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NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-015 (naca16015-il)
Reynolds number: 50,000
Max Cl/Cd: 21.71 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16015-il-50000-n5.txt
Download as CSV file: xf-naca16015-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-015                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6371   0.10993   0.10246  -0.0545   1.0000   0.0575
 -12.750  -0.6654   0.10178   0.09433  -0.0578   1.0000   0.0566
 -12.500  -0.6978   0.09470   0.08721  -0.0596   1.0000   0.0556
 -12.250  -0.7324   0.08873   0.08117  -0.0595   1.0000   0.0547
 -12.000  -0.7666   0.08385   0.07617  -0.0575   1.0000   0.0541
 -11.750  -0.7984   0.07984   0.07203  -0.0542   1.0000   0.0538
 -11.500  -0.8278   0.07650   0.06854  -0.0497   1.0000   0.0536
 -11.250  -0.8549   0.07367   0.06554  -0.0445   1.0000   0.0536
 -11.000  -0.8799   0.07123   0.06294  -0.0386   1.0000   0.0538
 -10.750  -0.9035   0.06911   0.06066  -0.0322   1.0000   0.0541
 -10.500  -0.9252   0.06714   0.05851  -0.0255   1.0000   0.0545
 -10.250  -0.9418   0.06490   0.05605  -0.0195   1.0000   0.0554
 -10.000  -0.9557   0.06257   0.05345  -0.0137   1.0000   0.0564
  -9.750  -0.9671   0.06012   0.05068  -0.0080   1.0000   0.0576
  -9.500  -0.9754   0.05759   0.04775  -0.0026   1.0000   0.0589
  -9.250  -0.9793   0.05499   0.04469   0.0024   1.0000   0.0601
  -9.000  -0.9789   0.05249   0.04166   0.0069   1.0000   0.0613
  -8.750  -0.9674   0.05037   0.03955   0.0089   1.0000   0.0638
  -8.500  -0.9575   0.04872   0.03769   0.0115   1.0000   0.0669
  -8.250  -0.9439   0.04675   0.03538   0.0138   1.0000   0.0700
  -8.000  -0.9246   0.04472   0.03287   0.0153   1.0000   0.0730
  -7.750  -0.9030   0.04301   0.03108   0.0159   1.0000   0.0773
  -7.500  -0.8790   0.04156   0.02947   0.0163   1.0000   0.0821
  -7.250  -0.8417   0.03998   0.02752   0.0147   1.0000   0.0872
  -7.000  -0.8091   0.03869   0.02628   0.0134   1.0000   0.0944
  -6.750  -0.7695   0.03759   0.02498   0.0112   1.0000   0.1032
  -6.500  -0.7337   0.03652   0.02386   0.0095   1.0000   0.1126
  -6.250  -0.7120   0.03557   0.02291   0.0104   1.0000   0.1241
  -6.000  -0.6969   0.03465   0.02200   0.0123   1.0000   0.1404
  -5.750  -0.6852   0.03367   0.02112   0.0149   1.0000   0.1622
  -5.500  -0.6779   0.03253   0.02025   0.0182   1.0000   0.1958
  -5.250  -0.6764   0.03118   0.01940   0.0224   1.0000   0.2611
  -5.000  -0.5834   0.03274   0.02350   0.0157   1.0000   0.7235
  -4.750  -0.5775   0.03344   0.02403   0.0211   1.0000   0.7734
  -4.500  -0.5463   0.03518   0.02548   0.0226   1.0000   0.8141
  -4.250  -0.5025   0.03714   0.02711   0.0216   1.0000   0.8506
  -4.000  -0.4340   0.03928   0.02887   0.0157   1.0000   0.8843
  -3.750  -0.3940   0.04000   0.02929   0.0135   1.0000   0.9060
  -3.500  -0.3560   0.04014   0.02920   0.0109   1.0000   0.9186
  -3.000  -0.2920   0.03996   0.02863   0.0074   1.0000   0.9381
  -2.750  -0.2647   0.03985   0.02835   0.0063   1.0000   0.9475
  -2.500  -0.2334   0.03964   0.02800   0.0045   1.0000   0.9548
  -2.250  -0.2075   0.03953   0.02776   0.0037   1.0000   0.9633
  -2.000  -0.1769   0.03932   0.02744   0.0018   1.0000   0.9699
  -1.750  -0.1487   0.03918   0.02720   0.0004   1.0000   0.9768
  -1.500  -0.1199   0.03905   0.02698  -0.0011   1.0000   0.9834
  -1.250  -0.0900   0.03888   0.02675  -0.0030   1.0000   0.9890
  -1.000  -0.0601   0.03881   0.02661  -0.0048   1.0000   0.9949
  -0.750  -0.0297   0.03871   0.02647  -0.0068   1.0000   1.0000
  -0.500  -0.0198   0.03865   0.02639  -0.0045   1.0000   1.0000
  -0.250  -0.0099   0.03861   0.02634  -0.0023   1.0000   1.0000
   0.000   0.0000   0.03859   0.02632   0.0000   1.0000   1.0000
   0.250   0.0099   0.03860   0.02633   0.0023   1.0000   1.0000
   0.500   0.0198   0.03864   0.02639   0.0045   1.0000   1.0000
   0.750   0.0297   0.03871   0.02647   0.0068   1.0000   1.0000
   1.000   0.0600   0.03880   0.02660   0.0048   0.9949   1.0000
   1.250   0.0899   0.03887   0.02674   0.0030   0.9891   1.0000
   1.500   0.1198   0.03904   0.02697   0.0012   0.9834   1.0000
   1.750   0.1486   0.03916   0.02718  -0.0004   0.9768   1.0000
   2.000   0.1768   0.03931   0.02743  -0.0018   0.9700   1.0000
   2.250   0.2074   0.03951   0.02774  -0.0036   0.9633   1.0000
   2.500   0.2333   0.03962   0.02797  -0.0044   0.9549   1.0000
   2.750   0.2647   0.03983   0.02833  -0.0063   0.9476   1.0000
   3.000   0.2919   0.03994   0.02860  -0.0073   0.9382   1.0000
   3.500   0.3561   0.04012   0.02918  -0.0109   0.9188   1.0000
   3.750   0.3936   0.03997   0.02927  -0.0134   0.9060   1.0000
   4.000   0.4339   0.03926   0.02884  -0.0157   0.8844   1.0000
   4.250   0.5022   0.03713   0.02709  -0.0215   0.8507   1.0000
   4.500   0.5464   0.03515   0.02546  -0.0226   0.8142   1.0000
   4.750   0.5776   0.03341   0.02400  -0.0211   0.7735   1.0000
   5.000   0.5835   0.03272   0.02348  -0.0157   0.7235   1.0000
   5.250   0.6765   0.03116   0.01939  -0.0225   0.2610   1.0000
   5.500   0.6780   0.03252   0.02023  -0.0182   0.1958   1.0000
   5.750   0.6853   0.03365   0.02110  -0.0149   0.1622   1.0000
   6.000   0.6970   0.03464   0.02199  -0.0123   0.1403   1.0000
   6.250   0.7122   0.03556   0.02289  -0.0104   0.1241   1.0000
   6.500   0.7339   0.03651   0.02385  -0.0096   0.1126   1.0000
   6.750   0.7696   0.03757   0.02496  -0.0113   0.1032   1.0000
   7.000   0.8092   0.03868   0.02626  -0.0134   0.0944   1.0000
   7.250   0.8417   0.03996   0.02750  -0.0147   0.0872   1.0000
   7.500   0.8790   0.04154   0.02945  -0.0163   0.0821   1.0000
   7.750   0.9029   0.04299   0.03106  -0.0159   0.0773   1.0000
   8.000   0.9245   0.04471   0.03285  -0.0153   0.0730   1.0000
   8.250   0.9438   0.04674   0.03537  -0.0138   0.0700   1.0000
   8.500   0.9574   0.04869   0.03766  -0.0115   0.0669   1.0000
   8.750   0.9674   0.05036   0.03954  -0.0089   0.0638   1.0000
   9.000   0.9789   0.05247   0.04164  -0.0069   0.0613   1.0000
   9.250   0.9793   0.05497   0.04467  -0.0024   0.0601   1.0000
   9.500   0.9754   0.05757   0.04774   0.0026   0.0589   1.0000
   9.750   0.9672   0.06011   0.05067   0.0080   0.0577   1.0000
  10.000   0.9558   0.06256   0.05344   0.0137   0.0565   1.0000
  10.250   0.9420   0.06490   0.05605   0.0195   0.0554   1.0000
  10.500   0.9254   0.06713   0.05850   0.0255   0.0546   1.0000
  10.750   0.9038   0.06911   0.06065   0.0322   0.0540   1.0000
  11.000   0.8802   0.07123   0.06293   0.0386   0.0537   1.0000
  11.250   0.8552   0.07365   0.06552   0.0445   0.0536   1.0000
  11.500   0.8281   0.07650   0.06853   0.0497   0.0536   1.0000
  11.750   0.7988   0.07982   0.07201   0.0542   0.0537   1.0000
  12.000   0.7670   0.08383   0.07615   0.0575   0.0541   1.0000
  12.250   0.7329   0.08870   0.08114   0.0594   0.0547   1.0000
  12.500   0.6982   0.09467   0.08719   0.0596   0.0556   1.0000
  12.750   0.6659   0.10176   0.09430   0.0578   0.0566   1.0000
  13.000   0.6377   0.10991   0.10244   0.0545   0.0575   1.0000
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