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NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-412 (naca651412-il)
Reynolds number: 200,000
Max Cl/Cd: 74.87 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651412-il-200000.txt
Download as CSV file: xf-naca651412-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-412                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4253   0.08907   0.08554  -0.0515   1.0000   0.0529
  -9.500  -0.4361   0.08422   0.08077  -0.0545   1.0000   0.0541
  -9.250  -0.4572   0.07845   0.07507  -0.0589   1.0000   0.0548
  -9.000  -0.4766   0.07540   0.07210  -0.0580   1.0000   0.0544
  -8.750  -0.5048   0.07399   0.07077  -0.0538   1.0000   0.0538
  -8.500  -0.5373   0.07341   0.07028  -0.0481   1.0000   0.0526
  -8.250  -0.5424   0.06711   0.06375  -0.0562   0.9923   0.0545
  -8.000  -0.5460   0.05979   0.05574  -0.0647   0.9809   0.0573
  -7.750  -0.5200   0.05600   0.05223  -0.0660   0.9781   0.0600
  -7.500  -0.4972   0.05249   0.04857  -0.0693   0.9730   0.0639
  -7.250  -0.4856   0.04793   0.04331  -0.0725   0.9638   0.0711
  -7.000  -0.4584   0.04436   0.03984  -0.0748   0.9602   0.0740
  -6.750  -0.4302   0.04124   0.03613  -0.0783   0.9564   0.0853
  -6.500  -0.4086   0.03836   0.03334  -0.0788   0.9496   0.0889
  -6.250  -0.3801   0.03575   0.03047  -0.0812   0.9452   0.1022
  -6.000  -0.3385   0.02790   0.02125  -0.0809   0.9428   0.0532
  -5.750  -0.3078   0.02440   0.01719  -0.0812   0.9385   0.0480
  -5.500  -0.2786   0.02266   0.01519  -0.0815   0.9327   0.0482
  -5.250  -0.2433   0.02128   0.01368  -0.0831   0.9295   0.0504
  -5.000  -0.2064   0.01978   0.01201  -0.0846   0.9270   0.0511
  -4.750  -0.1816   0.01882   0.01098  -0.0840   0.9199   0.0523
  -4.500  -0.1505   0.01794   0.01002  -0.0845   0.9153   0.0547
  -4.250  -0.1185   0.01685   0.00890  -0.0854   0.9120   0.0582
  -4.000  -0.0973   0.01612   0.00822  -0.0844   0.9041   0.0615
  -3.750  -0.0684   0.01546   0.00754  -0.0848   0.8992   0.0665
  -3.500  -0.0406   0.01480   0.00686  -0.0850   0.8945   0.0760
  -3.250  -0.0173   0.01426   0.00635  -0.0845   0.8872   0.0960
  -3.000  -0.0015   0.01177   0.00606  -0.0836   0.8823   0.6206
  -2.750   0.0208   0.01198   0.00634  -0.0819   0.8754   0.6804
  -2.500   0.0464   0.01217   0.00653  -0.0808   0.8701   0.7127
  -2.250   0.0706   0.01253   0.00692  -0.0787   0.8665   0.7476
  -2.000   0.0864   0.01306   0.00753  -0.0751   0.8590   0.7756
  -1.750   0.1081   0.01334   0.00780  -0.0727   0.8542   0.7945
  -1.500   0.1336   0.01341   0.00781  -0.0717   0.8499   0.8053
  -1.250   0.1579   0.01344   0.00779  -0.0712   0.8433   0.8119
  -1.000   0.1867   0.01336   0.00764  -0.0715   0.8390   0.8178
  -0.750   0.2136   0.01334   0.00757  -0.0712   0.8347   0.8230
  -0.500   0.2396   0.01337   0.00756  -0.0713   0.8283   0.8303
  -0.250   0.2662   0.01333   0.00749  -0.0708   0.8242   0.8349
   0.000   0.2939   0.01332   0.00745  -0.0708   0.8202   0.8410
   0.250   0.3180   0.01340   0.00753  -0.0704   0.8138   0.8474
   0.500   0.3446   0.01338   0.00750  -0.0701   0.8096   0.8531
   1.000   0.3948   0.01349   0.00764  -0.0693   0.7994   0.8660
   1.250   0.4222   0.01349   0.00764  -0.0693   0.7951   0.8733
   1.500   0.4497   0.01346   0.00761  -0.0690   0.7919   0.8793
   1.750   0.4708   0.01364   0.00787  -0.0681   0.7852   0.8874
   2.000   0.4957   0.01364   0.00791  -0.0674   0.7807   0.8944
   2.250   0.5237   0.01362   0.00790  -0.0673   0.7774   0.9025
   2.500   0.5428   0.01377   0.00814  -0.0658   0.7705   0.9110
   2.750   0.5686   0.01373   0.00816  -0.0654   0.7655   0.9200
   3.000   0.5951   0.01363   0.00809  -0.0648   0.7612   0.9289
   3.250   0.6155   0.01368   0.00826  -0.0635   0.7534   0.9399
   3.500   0.6469   0.01342   0.00802  -0.0638   0.7479   0.9490
   3.750   0.6745   0.01317   0.00785  -0.0635   0.7364   0.9599
   4.000   0.7114   0.01250   0.00717  -0.0643   0.7196   0.9676
   4.250   0.7468   0.01180   0.00643  -0.0648   0.6921   0.9764
   4.500   0.7840   0.01146   0.00614  -0.0664   0.6673   0.9856
   4.750   0.8222   0.01126   0.00596  -0.0684   0.6373   0.9957
   5.000   0.8393   0.01121   0.00587  -0.0665   0.6017   1.0000
   5.250   0.8502   0.01141   0.00580  -0.0634   0.5177   1.0000
   5.500   0.8384   0.01351   0.00651  -0.0573   0.2827   1.0000
   5.750   0.8285   0.01635   0.00806  -0.0525   0.0877   1.0000
   6.000   0.8418   0.01757   0.00912  -0.0506   0.0654   1.0000
   6.250   0.8576   0.01853   0.01007  -0.0491   0.0570   1.0000
   6.500   0.8699   0.01960   0.01118  -0.0469   0.0528   1.0000
   6.750   0.8852   0.02054   0.01217  -0.0452   0.0491   1.0000
   7.000   0.8996   0.02167   0.01326  -0.0435   0.0455   1.0000
   7.250   0.9165   0.02324   0.01481  -0.0422   0.0431   1.0000
   7.500   0.9403   0.02440   0.01604  -0.0417   0.0416   1.0000
   7.750   0.9691   0.02581   0.01751  -0.0420   0.0401   1.0000
   8.000   1.0037   0.02756   0.01936  -0.0433   0.0389   1.0000
   8.250   1.0336   0.02918   0.02106  -0.0438   0.0374   1.0000
   8.500   1.0621   0.03099   0.02292  -0.0444   0.0357   1.0000
   8.750   1.0935   0.03356   0.02565  -0.0452   0.0352   1.0000
   9.000   1.1201   0.03618   0.02857  -0.0451   0.0353   1.0000
   9.250   1.1396   0.04014   0.03323  -0.0432   0.0378   1.0000
   9.500   1.1535   0.04584   0.03944  -0.0415   0.0417   1.0000
  13.000   0.7063   0.13445   0.13161  -0.0444   0.0740   1.0000
  13.250   0.7034   0.13834   0.13551  -0.0465   0.0714   1.0000
  13.500   0.7097   0.14085   0.13805  -0.0469   0.0694   1.0000
  13.750   0.8650   0.15209   0.14887  -0.0572   0.0587   1.0000
  14.000   0.8734   0.15510   0.15190  -0.0578   0.0570   1.0000
  14.250   0.8905   0.15599   0.15284  -0.0554   0.0556   1.0000
  14.500   0.6889   0.15948   0.15668  -0.0587   0.0601   1.0000
  14.750   0.6980   0.16170   0.15891  -0.0591   0.0572   1.0000
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