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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 200,000
Max Cl/Cd: 47.58 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001234-il-200000.txt
Download as CSV file: xf-naca001234-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-34                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4678   0.11468   0.11123  -0.0286   1.0000   0.0538
 -12.000  -0.4784   0.10942   0.10601  -0.0313   1.0000   0.0558
 -11.750  -0.6288   0.10691   0.10338  -0.0279   1.0000   0.0476
 -11.500  -0.6235   0.10455   0.10103  -0.0270   1.0000   0.0489
 -11.250  -0.6264   0.09969   0.09618  -0.0291   1.0000   0.0501
 -11.000  -0.6381   0.09188   0.08841  -0.0346   1.0000   0.0507
 -10.750  -0.6685   0.08181   0.07828  -0.0430   1.0000   0.0498
 -10.500  -0.6967   0.07567   0.07203  -0.0461   1.0000   0.0495
 -10.250  -0.7190   0.07143   0.06770  -0.0462   1.0000   0.0496
 -10.000  -0.7377   0.06813   0.06430  -0.0444   1.0000   0.0500
  -9.750  -0.7560   0.06543   0.06152  -0.0411   1.0000   0.0505
  -9.500  -0.7712   0.06285   0.05884  -0.0374   1.0000   0.0514
  -9.250  -0.7841   0.06027   0.05612  -0.0335   1.0000   0.0527
  -9.000  -0.7970   0.05793   0.05358  -0.0290   1.0000   0.0547
  -7.000  -0.8047   0.03346   0.02620   0.0082   1.0000   0.0349
  -6.750  -0.7855   0.03006   0.02263   0.0099   1.0000   0.0325
  -6.500  -0.7678   0.02752   0.01979   0.0120   1.0000   0.0317
  -6.250  -0.7479   0.02554   0.01754   0.0137   1.0000   0.0317
  -6.000  -0.7271   0.02394   0.01576   0.0153   1.0000   0.0322
  -5.750  -0.7080   0.02306   0.01472   0.0170   1.0000   0.0336
  -5.500  -0.6879   0.02120   0.01279   0.0184   1.0000   0.0358
  -5.250  -0.6712   0.01992   0.01152   0.0203   1.0000   0.0376
  -5.000  -0.6556   0.01900   0.01058   0.0224   1.0000   0.0399
  -4.750  -0.6399   0.01822   0.00973   0.0246   1.0000   0.0429
  -4.500  -0.6248   0.01740   0.00886   0.0267   1.0000   0.0481
  -4.250  -0.6085   0.01670   0.00811   0.0285   1.0000   0.0563
  -4.000  -0.5923   0.01573   0.00726   0.0305   1.0000   0.0845
  -3.750  -0.5916   0.01256   0.00638   0.0340   1.0000   0.4942
  -3.500  -0.5652   0.01188   0.00646   0.0343   0.9969   0.6595
  -3.250  -0.5327   0.01191   0.00676   0.0338   0.9935   0.7474
  -3.000  -0.5028   0.01217   0.00716   0.0341   0.9887   0.8056
  -2.750  -0.4701   0.01267   0.00767   0.0340   0.9845   0.8454
  -2.500  -0.4370   0.01306   0.00798   0.0334   0.9800   0.8655
  -2.250  -0.4027   0.01332   0.00815   0.0323   0.9748   0.8791
  -2.000  -0.3631   0.01365   0.00839   0.0300   0.9711   0.8910
  -1.750  -0.3274   0.01392   0.00857   0.0284   0.9663   0.9022
  -1.500  -0.2911   0.01414   0.00870   0.0267   0.9609   0.9125
  -1.250  -0.2435   0.01443   0.00891   0.0226   0.9581   0.9178
  -1.000  -0.1944   0.01466   0.00907   0.0181   0.9558   0.9237
  -0.750  -0.1563   0.01480   0.00916   0.0158   0.9495   0.9303
  -0.500  -0.1042   0.01495   0.00927   0.0106   0.9465   0.9335
  -0.250  -0.0510   0.01502   0.00931   0.0051   0.9440   0.9371
   0.000   0.0000   0.01499   0.00927   0.0000   0.9418   0.9418
   0.250   0.0511   0.01502   0.00931  -0.0051   0.9371   0.9440
   0.500   0.1042   0.01495   0.00927  -0.0106   0.9335   0.9465
   0.750   0.1563   0.01480   0.00916  -0.0158   0.9303   0.9495
   1.000   0.1945   0.01466   0.00907  -0.0181   0.9237   0.9559
   1.250   0.2435   0.01443   0.00891  -0.0226   0.9178   0.9581
   1.500   0.2910   0.01414   0.00869  -0.0267   0.9125   0.9609
   1.750   0.3274   0.01392   0.00857  -0.0284   0.9022   0.9663
   2.000   0.3631   0.01365   0.00838  -0.0300   0.8911   0.9711
   2.250   0.4027   0.01332   0.00815  -0.0323   0.8791   0.9748
   2.500   0.4370   0.01305   0.00797  -0.0334   0.8655   0.9800
   2.750   0.4702   0.01267   0.00767  -0.0340   0.8455   0.9846
   3.000   0.5028   0.01217   0.00716  -0.0341   0.8056   0.9887
   3.250   0.5327   0.01190   0.00675  -0.0338   0.7471   0.9936
   3.500   0.5652   0.01188   0.00646  -0.0343   0.6596   0.9969
   3.750   0.5915   0.01255   0.00638  -0.0340   0.4945   1.0000
   4.000   0.5923   0.01571   0.00725  -0.0305   0.0853   1.0000
   4.250   0.6083   0.01669   0.00811  -0.0285   0.0563   1.0000
   4.500   0.6247   0.01739   0.00885  -0.0267   0.0482   1.0000
   4.750   0.6398   0.01821   0.00972  -0.0246   0.0430   1.0000
   5.000   0.6555   0.01899   0.01057  -0.0224   0.0400   1.0000
   5.250   0.6711   0.01991   0.01151  -0.0203   0.0377   1.0000
   5.500   0.6877   0.02119   0.01278  -0.0184   0.0359   1.0000
   5.750   0.7079   0.02304   0.01470  -0.0170   0.0336   1.0000
   6.000   0.7270   0.02394   0.01576  -0.0153   0.0322   1.0000
   6.250   0.7477   0.02553   0.01753  -0.0137   0.0317   1.0000
   6.500   0.7677   0.02750   0.01978  -0.0120   0.0318   1.0000
   6.750   0.7854   0.03005   0.02262  -0.0099   0.0325   1.0000
   7.000   0.8046   0.03346   0.02620  -0.0082   0.0349   1.0000
  12.000   0.4781   0.10924   0.10583   0.0313   0.0558   1.0000
  12.250   0.4673   0.11450   0.11105   0.0286   0.0538   1.0000
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