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NACA 23015 (naca23015-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 23015 (naca23015-il)
Reynolds number: 50,000
Max Cl/Cd: 27.17 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca23015-il-50000-n5.txt
Download as CSV file: xf-naca23015-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23015                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6514   0.09556   0.08743  -0.0353   1.0000   0.0775
 -12.250  -0.6838   0.08686   0.07864  -0.0408   1.0000   0.0771
 -12.000  -0.7167   0.07977   0.07142  -0.0445   1.0000   0.0768
 -11.750  -0.7479   0.07420   0.06567  -0.0459   1.0000   0.0767
 -11.500  -0.7769   0.06984   0.06110  -0.0451   1.0000   0.0767
 -11.250  -0.8031   0.06634   0.05738  -0.0424   1.0000   0.0769
 -11.000  -0.8242   0.06294   0.05366  -0.0395   1.0000   0.0774
 -10.750  -0.8220   0.06024   0.05088  -0.0379   1.0000   0.0786
 -10.500  -0.8160   0.05788   0.04845  -0.0363   1.0000   0.0799
 -10.250  -0.8141   0.05536   0.04575  -0.0342   1.0000   0.0810
 -10.000  -0.8114   0.05294   0.04310  -0.0319   1.0000   0.0825
  -9.750  -0.8084   0.05057   0.04045  -0.0295   1.0000   0.0842
  -9.500  -0.8045   0.04825   0.03777  -0.0268   1.0000   0.0860
  -9.250  -0.7987   0.04602   0.03512  -0.0242   1.0000   0.0875
  -9.000  -0.7840   0.04402   0.03302  -0.0226   1.0000   0.0892
  -8.750  -0.7677   0.04240   0.03137  -0.0212   1.0000   0.0914
  -8.500  -0.7519   0.04084   0.02968  -0.0195   1.0000   0.0939
  -8.250  -0.7356   0.03926   0.02789  -0.0178   1.0000   0.0963
  -8.000  -0.7184   0.03779   0.02615  -0.0160   1.0000   0.0986
  -7.750  -0.6983   0.03638   0.02473  -0.0149   1.0000   0.1013
  -7.500  -0.6783   0.03519   0.02356  -0.0136   1.0000   0.1044
  -7.250  -0.6578   0.03407   0.02237  -0.0123   1.0000   0.1075
  -7.000  -0.6374   0.03307   0.02123  -0.0108   1.0000   0.1109
  -6.750  -0.6174   0.03206   0.02027  -0.0095   1.0000   0.1146
  -6.500  -0.5992   0.03116   0.01942  -0.0078   1.0000   0.1186
  -6.250  -0.5815   0.03037   0.01858  -0.0060   1.0000   0.1229
  -6.000  -0.5651   0.02962   0.01780  -0.0041   1.0000   0.1277
  -5.750  -0.5512   0.02882   0.01708  -0.0019   1.0000   0.1333
  -5.500  -0.5369   0.02815   0.01636   0.0002   1.0000   0.1400
  -5.250  -0.5240   0.02737   0.01566   0.0025   1.0000   0.1473
  -5.000  -0.5108   0.02668   0.01501   0.0046   1.0000   0.1585
  -4.750  -0.4983   0.02584   0.01434   0.0066   1.0000   0.1751
  -4.500  -0.4865   0.02478   0.01369   0.0086   1.0000   0.2113
  -4.250  -0.4775   0.02354   0.01334   0.0109   1.0000   0.3329
  -4.000  -0.4551   0.02295   0.01333   0.0115   0.9946   0.4589
  -3.750  -0.4186   0.02276   0.01345   0.0101   0.9834   0.5459
  -3.500  -0.3824   0.02279   0.01371   0.0091   0.9716   0.6135
  -3.250  -0.3471   0.02299   0.01410   0.0088   0.9594   0.6753
  -3.000  -0.3123   0.02345   0.01472   0.0094   0.9471   0.7355
  -2.750  -0.2700   0.02393   0.01520   0.0084   0.9360   0.7748
  -2.500  -0.2233   0.02409   0.01526   0.0056   0.9241   0.7956
  -2.250  -0.1793   0.02412   0.01517   0.0030   0.9104   0.8134
  -2.000  -0.1339   0.02413   0.01506   0.0002   0.8969   0.8307
  -1.750  -0.0821   0.02413   0.01494  -0.0035   0.8841   0.8452
  -1.500  -0.0330   0.02407   0.01478  -0.0067   0.8693   0.8592
  -1.250   0.0115   0.02398   0.01459  -0.0092   0.8522   0.8737
  -1.000   0.0546   0.02385   0.01436  -0.0114   0.8341   0.8883
  -0.750   0.1002   0.02370   0.01410  -0.0141   0.8150   0.9013
  -0.500   0.1492   0.02349   0.01377  -0.0173   0.7940   0.9123
  -0.250   0.1894   0.02332   0.01349  -0.0191   0.7688   0.9255
   0.000   0.2282   0.02314   0.01317  -0.0206   0.7431   0.9390
   0.250   0.2725   0.02293   0.01280  -0.0231   0.7161   0.9498
   0.500   0.3123   0.02280   0.01254  -0.0252   0.6877   0.9617
   0.750   0.3521   0.02268   0.01224  -0.0273   0.6605   0.9735
   1.000   0.3921   0.02260   0.01203  -0.0297   0.6313   0.9850
   1.250   0.4331   0.02251   0.01177  -0.0323   0.6034   0.9957
   1.500   0.4607   0.02252   0.01165  -0.0327   0.5771   1.0000
   1.750   0.4787   0.02259   0.01157  -0.0311   0.5544   1.0000
   2.000   0.4972   0.02270   0.01153  -0.0296   0.5330   1.0000
   2.250   0.5158   0.02286   0.01155  -0.0282   0.5123   1.0000
   2.500   0.5341   0.02308   0.01165  -0.0267   0.4916   1.0000
   2.750   0.5525   0.02332   0.01179  -0.0252   0.4723   1.0000
   3.000   0.5711   0.02361   0.01196  -0.0238   0.4545   1.0000
   3.250   0.5899   0.02393   0.01216  -0.0223   0.4379   1.0000
   3.500   0.6084   0.02428   0.01244  -0.0208   0.4219   1.0000
   3.750   0.6270   0.02467   0.01278  -0.0194   0.4069   1.0000
   4.000   0.6459   0.02510   0.01314  -0.0180   0.3935   1.0000
   4.250   0.6652   0.02553   0.01347  -0.0166   0.3817   1.0000
   4.500   0.6841   0.02601   0.01392  -0.0152   0.3698   1.0000
   4.750   0.7032   0.02653   0.01441  -0.0138   0.3593   1.0000
   5.000   0.7230   0.02704   0.01486  -0.0125   0.3500   1.0000
   5.250   0.7419   0.02764   0.01549  -0.0112   0.3405   1.0000
   5.500   0.7619   0.02820   0.01598  -0.0099   0.3323   1.0000
   5.750   0.7807   0.02887   0.01670  -0.0086   0.3241   1.0000
   6.000   0.8002   0.02952   0.01736  -0.0073   0.3166   1.0000
   6.250   0.8204   0.03019   0.01799  -0.0062   0.3100   1.0000
   6.500   0.8378   0.03098   0.01892  -0.0047   0.3025   1.0000
   6.750   0.8583   0.03164   0.01953  -0.0036   0.2963   1.0000
   7.000   0.8758   0.03253   0.02053  -0.0022   0.2900   1.0000
   7.250   0.8932   0.03341   0.02150  -0.0008   0.2835   1.0000
   7.500   0.9149   0.03408   0.02211   0.0001   0.2780   1.0000
   7.750   0.9287   0.03520   0.02343   0.0018   0.2716   1.0000
   8.000   0.9454   0.03616   0.02449   0.0032   0.2655   1.0000
   8.250   0.9682   0.03681   0.02506   0.0039   0.2603   1.0000
   8.500   0.9771   0.03823   0.02676   0.0060   0.2540   1.0000
   8.750   0.9926   0.03925   0.02787   0.0074   0.2480   1.0000
   9.000   1.0156   0.03990   0.02844   0.0080   0.2429   1.0000
   9.250   1.0182   0.04167   0.03056   0.0106   0.2367   1.0000
   9.500   1.0318   0.04277   0.03175   0.0121   0.2309   1.0000
   9.750   1.0535   0.04348   0.03238   0.0128   0.2258   1.0000
  10.000   1.0481   0.04570   0.03497   0.0158   0.2201   1.0000
  10.250   1.0574   0.04699   0.03637   0.0175   0.2145   1.0000
  10.500   1.0802   0.04756   0.03684   0.0181   0.2094   1.0000
  10.750   1.0597   0.05060   0.04027   0.0218   0.2046   1.0000
  11.000   1.0501   0.05284   0.04268   0.0246   0.2000   1.0000
  11.250   1.0811   0.05273   0.04246   0.0248   0.1946   1.0000
  11.500   1.0492   0.05674   0.04673   0.0279   0.1913   1.0000
  11.750   0.9886   0.06441   0.05473   0.0285   0.1884   1.0000
  12.000   0.8454   0.08771   0.07826   0.0177   0.1827   1.0000
  12.250   0.9133   0.07976   0.07032   0.0235   0.1799   1.0000
  12.500   0.7734   0.10859   0.09917   0.0080   0.1683   1.0000
  12.750   0.7940   0.10842   0.09904   0.0092   0.1650   1.0000
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