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NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-015 (naca16015-il)
Reynolds number: 100,000
Max Cl/Cd: 28.07 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16015-il-100000-n5.txt
Download as CSV file: xf-naca16015-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6864   0.10070   0.09534  -0.0598   1.0000   0.0301
 -13.750  -0.7174   0.09234   0.08692  -0.0634   1.0000   0.0297
 -13.500  -0.7487   0.08555   0.08005  -0.0651   1.0000   0.0293
 -13.250  -0.7799   0.07992   0.07428  -0.0651   1.0000   0.0290
 -13.000  -0.8104   0.07515   0.06936  -0.0635   1.0000   0.0288
 -12.750  -0.8396   0.07108   0.06511  -0.0607   1.0000   0.0288
 -12.500  -0.8675   0.06755   0.06138  -0.0568   1.0000   0.0288
 -12.250  -0.8938   0.06444   0.05807  -0.0521   1.0000   0.0289
 -12.000  -0.9190   0.06164   0.05504  -0.0468   1.0000   0.0292
 -11.750  -0.9431   0.05912   0.05227  -0.0408   1.0000   0.0295
 -11.500  -0.9656   0.05682   0.04970  -0.0343   1.0000   0.0298
 -11.250  -0.9869   0.05474   0.04733  -0.0275   1.0000   0.0302
 -11.000  -1.0071   0.05289   0.04516  -0.0202   1.0000   0.0305
 -10.750  -1.0252   0.05120   0.04315  -0.0129   1.0000   0.0308
 -10.500  -1.0298   0.04909   0.04091  -0.0083   1.0000   0.0314
 -10.250  -1.0305   0.04744   0.03913  -0.0041   1.0000   0.0321
 -10.000  -1.0299   0.04604   0.03755  -0.0001   1.0000   0.0329
  -9.750  -1.0280   0.04477   0.03612   0.0039   1.0000   0.0341
  -9.500  -1.0242   0.04340   0.03453   0.0077   1.0000   0.0357
  -9.250  -1.0172   0.04180   0.03261   0.0111   1.0000   0.0374
  -9.000  -1.0063   0.04013   0.03054   0.0140   1.0000   0.0390
  -8.750  -0.9900   0.03836   0.02866   0.0155   1.0000   0.0407
  -8.500  -0.9749   0.03732   0.02757   0.0171   0.9994   0.0429
  -8.250  -0.9512   0.03615   0.02619   0.0172   0.9978   0.0457
  -8.000  -0.9233   0.03488   0.02464   0.0167   0.9964   0.0485
  -7.750  -0.8957   0.03360   0.02330   0.0160   0.9951   0.0517
  -7.500  -0.8703   0.03267   0.02232   0.0157   0.9934   0.0549
  -7.250  -0.8452   0.03175   0.02129   0.0157   0.9916   0.0582
  -7.000  -0.8210   0.03094   0.02031   0.0159   0.9898   0.0619
  -6.750  -0.7992   0.03003   0.01943   0.0163   0.9879   0.0654
  -6.500  -0.7763   0.02932   0.01864   0.0167   0.9859   0.0692
  -6.250  -0.7548   0.02872   0.01791   0.0174   0.9836   0.0740
  -6.000  -0.7388   0.02797   0.01721   0.0191   0.9808   0.0799
  -5.750  -0.7194   0.02741   0.01653   0.0203   0.9782   0.0874
  -5.500  -0.6991   0.02675   0.01592   0.0212   0.9758   0.0977
  -5.250  -0.6783   0.02616   0.01538   0.0221   0.9735   0.1150
  -5.000  -0.6635   0.02549   0.01487   0.0241   0.9702   0.1437
  -4.750  -0.6470   0.02468   0.01441   0.0257   0.9674   0.2027
  -4.500  -0.6324   0.02357   0.01395   0.0275   0.9648   0.3184
  -4.250  -0.6222   0.02217   0.01363   0.0305   0.9626   0.5097
  -4.000  -0.5179   0.02457   0.01713   0.0184   0.9684   0.7787
  -3.750  -0.4911   0.02539   0.01783   0.0194   0.9658   0.8092
  -3.500  -0.4598   0.02625   0.01855   0.0194   0.9641   0.8289
  -3.250  -0.4169   0.02772   0.01987   0.0176   0.9633   0.8506
  -3.000  -0.3604   0.02939   0.02139   0.0131   0.9635   0.8684
  -2.750  -0.3270   0.02981   0.02167   0.0118   0.9617   0.8789
  -2.500  -0.2938   0.03002   0.02177   0.0103   0.9590   0.8840
  -2.250  -0.2734   0.03002   0.02168   0.0112   0.9553   0.8922
  -2.000  -0.2347   0.03015   0.02170   0.0084   0.9534   0.8953
  -1.750  -0.2011   0.03022   0.02169   0.0065   0.9513   0.9001
  -1.500  -0.1741   0.03022   0.02160   0.0059   0.9492   0.9064
  -1.250  -0.1451   0.03026   0.02160   0.0050   0.9453   0.9095
  -0.750  -0.0960   0.03024   0.02149   0.0049   0.9382   0.9202
  -0.500  -0.0571   0.03025   0.02148   0.0018   0.9364   0.9222
  -0.250  -0.0212   0.03027   0.02148  -0.0006   0.9342   0.9246
   0.000   0.0000   0.03028   0.02150   0.0000   0.9288   0.9288
   0.250   0.0211   0.03027   0.02148   0.0007   0.9246   0.9342
   0.500   0.0571   0.03025   0.02148  -0.0018   0.9222   0.9364
   0.750   0.0960   0.03023   0.02149  -0.0049   0.9202   0.9383
   1.250   0.1451   0.03025   0.02159  -0.0050   0.9095   0.9453
   1.500   0.1742   0.03021   0.02160  -0.0059   0.9064   0.9492
   1.750   0.2012   0.03021   0.02168  -0.0065   0.9001   0.9513
   2.000   0.2347   0.03014   0.02169  -0.0084   0.8954   0.9534
   2.250   0.2734   0.03001   0.02167  -0.0112   0.8922   0.9554
   2.500   0.2938   0.03001   0.02176  -0.0103   0.8840   0.9590
   2.750   0.3268   0.02981   0.02166  -0.0118   0.8789   0.9617
   3.000   0.3605   0.02938   0.02137  -0.0131   0.8685   0.9635
   3.250   0.4171   0.02771   0.01985  -0.0176   0.8506   0.9633
   3.500   0.4601   0.02623   0.01853  -0.0194   0.8289   0.9641
   3.750   0.4912   0.02538   0.01782  -0.0195   0.8093   0.9659
   4.000   0.5182   0.02455   0.01711  -0.0185   0.7786   0.9684
   4.250   0.6223   0.02217   0.01362  -0.0305   0.5081   0.9627
   4.500   0.6326   0.02356   0.01394  -0.0275   0.3184   0.9648
   4.750   0.6472   0.02467   0.01440  -0.0257   0.2025   0.9674
   5.000   0.6636   0.02548   0.01486  -0.0241   0.1438   0.9703
   5.250   0.6783   0.02615   0.01537  -0.0221   0.1150   0.9736
   5.500   0.6993   0.02674   0.01591  -0.0213   0.0977   0.9759
   5.750   0.7196   0.02740   0.01652  -0.0204   0.0874   0.9783
   6.000   0.7390   0.02796   0.01720  -0.0192   0.0799   0.9809
   6.250   0.7550   0.02871   0.01790  -0.0175   0.0740   0.9837
   6.500   0.7766   0.02930   0.01863  -0.0167   0.0691   0.9859
   6.750   0.7995   0.03002   0.01941  -0.0164   0.0654   0.9879
   7.000   0.8213   0.03093   0.02030  -0.0160   0.0618   0.9899
   7.250   0.8455   0.03175   0.02128  -0.0158   0.0582   0.9917
   7.500   0.8707   0.03266   0.02231  -0.0158   0.0549   0.9935
   7.750   0.8961   0.03359   0.02329  -0.0161   0.0517   0.9951
   8.000   0.9236   0.03487   0.02463  -0.0168   0.0485   0.9965
   8.250   0.9516   0.03614   0.02618  -0.0173   0.0457   0.9979
   8.500   0.9753   0.03732   0.02757  -0.0172   0.0428   0.9995
   8.750   0.9900   0.03834   0.02864  -0.0155   0.0407   1.0000
   9.000   1.0063   0.04012   0.03053  -0.0140   0.0390   1.0000
   9.250   1.0173   0.04179   0.03259  -0.0111   0.0374   1.0000
   9.500   1.0242   0.04340   0.03453  -0.0077   0.0357   1.0000
   9.750   1.0282   0.04477   0.03612  -0.0040   0.0341   1.0000
  10.000   1.0300   0.04603   0.03754   0.0000   0.0329   1.0000
  10.250   1.0307   0.04743   0.03912   0.0041   0.0321   1.0000
  10.500   1.0300   0.04908   0.04090   0.0083   0.0314   1.0000
  10.750   1.0252   0.05118   0.04314   0.0130   0.0308   1.0000
  11.000   1.0072   0.05288   0.04516   0.0202   0.0305   1.0000
  11.250   0.9870   0.05473   0.04732   0.0275   0.0301   1.0000
  11.500   0.9659   0.05680   0.04968   0.0343   0.0298   1.0000
  11.750   0.9432   0.05910   0.05225   0.0408   0.0294   1.0000
  12.000   0.9195   0.06162   0.05501   0.0467   0.0292   1.0000
  12.250   0.8943   0.06441   0.05803   0.0521   0.0289   1.0000
  12.500   0.8677   0.06753   0.06137   0.0568   0.0288   1.0000
  12.750   0.8399   0.07106   0.06509   0.0607   0.0287   1.0000
  13.000   0.8108   0.07512   0.06932   0.0635   0.0288   1.0000
  13.250   0.7803   0.07988   0.07424   0.0651   0.0290   1.0000
  13.500   0.7488   0.08556   0.08006   0.0651   0.0292   1.0000
  13.750   0.7178   0.09232   0.08689   0.0634   0.0297   1.0000
  14.000   0.6865   0.10078   0.09542   0.0597   0.0301   1.0000
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