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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 500,000
Max Cl/Cd: 46.65 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du861372-il-500000.txt
Download as CSV file: xf-du861372-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU 86-137/25 AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.4909   0.14319   0.13941   0.0008   0.2984   0.0137
 -14.750  -0.4929   0.13904   0.13525  -0.0018   0.2985   0.0142
 -14.500  -0.6000   0.13681   0.13261  -0.0104   0.2970   0.0131
 -13.500  -0.6685   0.09295   0.08868  -0.0346   0.2964   0.0136
 -13.250  -0.6979   0.08377   0.07936  -0.0408   0.2961   0.0133
 -13.000  -0.7217   0.07731   0.07276  -0.0445   0.2963   0.0132
 -12.750  -0.7435   0.07187   0.06720  -0.0467   0.2964   0.0133
 -12.500  -0.7649   0.06726   0.06245  -0.0478   0.2963   0.0133
 -12.250  -0.7824   0.06352   0.05857  -0.0479   0.2963   0.0133
 -12.000  -0.7992   0.06007   0.05499  -0.0473   0.2966   0.0134
 -11.750  -0.8147   0.05707   0.05184  -0.0459   0.2967   0.0135
 -11.500  -0.8290   0.05440   0.04902  -0.0440   0.2968   0.0136
 -11.250  -0.8432   0.05198   0.04643  -0.0415   0.2969   0.0139
 -11.000  -0.8544   0.04994   0.04423  -0.0385   0.2970   0.0140
 -10.750  -0.8675   0.04826   0.04238  -0.0344   0.2972   0.0142
 -10.500  -0.8803   0.04729   0.04117  -0.0297   0.2974   0.0146
 -10.250  -0.8951   0.04696   0.04045  -0.0245   0.2976   0.0148
 -10.000  -0.9080   0.04710   0.04013  -0.0195   0.2979   0.0150
  -9.750  -0.9160   0.04715   0.03965  -0.0150   0.2981   0.0150
  -9.500  -0.9141   0.04657   0.03863  -0.0118   0.2986   0.0151
  -9.250  -0.9078   0.04589   0.03749  -0.0092   0.2990   0.0151
  -9.000  -0.8488   0.03662   0.02896  -0.0153   0.3000   0.0156
  -8.750  -0.8254   0.03424   0.02654  -0.0154   0.3007   0.0159
  -8.500  -0.8054   0.03257   0.02473  -0.0147   0.3013   0.0162
  -8.250  -0.7856   0.03115   0.02316  -0.0140   0.3021   0.0165
  -8.000  -0.7658   0.03000   0.02183  -0.0131   0.3026   0.0169
  -7.750  -0.7468   0.02923   0.02086  -0.0120   0.3033   0.0173
  -7.500  -0.7328   0.02941   0.02069  -0.0100   0.3038   0.0178
  -7.250  -0.7210   0.03021   0.02103  -0.0075   0.3043   0.0180
  -7.000  -0.7016   0.03047   0.02095  -0.0062   0.3049   0.0181
  -6.750  -0.6614   0.02594   0.01681  -0.0089   0.3057   0.0185
  -6.500  -0.6263   0.02384   0.01487  -0.0104   0.3067   0.0190
  -6.250  -0.5982   0.02273   0.01375  -0.0108   0.3075   0.0196
  -6.000  -0.5748   0.02223   0.01313  -0.0102   0.3084   0.0205
  -5.750  -0.5620   0.02311   0.01359  -0.0078   0.3091   0.0211
  -5.500  -0.5219   0.02058   0.01138  -0.0102   0.3100   0.0219
  -5.250  -0.4921   0.01940   0.01034  -0.0108   0.3107   0.0232
  -5.000  -0.4763   0.02013   0.01067  -0.0089   0.3113   0.0244
  -4.750  -0.4446   0.01751   0.00857  -0.0100   0.3118   0.0268
  -4.500  -0.4278   0.01643   0.00754  -0.0085   0.3122   0.0291
  -4.250  -0.4109   0.01559   0.00675  -0.0070   0.3125   0.0306
  -4.000  -0.3894   0.01513   0.00626  -0.0062   0.3128   0.0318
  -3.750  -0.3702   0.01442   0.00555  -0.0050   0.3132   0.0334
  -3.500  -0.3477   0.01397   0.00506  -0.0044   0.3137   0.0348
  -3.250  -0.3230   0.01368   0.00472  -0.0040   0.3144   0.0358
  -3.000  -0.2974   0.01348   0.00449  -0.0038   0.3150   0.0367
  -2.750  -0.2714   0.01330   0.00429  -0.0036   0.3156   0.0378
  -2.500  -0.2454   0.01312   0.00412  -0.0034   0.3162   0.0396
  -2.250  -0.2197   0.01292   0.00397  -0.0033   0.3168   0.0517
  -2.000  -0.1929   0.01284   0.00386  -0.0032   0.3171   0.0548
  -1.750  -0.1662   0.01277   0.00379  -0.0032   0.3169   0.0562
  -1.500  -0.1398   0.01272   0.00373  -0.0031   0.3165   0.0586
  -1.250  -0.1133   0.01268   0.00369  -0.0031   0.3160   0.0603
  -1.000  -0.0867   0.01265   0.00364  -0.0031   0.3157   0.0618
  -0.750  -0.0602   0.01267   0.00362  -0.0030   0.3153   0.0600
  -0.500  -0.0332   0.01266   0.00357  -0.0031   0.3154   0.0566
  -0.250  -0.0063   0.01263   0.00351  -0.0031   0.3155   0.0542
   0.000   0.0204   0.01261   0.00348  -0.0031   0.3155   0.0510
   0.250   0.0477   0.01269   0.00347  -0.0031   0.3155   0.0349
   0.500   0.0735   0.01272   0.00351  -0.0030   0.3150   0.0328
   0.750   0.0989   0.01285   0.00363  -0.0028   0.3141   0.0316
   1.000   0.1246   0.01300   0.00375  -0.0026   0.3134   0.0307
   1.250   0.1505   0.01311   0.00384  -0.0025   0.3130   0.0313
   1.500   0.1763   0.01320   0.00396  -0.0024   0.3125   0.0578
   1.750   0.2026   0.01336   0.00410  -0.0024   0.3120   0.0590
   2.000   0.2294   0.01341   0.00418  -0.0024   0.3114   0.0615
   2.250   0.2558   0.01358   0.00438  -0.0024   0.3094   0.0655
   2.500   0.2826   0.01466   0.00536  -0.0028   0.3044   0.1293
   2.750   0.3095   0.01548   0.00625  -0.0031   0.2961   0.1623
   3.000   0.3228   0.01412   0.00652  -0.0019   0.2861   0.6479
   3.250   0.3468   0.01529   0.00795  -0.0016   0.2722   0.7204
   3.500   0.3705   0.01557   0.00846  -0.0007   0.2636   0.7602
   3.750   0.3951   0.01614   0.00916   0.0000   0.2580   0.7822
   4.000   0.4166   0.01662   0.00983   0.0018   0.2523   0.8066
   4.250   0.4402   0.01687   0.01019   0.0026   0.2461   0.8144
   4.500   0.4656   0.01682   0.01024   0.0030   0.2405   0.8195
   4.750   0.4894   0.01696   0.01046   0.0035   0.2371   0.8227
   5.000   0.5142   0.01638   0.01006   0.0040   0.2298   0.8248
   5.250   0.5370   0.01589   0.00975   0.0049   0.2241   0.8272
   5.500   0.5680   0.01561   0.00953   0.0043   0.1899   0.8294
   5.750   0.5956   0.01408   0.00812   0.0047   0.1686   0.8323
   6.000   0.6256   0.01389   0.00783   0.0042   0.1444   0.8346
   6.250   0.6492   0.01424   0.00807   0.0045   0.1204   0.8367
   6.500   0.6703   0.01465   0.00829   0.0053   0.0961   0.8388
   6.750   0.6917   0.01505   0.00860   0.0060   0.0799   0.8411
   7.000   0.7135   0.01545   0.00895   0.0067   0.0679   0.8435
   7.250   0.7359   0.01581   0.00929   0.0073   0.0589   0.8460
   7.500   0.7571   0.01626   0.00971   0.0081   0.0510   0.8484
   7.750   0.7786   0.01669   0.01011   0.0088   0.0452   0.8509
   8.000   0.7979   0.01723   0.01068   0.0098   0.0405   0.8535
   8.250   0.8179   0.01761   0.01110   0.0108   0.0372   0.8560
   8.500   0.8334   0.01822   0.01172   0.0124   0.0338   0.8587
   8.750   0.8479   0.01883   0.01242   0.0142   0.0316   0.8616
   9.000   0.8654   0.01930   0.01294   0.0155   0.0301   0.8646
   9.250   0.8797   0.01981   0.01350   0.0173   0.0284   0.8679
   9.500   0.8921   0.02041   0.01413   0.0194   0.0274   0.8711
   9.750   0.8992   0.02122   0.01501   0.0221   0.0261   0.8747
  10.000   0.8963   0.02267   0.01657   0.0258   0.0251   0.8792
  10.250   0.9116   0.02335   0.01733   0.0270   0.0245   0.8829
  10.500   0.9279   0.02403   0.01808   0.0280   0.0236   0.8866
  10.750   0.9412   0.02480   0.01896   0.0295   0.0229   0.8909
  11.000   0.9547   0.02563   0.01988   0.0307   0.0221   0.8956
  11.250   0.9677   0.02658   0.02090   0.0320   0.0214   0.9004
  11.500   0.9807   0.02747   0.02185   0.0331   0.0207   0.9056
  11.750   0.9911   0.02858   0.02305   0.0345   0.0201   0.9122
  12.000   0.9964   0.03054   0.02514   0.0362   0.0193   0.9202
  12.250   1.0062   0.03243   0.02725   0.0374   0.0189   0.9308
  12.500   1.0256   0.03345   0.02845   0.0369   0.0185   0.9477
  12.750   1.0487   0.03486   0.03004   0.0352   0.0178   1.0000
  13.000   1.0598   0.03637   0.03168   0.0356   0.0173   1.0000
  13.250   1.0687   0.03804   0.03346   0.0361   0.0168   1.0000
  13.500   1.0750   0.03993   0.03547   0.0366   0.0164   1.0000
  13.750   1.0795   0.04195   0.03761   0.0372   0.0161   1.0000
  14.000   1.0833   0.04393   0.03969   0.0376   0.0158   1.0000
  14.250   1.0834   0.04634   0.04222   0.0381   0.0155   1.0000
  14.500   1.0836   0.04868   0.04464   0.0383   0.0152   1.0000
  14.750   1.0774   0.05193   0.04805   0.0384   0.0151   1.0000
  15.000   1.0700   0.05532   0.05155   0.0382   0.0149   1.0000
  15.250   1.0564   0.05970   0.05611   0.0375   0.0148   1.0000
  15.500   1.0398   0.06470   0.06130   0.0361   0.0147   1.0000
  15.750   1.0169   0.07111   0.06791   0.0336   0.0146   1.0000
  16.000   0.9948   0.07824   0.07523   0.0300   0.0146   1.0000
  16.250   0.9708   0.08676   0.08395   0.0249   0.0146   1.0000
  16.500   0.9493   0.09621   0.09358   0.0185   0.0148   1.0000
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