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NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-015 (naca16015-il)
Reynolds number: 200,000
Max Cl/Cd: 31.97 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16015-il-200000-n5.txt
Download as CSV file: xf-naca16015-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.8149   0.08435   0.08025  -0.0675   1.0000   0.0155
 -15.000  -0.8570   0.07531   0.07097  -0.0704   1.0000   0.0153
 -14.750  -0.8887   0.06922   0.06466  -0.0705   1.0000   0.0153
 -14.500  -0.9149   0.06454   0.05978  -0.0692   1.0000   0.0153
 -14.250  -0.9378   0.06068   0.05572  -0.0669   1.0000   0.0154
 -14.000  -0.9579   0.05740   0.05225  -0.0640   1.0000   0.0156
 -13.750  -0.9759   0.05450   0.04915  -0.0606   1.0000   0.0157
 -13.500  -0.9919   0.05194   0.04638  -0.0567   1.0000   0.0159
 -13.250  -1.0057   0.04964   0.04388  -0.0526   1.0000   0.0162
 -13.000  -1.0177   0.04754   0.04156  -0.0484   1.0000   0.0166
 -12.750  -1.0280   0.04556   0.03934  -0.0439   1.0000   0.0170
 -12.500  -1.0362   0.04368   0.03719  -0.0395   1.0000   0.0176
 -12.250  -1.0346   0.04168   0.03483  -0.0367   0.9991   0.0181
 -12.000  -1.0263   0.04007   0.03313  -0.0353   0.9976   0.0187
 -11.750  -1.0153   0.03893   0.03190  -0.0340   0.9960   0.0194
 -11.500  -1.0025   0.03774   0.03057  -0.0329   0.9946   0.0201
 -11.250  -0.9890   0.03645   0.02910  -0.0316   0.9928   0.0209
 -11.000  -0.9735   0.03514   0.02758  -0.0305   0.9909   0.0221
 -10.750  -0.9560   0.03399   0.02615  -0.0296   0.9891   0.0235
 -10.500  -0.9381   0.03275   0.02477  -0.0290   0.9877   0.0247
 -10.250  -0.9198   0.03190   0.02387  -0.0284   0.9862   0.0259
 -10.000  -0.8985   0.03103   0.02289  -0.0282   0.9851   0.0274
  -9.750  -0.8805   0.03019   0.02192  -0.0271   0.9827   0.0290
  -9.500  -0.8605   0.02950   0.02102  -0.0262   0.9804   0.0307
  -9.250  -0.8404   0.02841   0.01992  -0.0257   0.9787   0.0325
  -9.000  -0.8196   0.02771   0.01915  -0.0252   0.9771   0.0342
  -8.750  -0.7964   0.02707   0.01844  -0.0252   0.9757   0.0364
  -8.500  -0.7713   0.02645   0.01768  -0.0254   0.9746   0.0386
  -8.250  -0.7559   0.02573   0.01690  -0.0235   0.9714   0.0402
  -8.000  -0.7397   0.02503   0.01620  -0.0220   0.9687   0.0424
  -7.750  -0.7194   0.02449   0.01560  -0.0212   0.9666   0.0448
  -7.500  -0.6967   0.02394   0.01497  -0.0208   0.9648   0.0471
  -7.250  -0.6720   0.02345   0.01438  -0.0209   0.9634   0.0494
  -7.000  -0.6568   0.02283   0.01376  -0.0190   0.9606   0.0524
  -6.750  -0.6452   0.02241   0.01332  -0.0161   0.9566   0.0550
  -6.500  -0.6256   0.02198   0.01281  -0.0150   0.9540   0.0584
  -6.250  -0.6033   0.02151   0.01231  -0.0144   0.9520   0.0632
  -6.000  -0.5796   0.02104   0.01185  -0.0142   0.9504   0.0717
  -5.750  -0.5555   0.02056   0.01141  -0.0141   0.9491   0.0847
  -5.500  -0.5558   0.02031   0.01120  -0.0084   0.9426   0.0957
  -5.250  -0.5377   0.01986   0.01083  -0.0070   0.9397   0.1195
  -5.000  -0.5184   0.01934   0.01046  -0.0058   0.9375   0.1556
  -4.750  -0.4995   0.01873   0.01009  -0.0046   0.9358   0.2075
  -4.500  -0.5020   0.01833   0.00989   0.0014   0.9295   0.2538
  -4.250  -0.4973   0.01756   0.00950   0.0057   0.9253   0.3376
  -3.750  -0.5022   0.01571   0.00876   0.0180   0.9166   0.5632
  -3.500  -0.4360   0.01565   0.00963   0.0103   0.9208   0.7588
  -3.250  -0.3863   0.01630   0.01032   0.0061   0.9209   0.8006
  -3.000  -0.3798   0.01657   0.01056   0.0108   0.9150   0.8165
  -2.750  -0.3595   0.01687   0.01082   0.0127   0.9116   0.8338
  -2.500  -0.3028   0.01825   0.01216   0.0076   0.9123   0.8516
  -2.250  -0.2755   0.01872   0.01258   0.0081   0.9101   0.8630
  -2.000  -0.2329   0.01904   0.01283   0.0048   0.9094   0.8645
  -1.750  -0.1932   0.01924   0.01297   0.0020   0.9085   0.8663
  -1.250  -0.1509   0.01921   0.01286   0.0043   0.9024   0.8774
  -1.000  -0.1202   0.01941   0.01303   0.0034   0.8991   0.8789
  -0.750  -0.0861   0.01950   0.01309   0.0017   0.8970   0.8806
  -0.500  -0.0521   0.01953   0.01311   0.0000   0.8952   0.8826
   0.000   0.0000   0.01918   0.01272   0.0000   0.8916   0.8916
   0.500   0.0521   0.01953   0.01311   0.0000   0.8826   0.8952
   0.750   0.0862   0.01950   0.01309  -0.0017   0.8806   0.8970
   1.000   0.1202   0.01941   0.01303  -0.0033   0.8789   0.8991
   1.250   0.1507   0.01921   0.01285  -0.0042   0.8774   0.9025
   1.750   0.1932   0.01924   0.01297  -0.0020   0.8663   0.9085
   2.000   0.2329   0.01904   0.01283  -0.0048   0.8645   0.9095
   2.250   0.2754   0.01872   0.01258  -0.0081   0.8630   0.9102
   2.500   0.3028   0.01825   0.01216  -0.0076   0.8516   0.9124
   2.750   0.3597   0.01686   0.01081  -0.0127   0.8338   0.9116
   3.000   0.3799   0.01656   0.01055  -0.0108   0.8165   0.9150
   3.250   0.3862   0.01630   0.01031  -0.0060   0.8003   0.9209
   3.500   0.4362   0.01564   0.00962  -0.0104   0.7586   0.9208
   3.750   0.5020   0.01570   0.00876  -0.0179   0.5634   0.9167
   4.000   0.4944   0.01654   0.00903  -0.0105   0.4524   0.9222
   4.250   0.4973   0.01756   0.00950  -0.0057   0.3373   0.9253
   4.500   0.5021   0.01832   0.00988  -0.0015   0.2544   0.9296
   4.750   0.4997   0.01873   0.01008   0.0046   0.2072   0.9358
   5.000   0.5186   0.01934   0.01046   0.0057   0.1555   0.9376
   5.250   0.5379   0.01985   0.01082   0.0069   0.1194   0.9397
   5.500   0.5560   0.02031   0.01119   0.0084   0.0957   0.9426
   5.750   0.5558   0.02056   0.01141   0.0140   0.0847   0.9491
   6.000   0.5799   0.02103   0.01185   0.0141   0.0716   0.9504
   6.250   0.6036   0.02151   0.01231   0.0144   0.0631   0.9520
   6.500   0.6260   0.02197   0.01281   0.0149   0.0584   0.9540
   6.750   0.6455   0.02240   0.01331   0.0161   0.0550   0.9567
   7.000   0.6567   0.02281   0.01375   0.0190   0.0524   0.9607
   7.250   0.6725   0.02345   0.01438   0.0208   0.0494   0.9634
   7.500   0.6972   0.02393   0.01496   0.0207   0.0471   0.9649
   7.750   0.7198   0.02448   0.01559   0.0211   0.0447   0.9666
   8.000   0.7401   0.02502   0.01618   0.0219   0.0423   0.9687
   8.250   0.7562   0.02572   0.01689   0.0235   0.0402   0.9715
   8.500   0.7718   0.02644   0.01767   0.0253   0.0385   0.9746
   8.750   0.7970   0.02706   0.01842   0.0250   0.0364   0.9758
   9.000   0.8202   0.02770   0.01914   0.0251   0.0342   0.9772
   9.250   0.8410   0.02840   0.01991   0.0256   0.0325   0.9788
   9.500   0.8611   0.02949   0.02102   0.0261   0.0307   0.9805
   9.750   0.8811   0.03019   0.02192   0.0269   0.0290   0.9828
  10.000   0.8993   0.03102   0.02288   0.0280   0.0273   0.9851
  10.250   0.9206   0.03189   0.02386   0.0282   0.0259   0.9863
  10.500   0.9390   0.03275   0.02477   0.0288   0.0247   0.9877
  10.750   0.9567   0.03396   0.02612   0.0295   0.0234   0.9892
  11.000   0.9744   0.03514   0.02757   0.0304   0.0221   0.9910
  11.250   0.9899   0.03644   0.02909   0.0315   0.0209   0.9929
  11.500   1.0035   0.03774   0.03057   0.0327   0.0201   0.9947
  11.750   1.0163   0.03891   0.03188   0.0338   0.0193   0.9961
  12.000   1.0274   0.04006   0.03312   0.0351   0.0187   0.9977
  12.250   1.0358   0.04168   0.03483   0.0365   0.0181   0.9992
  12.500   1.0365   0.04366   0.03717   0.0394   0.0176   1.0000
  12.750   1.0283   0.04553   0.03931   0.0439   0.0170   1.0000
  13.000   1.0181   0.04751   0.04153   0.0483   0.0166   1.0000
  13.250   1.0061   0.04962   0.04385   0.0526   0.0162   1.0000
  13.500   0.9924   0.05189   0.04633   0.0567   0.0159   1.0000
  13.750   0.9763   0.05447   0.04912   0.0606   0.0157   1.0000
  14.000   0.9586   0.05732   0.05216   0.0640   0.0155   1.0000
  14.250   0.9385   0.06060   0.05564   0.0669   0.0154   1.0000
  14.500   0.9161   0.06439   0.05962   0.0692   0.0153   1.0000
  14.750   0.8895   0.06911   0.06455   0.0705   0.0153   1.0000
  15.000   0.8572   0.07531   0.07097   0.0703   0.0153   1.0000
  15.250   0.8158   0.08422   0.08012   0.0675   0.0155   1.0000
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