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=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 16-015 (naca16015-il)
Reynolds number: 500,000
Max Cl/Cd: 44.57 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca16015-il-500000.txt
Download as CSV file: xf-naca16015-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.9018   0.07669   0.07344  -0.0717   1.0000   0.0147
 -15.750  -0.9304   0.07065   0.06723  -0.0724   1.0000   0.0147
 -15.500  -0.9568   0.06564   0.06205  -0.0718   1.0000   0.0147
 -15.250  -0.9815   0.06135   0.05758  -0.0702   1.0000   0.0147
 -14.750  -1.0350   0.05335   0.04918  -0.0641   1.0000   0.0148
 -14.500  -1.0581   0.04999   0.04562  -0.0602   1.0000   0.0149
 -14.250  -1.0762   0.04722   0.04268  -0.0561   1.0000   0.0151
 -14.000  -1.0881   0.04518   0.04052  -0.0521   1.0000   0.0153
 -13.750  -1.0960   0.04363   0.03888  -0.0482   1.0000   0.0154
 -13.500  -1.1030   0.04223   0.03738  -0.0441   1.0000   0.0156
 -13.250  -1.1083   0.04109   0.03617  -0.0401   1.0000   0.0158
 -13.000  -1.1111   0.03986   0.03483  -0.0365   0.9998   0.0161
 -12.750  -1.1022   0.03852   0.03335  -0.0351   0.9985   0.0165
 -12.500  -1.0919   0.03729   0.03199  -0.0339   0.9971   0.0170
 -12.250  -1.0808   0.03587   0.03039  -0.0326   0.9958   0.0176
 -12.000  -1.0675   0.03452   0.02882  -0.0315   0.9946   0.0182
 -11.750  -1.0554   0.03350   0.02758  -0.0299   0.9928   0.0186
 -11.500  -1.0406   0.03111   0.02501  -0.0288   0.9915   0.0193
 -11.250  -1.0241   0.03019   0.02405  -0.0279   0.9898   0.0199
 -11.000  -1.0061   0.02946   0.02325  -0.0272   0.9881   0.0206
 -10.750  -0.9855   0.02866   0.02235  -0.0268   0.9867   0.0214
 -10.500  -0.9624   0.02787   0.02144  -0.0269   0.9855   0.0223
 -10.250  -0.9389   0.02735   0.02077  -0.0270   0.9845   0.0232
 -10.000  -0.9120   0.02579   0.01913  -0.0278   0.9841   0.0246
  -9.750  -0.8949   0.02519   0.01852  -0.0265   0.9818   0.0256
  -9.500  -0.8782   0.02463   0.01791  -0.0250   0.9789   0.0266
  -9.250  -0.8553   0.02403   0.01723  -0.0247   0.9770   0.0279
  -9.000  -0.8303   0.02358   0.01669  -0.0248   0.9754   0.0290
  -8.750  -0.8056   0.02237   0.01543  -0.0250   0.9745   0.0309
  -8.500  -0.7806   0.02180   0.01486  -0.0253   0.9735   0.0325
  -8.250  -0.7540   0.02130   0.01431  -0.0258   0.9726   0.0342
  -8.000  -0.7259   0.02085   0.01380  -0.0266   0.9719   0.0358
  -7.750  -0.7161   0.02062   0.01351  -0.0232   0.9670   0.0367
  -7.500  -0.7021   0.01963   0.01250  -0.0211   0.9642   0.0391
  -7.250  -0.6793   0.01916   0.01202  -0.0207   0.9624   0.0411
  -7.000  -0.6534   0.01875   0.01157  -0.0209   0.9611   0.0433
  -6.750  -0.6250   0.01841   0.01118  -0.0216   0.9600   0.0452
  -6.500  -0.5999   0.01774   0.01050  -0.0217   0.9590   0.0488
  -6.250  -0.5932   0.01751   0.01026  -0.0176   0.9541   0.0513
  -6.000  -0.5767   0.01726   0.00997  -0.0156   0.9505   0.0545
  -5.750  -0.5534   0.01681   0.00953  -0.0151   0.9485   0.0608
  -5.500  -0.5276   0.01634   0.00913  -0.0152   0.9471   0.0742
  -5.250  -0.5039   0.01570   0.00872  -0.0150   0.9459   0.1166
  -5.000  -0.4816   0.01499   0.00834  -0.0145   0.9448   0.1849
  -4.750  -0.4940   0.01477   0.00827  -0.0061   0.9364   0.2224
  -4.500  -0.4839   0.01394   0.00789  -0.0029   0.9336   0.3208
  -4.250  -0.4784   0.01290   0.00741   0.0013   0.9313   0.4464
  -4.000  -0.4975   0.01248   0.00729   0.0114   0.9228   0.5168
  -3.750  -0.5032   0.01150   0.00689   0.0187   0.9188   0.6431
  -3.500  -0.4877   0.01095   0.00679   0.0216   0.9171   0.7454
  -3.250  -0.4570   0.01086   0.00684   0.0211   0.9163   0.7915
  -3.000  -0.4573   0.01106   0.00706   0.0273   0.9089   0.8104
  -2.750  -0.4315   0.01109   0.00707   0.0277   0.9066   0.8279
  -2.500  -0.4007   0.01115   0.00713   0.0271   0.9052   0.8435
  -2.250  -0.3694   0.01127   0.00725   0.0264   0.9041   0.8581
  -2.000  -0.3335   0.01149   0.00746   0.0248   0.9034   0.8686
  -1.750  -0.2897   0.01199   0.00797   0.0215   0.9032   0.8781
  -1.500  -0.2414   0.01288   0.00886   0.0177   0.9033   0.8887
  -1.250  -0.1878   0.01347   0.00943   0.0120   0.9036   0.8901
  -1.000  -0.1430   0.01366   0.00960   0.0081   0.9035   0.8909
  -0.750  -0.0989   0.01377   0.00969   0.0042   0.9033   0.8916
  -0.500  -0.1126   0.01372   0.00964   0.0133   0.8951   0.9016
  -0.250  -0.0727   0.01380   0.00971   0.0104   0.8940   0.9022
   0.000  -0.0314   0.01384   0.00975   0.0071   0.8932   0.9026
   0.250   0.0111   0.01385   0.00975   0.0035   0.8927   0.9029
   0.500   0.0547   0.01382   0.00973  -0.0003   0.8921   0.9031
   0.750   0.0988   0.01377   0.00969  -0.0042   0.8916   0.9033
   1.000   0.1429   0.01365   0.00960  -0.0080   0.8909   0.9035
   1.250   0.1877   0.01347   0.00943  -0.0120   0.8901   0.9037
   1.500   0.2412   0.01288   0.00887  -0.0176   0.8887   0.9033
   1.750   0.2897   0.01198   0.00796  -0.0215   0.8782   0.9032
   2.000   0.3332   0.01149   0.00746  -0.0247   0.8684   0.9034
   2.250   0.3693   0.01127   0.00725  -0.0264   0.8581   0.9041
   2.500   0.4004   0.01115   0.00714  -0.0270   0.8437   0.9052
   2.750   0.4313   0.01108   0.00707  -0.0276   0.8280   0.9066
   3.000   0.4572   0.01106   0.00706  -0.0272   0.8105   0.9090
   3.250   0.4569   0.01086   0.00683  -0.0210   0.7912   0.9163
   3.500   0.4876   0.01094   0.00679  -0.0216   0.7454   0.9171
   3.750   0.5029   0.01150   0.00689  -0.0186   0.6424   0.9188
   4.000   0.4975   0.01247   0.00729  -0.0114   0.5172   0.9228
   4.250   0.4785   0.01289   0.00740  -0.0013   0.4465   0.9313
   4.500   0.4840   0.01394   0.00788   0.0029   0.3203   0.9336
   4.750   0.4941   0.01476   0.00827   0.0060   0.2223   0.9364
   5.000   0.4818   0.01498   0.00834   0.0145   0.1848   0.9448
   5.250   0.5041   0.01569   0.00871   0.0149   0.1166   0.9460
   5.500   0.5277   0.01633   0.00913   0.0151   0.0741   0.9472
   5.750   0.5535   0.01680   0.00953   0.0151   0.0607   0.9486
   6.000   0.5767   0.01725   0.00996   0.0156   0.0544   0.9506
   6.250   0.5929   0.01750   0.01025   0.0177   0.0512   0.9542
   6.500   0.6003   0.01773   0.01049   0.0216   0.0487   0.9590
   6.750   0.6253   0.01841   0.01118   0.0215   0.0452   0.9600
   7.000   0.6538   0.01875   0.01157   0.0208   0.0433   0.9611
   7.250   0.6796   0.01916   0.01201   0.0206   0.0411   0.9624
   7.500   0.7024   0.01962   0.01249   0.0210   0.0391   0.9642
   7.750   0.7165   0.02058   0.01348   0.0231   0.0367   0.9671
   8.000   0.7264   0.02086   0.01380   0.0265   0.0358   0.9719
   8.250   0.7545   0.02130   0.01431   0.0257   0.0342   0.9726
   8.500   0.7811   0.02179   0.01485   0.0252   0.0325   0.9735
   8.750   0.8062   0.02237   0.01543   0.0249   0.0309   0.9745
   9.000   0.8308   0.02358   0.01668   0.0247   0.0290   0.9755
   9.250   0.8558   0.02402   0.01723   0.0246   0.0279   0.9771
   9.500   0.8786   0.02462   0.01790   0.0249   0.0266   0.9790
   9.750   0.8949   0.02518   0.01851   0.0265   0.0256   0.9820
  10.000   0.9127   0.02578   0.01912   0.0276   0.0246   0.9841
  10.250   0.9397   0.02735   0.02078   0.0268   0.0232   0.9845
  10.500   0.9632   0.02787   0.02144   0.0267   0.0223   0.9855
  10.750   0.9862   0.02865   0.02235   0.0267   0.0214   0.9867
  11.000   1.0069   0.02945   0.02324   0.0270   0.0206   0.9881
  11.250   1.0249   0.03018   0.02403   0.0277   0.0199   0.9898
  11.500   1.0414   0.03111   0.02500   0.0287   0.0193   0.9916
  11.750   1.0562   0.03351   0.02759   0.0297   0.0186   0.9929
  12.000   1.0687   0.03448   0.02878   0.0313   0.0181   0.9947
  12.250   1.0822   0.03581   0.03032   0.0323   0.0175   0.9958
  12.500   1.0935   0.03716   0.03186   0.0336   0.0169   0.9972
  12.750   1.1036   0.03846   0.03329   0.0349   0.0164   0.9986
  13.000   1.1124   0.03985   0.03482   0.0362   0.0160   0.9999
  13.250   1.1088   0.04106   0.03613   0.0400   0.0158   1.0000
  13.500   1.1035   0.04218   0.03733   0.0441   0.0156   1.0000
  13.750   1.0973   0.04347   0.03870   0.0481   0.0154   1.0000
  14.000   1.0890   0.04507   0.04041   0.0520   0.0152   1.0000
  14.250   1.0767   0.04716   0.04262   0.0560   0.0151   1.0000
  14.500   1.0588   0.04991   0.04553   0.0601   0.0149   1.0000
  14.750   1.0343   0.05342   0.04926   0.0642   0.0148   1.0000
  15.000   1.0059   0.05748   0.05353   0.0677   0.0148   1.0000
  15.250   0.9827   0.06118   0.05740   0.0702   0.0147   1.0000
  15.500   0.9582   0.06543   0.06184   0.0718   0.0147   1.0000
  15.750   0.9317   0.07044   0.06703   0.0724   0.0147   1.0000
  16.000   0.9028   0.07651   0.07326   0.0717   0.0147   1.0000
  16.250   0.8756   0.08322   0.08013   0.0697   0.0148   1.0000
  16.500   0.8514   0.09041   0.08747   0.0666   0.0148   1.0000
<< Back to NACA 16-015 (naca16015-il)

Polar data table (+)

Polar graphs


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