Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 16-015 (naca16015-il)
Reynolds number: 1,000,000
Max Cl/Cd: 50.48 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca16015-il-1000000.txt
Download as CSV file: xf-naca16015-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -0.9715   0.10446   0.10192  -0.0603   1.0000   0.0088
 -19.000  -1.0089   0.09381   0.09110  -0.0655   1.0000   0.0087
 -18.750  -1.0414   0.08462   0.08174  -0.0697   1.0000   0.0087
 -18.500  -1.0676   0.07711   0.07407  -0.0728   1.0000   0.0087
 -18.250  -1.0868   0.07127   0.06808  -0.0746   1.0000   0.0087
 -18.000  -1.1034   0.06630   0.06298  -0.0756   1.0000   0.0087
 -17.750  -1.1177   0.06205   0.05860  -0.0758   1.0000   0.0088
 -17.500  -1.1372   0.05754   0.05395  -0.0753   1.0000   0.0088
 -17.250  -1.1599   0.05312   0.04936  -0.0739   1.0000   0.0089
 -17.000  -1.1816   0.04923   0.04531  -0.0718   1.0000   0.0090
 -16.750  -1.1972   0.04622   0.04218  -0.0693   1.0000   0.0092
 -16.500  -1.2086   0.04381   0.03967  -0.0665   1.0000   0.0093
 -16.250  -1.2162   0.04186   0.03763  -0.0636   1.0000   0.0094
 -16.000  -1.2212   0.04023   0.03592  -0.0607   1.0000   0.0096
 -15.750  -1.2190   0.03860   0.03421  -0.0590   0.9997   0.0097
 -15.500  -1.2093   0.03702   0.03255  -0.0586   0.9991   0.0100
 -15.250  -1.1998   0.03548   0.03091  -0.0580   0.9983   0.0102
 -15.000  -1.1890   0.03408   0.02941  -0.0574   0.9976   0.0104
 -14.750  -1.1769   0.03276   0.02800  -0.0568   0.9968   0.0107
 -14.500  -1.1640   0.03146   0.02659  -0.0563   0.9960   0.0109
 -14.250  -1.1488   0.03034   0.02537  -0.0559   0.9954   0.0112
 -14.000  -1.1319   0.02935   0.02428  -0.0557   0.9948   0.0114
 -13.750  -1.1192   0.02800   0.02281  -0.0549   0.9943   0.0117
 -13.500  -1.1118   0.02653   0.02124  -0.0530   0.9930   0.0121
 -13.250  -1.0970   0.02564   0.02030  -0.0520   0.9915   0.0125
 -13.000  -1.0782   0.02493   0.01954  -0.0516   0.9901   0.0129
 -12.750  -1.0581   0.02425   0.01882  -0.0514   0.9890   0.0134
 -12.500  -1.0371   0.02360   0.01811  -0.0513   0.9880   0.0139
 -12.250  -1.0149   0.02302   0.01746  -0.0514   0.9871   0.0144
 -12.000  -0.9908   0.02256   0.01693  -0.0517   0.9864   0.0147
 -11.750  -0.9751   0.02136   0.01566  -0.0508   0.9856   0.0157
 -11.500  -0.9505   0.02084   0.01513  -0.0513   0.9850   0.0164
 -11.250  -0.9248   0.02035   0.01461  -0.0519   0.9845   0.0171
 -11.000  -0.8986   0.01988   0.01410  -0.0526   0.9841   0.0179
 -10.750  -0.8714   0.01948   0.01364  -0.0534   0.9837   0.0185
 -10.500  -0.8632   0.01882   0.01292  -0.0501   0.9797   0.0192
 -10.250  -0.8422   0.01822   0.01232  -0.0496   0.9780   0.0203
 -10.000  -0.8160   0.01788   0.01197  -0.0501   0.9769   0.0214
  -9.750  -0.7892   0.01751   0.01157  -0.0507   0.9759   0.0224
  -9.500  -0.7614   0.01718   0.01121  -0.0515   0.9752   0.0232
  -9.250  -0.7382   0.01643   0.01040  -0.0515   0.9745   0.0246
  -9.000  -0.7113   0.01592   0.00990  -0.0521   0.9739   0.0260
  -8.750  -0.6825   0.01556   0.00952  -0.0531   0.9734   0.0274
  -8.500  -0.6538   0.01521   0.00915  -0.0540   0.9728   0.0286
  -8.250  -0.6249   0.01491   0.00882  -0.0549   0.9721   0.0293
  -8.000  -0.6012   0.01424   0.00811  -0.0548   0.9713   0.0314
  -7.750  -0.5914   0.01399   0.00785  -0.0514   0.9663   0.0328
  -7.500  -0.5675   0.01367   0.00751  -0.0511   0.9644   0.0344
  -7.250  -0.5420   0.01335   0.00717  -0.0511   0.9628   0.0358
  -7.000  -0.5160   0.01305   0.00684  -0.0513   0.9615   0.0369
  -6.750  -0.4917   0.01260   0.00638  -0.0511   0.9602   0.0404
  -6.500  -0.4656   0.01227   0.00606  -0.0512   0.9590   0.0433
  -6.250  -0.4421   0.01203   0.00580  -0.0507   0.9571   0.0466
  -6.000  -0.4271   0.01176   0.00558  -0.0483   0.9531   0.0542
  -5.750  -0.4079   0.01138   0.00530  -0.0469   0.9504   0.0738
  -5.500  -0.3872   0.01094   0.00499  -0.0458   0.9483   0.1042
  -5.250  -0.3661   0.01046   0.00469  -0.0449   0.9464   0.1445
  -5.000  -0.3459   0.00997   0.00439  -0.0438   0.9446   0.1936
  -4.750  -0.3351   0.00954   0.00421  -0.0406   0.9407   0.2519
  -4.500  -0.3251   0.00899   0.00395  -0.0372   0.9366   0.3248
  -4.250  -0.3151   0.00829   0.00360  -0.0338   0.9335   0.4155
  -4.000  -0.3081   0.00755   0.00323  -0.0297   0.9306   0.5125
  -3.750  -0.3153   0.00707   0.00306  -0.0221   0.9246   0.5897
  -3.500  -0.3220   0.00661   0.00287  -0.0143   0.9196   0.6610
  -3.250  -0.3157   0.00625   0.00271  -0.0095   0.9166   0.7202
  -3.000  -0.3036   0.00615   0.00271  -0.0059   0.9132   0.7530
  -2.750  -0.2894   0.00608   0.00272  -0.0029   0.9093   0.7766
  -2.500  -0.2683   0.00600   0.00267  -0.0014   0.9067   0.7971
  -2.250  -0.2427   0.00594   0.00262  -0.0010   0.9047   0.8115
  -2.000  -0.2149   0.00590   0.00260  -0.0011   0.9031   0.8244
  -1.750  -0.1861   0.00589   0.00261  -0.0014   0.9015   0.8363
  -1.500  -0.1657   0.00596   0.00269   0.0003   0.8983   0.8472
  -1.250  -0.1462   0.00604   0.00280   0.0022   0.8949   0.8596
  -1.000  -0.1195   0.00613   0.00291   0.0025   0.8924   0.8691
  -0.750  -0.0891   0.00616   0.00293   0.0018   0.8905   0.8742
  -0.500  -0.0546   0.00619   0.00297   0.0001   0.8890   0.8772
  -0.250  -0.0219   0.00620   0.00298  -0.0012   0.8873   0.8802
   0.000   0.0000   0.00623   0.00300   0.0000   0.8840   0.8840
   0.250   0.0219   0.00621   0.00298   0.0012   0.8802   0.8873
   0.500   0.0546   0.00619   0.00297  -0.0001   0.8772   0.8890
   0.750   0.0891   0.00615   0.00293  -0.0018   0.8742   0.8905
   1.000   0.1194   0.00613   0.00291  -0.0025   0.8691   0.8924
   1.250   0.1462   0.00604   0.00280  -0.0022   0.8596   0.8949
   1.500   0.1657   0.00596   0.00270  -0.0003   0.8472   0.8983
   1.750   0.1862   0.00589   0.00261   0.0014   0.8364   0.9015
   2.000   0.2147   0.00590   0.00260   0.0011   0.8242   0.9031
   2.250   0.2428   0.00594   0.00262   0.0010   0.8117   0.9047
   2.500   0.2683   0.00600   0.00267   0.0014   0.7970   0.9067
   2.750   0.2894   0.00608   0.00272   0.0029   0.7767   0.9093
   3.000   0.3036   0.00614   0.00271   0.0059   0.7530   0.9132
   3.250   0.3155   0.00625   0.00271   0.0095   0.7194   0.9166
   3.500   0.3219   0.00662   0.00287   0.0143   0.6607   0.9196
   3.750   0.3150   0.00708   0.00306   0.0222   0.5887   0.9246
   4.000   0.3083   0.00755   0.00323   0.0296   0.5126   0.9306
   4.250   0.3153   0.00829   0.00360   0.0338   0.4157   0.9335
   4.500   0.3252   0.00899   0.00395   0.0372   0.3242   0.9366
   4.750   0.3354   0.00954   0.00421   0.0405   0.2517   0.9406
   5.000   0.3462   0.00997   0.00439   0.0437   0.1935   0.9446
   5.250   0.3664   0.01045   0.00469   0.0448   0.1443   0.9464
   5.500   0.3874   0.01094   0.00499   0.0458   0.1042   0.9483
   5.750   0.4081   0.01138   0.00529   0.0468   0.0734   0.9504
   6.000   0.4274   0.01176   0.00558   0.0482   0.0540   0.9531
   6.250   0.4425   0.01203   0.00580   0.0506   0.0464   0.9571
   6.500   0.4660   0.01227   0.00606   0.0511   0.0433   0.9590
   6.750   0.4920   0.01259   0.00638   0.0510   0.0404   0.9602
   7.000   0.5163   0.01305   0.00684   0.0512   0.0369   0.9615
   7.250   0.5423   0.01334   0.00716   0.0511   0.0357   0.9628
   7.500   0.5678   0.01366   0.00750   0.0510   0.0344   0.9644
   7.750   0.5917   0.01399   0.00785   0.0513   0.0329   0.9664
   8.000   0.6017   0.01424   0.00811   0.0548   0.0315   0.9713
   8.250   0.6254   0.01491   0.00882   0.0548   0.0293   0.9722
   8.500   0.6543   0.01521   0.00914   0.0539   0.0286   0.9728
   8.750   0.6829   0.01556   0.00952   0.0530   0.0274   0.9734
   9.000   0.7118   0.01592   0.00989   0.0521   0.0260   0.9740
   9.250   0.7387   0.01642   0.01039   0.0514   0.0246   0.9745
   9.500   0.7621   0.01716   0.01119   0.0513   0.0232   0.9753
   9.750   0.7899   0.01750   0.01156   0.0506   0.0224   0.9760
  10.000   0.8169   0.01786   0.01195   0.0499   0.0213   0.9769
  10.250   0.8428   0.01822   0.01232   0.0495   0.0203   0.9781
  10.500   0.8640   0.01879   0.01289   0.0499   0.0192   0.9798
  10.750   0.8723   0.01947   0.01363   0.0532   0.0185   0.9837
  11.000   0.8995   0.01987   0.01409   0.0524   0.0179   0.9841
  11.250   0.9258   0.02034   0.01460   0.0517   0.0171   0.9846
  11.500   0.9516   0.02082   0.01511   0.0511   0.0164   0.9851
  11.750   0.9762   0.02135   0.01565   0.0506   0.0157   0.9856
  12.000   0.9922   0.02253   0.01690   0.0514   0.0147   0.9864
  12.250   1.0164   0.02298   0.01742   0.0511   0.0144   0.9872
  12.500   1.0387   0.02355   0.01805   0.0510   0.0139   0.9881
  12.750   1.0595   0.02422   0.01878   0.0511   0.0134   0.9891
  13.000   1.0796   0.02491   0.01952   0.0513   0.0129   0.9903
  13.250   1.0983   0.02563   0.02028   0.0518   0.0125   0.9916
  13.500   1.1129   0.02651   0.02123   0.0528   0.0121   0.9932
  13.750   1.1201   0.02806   0.02287   0.0547   0.0116   0.9943
  14.000   1.1341   0.02930   0.02423   0.0553   0.0114   0.9949
  14.250   1.1510   0.03030   0.02533   0.0555   0.0112   0.9954
  14.500   1.1660   0.03144   0.02657   0.0559   0.0109   0.9961
  14.750   1.1794   0.03269   0.02793   0.0564   0.0106   0.9969
  15.000   1.1915   0.03401   0.02934   0.0570   0.0104   0.9977
  15.250   1.2022   0.03542   0.03085   0.0576   0.0102   0.9984
  15.500   1.2120   0.03695   0.03248   0.0582   0.0099   0.9992
  15.750   1.2215   0.03855   0.03416   0.0586   0.0097   0.9998
  16.000   1.2219   0.04013   0.03582   0.0607   0.0096   1.0000
  16.250   1.2166   0.04179   0.03756   0.0636   0.0094   1.0000
  16.500   1.2092   0.04371   0.03956   0.0665   0.0093   1.0000
  16.750   1.1976   0.04613   0.04209   0.0693   0.0092   1.0000
  17.000   1.1819   0.04915   0.04523   0.0718   0.0090   1.0000
  17.250   1.1622   0.05283   0.04906   0.0739   0.0089   1.0000
  17.500   1.1401   0.05716   0.05355   0.0753   0.0088   1.0000
  17.750   1.1190   0.06184   0.05839   0.0758   0.0088   1.0000
  18.000   1.1057   0.06597   0.06265   0.0756   0.0087   1.0000
  18.250   1.0891   0.07094   0.06775   0.0747   0.0087   1.0000
  18.500   1.0690   0.07691   0.07386   0.0728   0.0087   1.0000
  18.750   1.0443   0.08419   0.08130   0.0698   0.0087   1.0000
  19.000   1.0125   0.09328   0.09056   0.0656   0.0087   1.0000
  19.250   0.9725   0.10444   0.10190   0.0602   0.0088   1.0000
<< Back to NACA 16-015 (naca16015-il)

Polar data table (+)

Polar graphs


<< Back to NACA 16-015 (naca16015-il)