000   0.0287
  -7.000  -0.8462   0.03364   0.02423   0.0198   1.0000   0.0303
  -6.750  -0.8282   0.03207   0.02226   0.0218   1.0000   0.0328
  -6.500  -0.8104   0.03051   0.02066   0.0231   1.0000   0.0355
  -6.250  -0.7905   0.02920   0.01919   0.0245   1.0000   0.0382
  -6.000  -0.7706   0.02818   0.01793   0.0260   1.0000   0.0422
  -5.750  -0.7515   0.02688   0.01659   0.0273   1.0000   0.0461
  -5.500  -0.7336   0.02597   0.01560   0.0290   1.0000   0.0500
  -5.250  -0.7156   0.02533   0.01477   0.0308   1.0000   0.0552
  -5.000  -0.7002   0.02434   0.01381   0.0328   1.0000   0.0594
  -4.750  -0.6820   0.02371   0.01311   0.0344   0.9996   0.0654
  -4.500  -0.6577   0.02299   0.01233   0.0347   0.9975   0.0726
  -4.250  -0.6324   0.02239   0.01161   0.0348   0.9953   0.0809
  -4.000  -0.6077   0.02175   0.01098   0.0350   0.9930   0.0948
  -3.750  -0.5840   0.02105   0.01045   0.0353   0.9905   0.1282
  -3.500  -0.5636   0.01987   0.01000   0.0360   0.9883   0.2548
  -3.250  -0.5520   0.01792   0.00970   0.0387   0.9867   0.5632
  -3.000  -0.4865   0.01903   0.01168   0.0338   0.9906   0.8188
  -2.750  -0.4508   0.02034   0.01288   0.0339   0.9895   0.8789
  -2.500  -0.3719   0.02300   0.01530   0.0264   0.9949   0.9239
  -2.250  -0.3225   0.02364   0.01575   0.0221   0.9952   0.9378
  -2.000  -0.2801   0.02373   0.01566   0.0185   0.9940   0.9420
  -1.750  -0.2449   0.02377   0.01557   0.0163   0.9919   0.9476
  -1.500  -0.2113   0.02379   0.01547   0.0143   0.9895   0.9529
  -1.250  -0.1726   0.02380   0.01539   0.0112   0.9876   0.9562
  -1.000  -0.1369   0.02383   0.01534   0.0087   0.9856   0.9604
  -0.750  -0.1069   0.02381   0.01526   0.0075   0.9823   0.9649
  -0.500  -0.0696   0.02379   0.01520   0.0046   0.9796   0.9675
  -0.250  -0.0330   0.02380   0.01518   0.0019   0.9773   0.9707
   0.000   0.0000   0.02382   0.01519   0.0000   0.9744   0.9744
   0.250   0.0330   0.02380   0.01518  -0.0019   0.9707   0.9773
   0.500   0.0695   0.02378   0.01520  -0.0046   0.9675   0.9796
   0.750   0.1068   0.02381   0.01526  -0.0074   0.9650   0.9823
   1.000   0.1369   0.02383   0.01534  -0.0087   0.9605   0.9856
   1.250   0.1726   0.02379   0.01538  -0.0112   0.9562   0.9876
   1.500   0.2113   0.02378   0.01546  -0.0143   0.9529   0.9895
   1.750   0.2450   0.02376   0.01556  -0.0163   0.9477   0.9919
   2.000   0.2801   0.02373   0.01566  -0.0185   0.9420   0.9940
   2.250   0.3225   0.02363   0.01574  -0.0221   0.9379   0.9952
   2.500   0.3720   0.02299   0.01529  -0.0265   0.9239   0.9949
   2.750   0.4509   0.02033   0.01288  -0.0339   0.8790   0.9896
   3.000   0.4866   0.01902   0.01167  -0.0338   0.8186   0.9906
   3.250   0.5521   0.01792   0.00970  -0.0387   0.5633   0.9867
   3.500   0.5637   0.01986   0.01000  -0.0360   0.2554   0.9884
   3.750   0.5840   0.02104   0.01045  -0.0353   0.1282   0.9905
   4.000   0.6078   0.02175   0.01097  -0.0350   0.0949   0.9930
   4.250   0.6324   0.02239   0.01161  -0.0348   0.0809   0.9954
   4.500   0.6577   0.02298   0.01232  -0.0347   0.0726   0.9975
   4.750   0.6821   0.02370   0.01310  -0.0344   0.0654   0.9996
   5.000   0.7001   0.02434   0.01380  -0.0328   0.0594   1.0000
   5.250   0.7154   0.02532   0.01476  -0.0307   0.0553   1.0000
   5.500   0.7335   0.02596   0.01559  -0.0290   0.0500   1.0000
   5.750   0.7514   0.02687   0.01658  -0.0273   0.0461   1.0000
   6.000   0.7705   0.02817   0.01792  -0.0260   0.0422   1.0000
   6.250   0.7904   0.02919   0.01918  -0.0245   0.0382   1.0000
   6.500   0.8103   0.03050   0.02065  -0.0231   0.0355   1.0000
   6.750   0.8281   0.03204   0.02223  -0.0217   0.0328   1.0000
   7.000   0.8461   0.03363   0.02422  -0.0198   0.0303   1.0000
   7.250   0.8625   0.03578   0.02679  -0.0175   0.0287   1.0000
   7.500   0.8749   0.03803   0.02945  -0.0146   0.0274   1.0000
   7.750   0.8844   0.03984   0.03160  -0.0116   0.0259   1.0000
   8.000   0.8918   0.04128   0.03322  -0.0085   0.0245   1.0000
   8.250   0.8968   0.04299   0.03507  -0.0052   0.0234   1.0000
   8.500   0.8956   0.04590   0.03827  -0.0009   0.0228   1.0000
   8.750   0.8910   0.04866   0.04146   0.0043   0.0225   1.0000
   9.000   0.8825   0.05153   0.04471   0.0099   0.0223   1.0000
   9.250   0.8702   0.05440   0.04791   0.0157   0.0222   1.0000
   9.500   0.8547   0.05720   0.05098   0.0218   0.0221   1.0000
   9.750   0.8362   0.05989   0.05389   0.0279   0.0221   1.0000
  10.000   0.8134   0.06208   0.05623   0.0346   0.0221   1.0000
  10.250   0.7887   0.06419   0.05847   0.0411   0.0221   1.0000
  10.500   0.7645   0.06669   0.06108   0.0464   0.0221   1.0000
  10.750   0.7404   0.06962   0.06414   0.0506   0.0222   1.0000
  11.000   0.7164   0.07306   0.06768   0.0534   0.0223   1.0000
  11.250   0.6927   0.07712   0.07183   0.0548   0.0224   1.0000
  11.500   0.6698   0.08198   0.07675   0.0545   0.0225   1.0000
  11.750   0.6486   0.08787   0.08269   0.0523   0.0227   1.0000
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