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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 200,000
Max Cl/Cd: 35.47 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du861372-il-200000-n5.txt
Download as CSV file: xf-du861372-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7175   0.10251   0.09701  -0.0333   0.2664   0.0162
 -13.750  -0.7325   0.09703   0.09143  -0.0364   0.2664   0.0162
 -13.500  -0.7550   0.09185   0.08611  -0.0393   0.2665   0.0162
 -13.250  -0.7726   0.08738   0.08152  -0.0409   0.2664   0.0162
 -13.000  -0.7960   0.08335   0.07733  -0.0418   0.2665   0.0162
 -12.750  -0.8183   0.07998   0.07380  -0.0418   0.2666   0.0162
 -12.500  -0.8327   0.07672   0.07040  -0.0412   0.2666   0.0162
 -12.250  -0.8573   0.07426   0.06775  -0.0392   0.2667   0.0162
 -12.000  -0.8881   0.07269   0.06597  -0.0355   0.2667   0.0163
 -11.750  -0.8335   0.06466   0.05811  -0.0401   0.2663   0.0168
 -11.500  -0.8392   0.06154   0.05486  -0.0388   0.2664   0.0171
 -11.250  -0.8483   0.05887   0.05204  -0.0367   0.2663   0.0173
 -11.000  -0.8583   0.05669   0.04968  -0.0339   0.2662   0.0174
 -10.750  -0.8682   0.05478   0.04757  -0.0304   0.2663   0.0177
 -10.500  -0.8731   0.05281   0.04536  -0.0274   0.2662   0.0180
 -10.250  -0.8771   0.05109   0.04334  -0.0243   0.2661   0.0184
 -10.000  -0.8807   0.04988   0.04177  -0.0209   0.2661   0.0188
  -9.750  -0.8895   0.04974   0.04106  -0.0165   0.2661   0.0191
  -9.500  -0.8956   0.04997   0.04067  -0.0122   0.2660   0.0192
  -9.250  -0.8653   0.04491   0.03571  -0.0137   0.2659   0.0197
  -9.000  -0.8384   0.04132   0.03214  -0.0146   0.2658   0.0205
  -8.750  -0.8246   0.03987   0.03040  -0.0131   0.2657   0.0215
  -8.500  -0.8195   0.04003   0.03003  -0.0099   0.2657   0.0222
  -8.250  -0.8183   0.04126   0.03051  -0.0061   0.2657   0.0225
  -8.000  -0.7715   0.03536   0.02507  -0.0099   0.2656   0.0234
  -7.750  -0.7473   0.03365   0.02324  -0.0098   0.2655   0.0244
  -7.500  -0.7339   0.03355   0.02272  -0.0078   0.2656   0.0256
  -7.250  -0.7019   0.03096   0.02015  -0.0089   0.2655   0.0271
  -7.000  -0.6813   0.03012   0.01908  -0.0081   0.2655   0.0292
  -6.750  -0.6469   0.02766   0.01666  -0.0096   0.2655   0.0331
  -6.500  -0.6058   0.02536   0.01465  -0.0121   0.2656   0.0355
  -6.250  -0.5799   0.02444   0.01375  -0.0121   0.2656   0.0365
  -6.000  -0.5573   0.02379   0.01306  -0.0115   0.2657   0.0373
  -5.750  -0.5358   0.02330   0.01250  -0.0108   0.2658   0.0378
  -5.500  -0.5170   0.02246   0.01169  -0.0096   0.2659   0.0382
  -5.250  -0.5007   0.02172   0.01099  -0.0082   0.2660   0.0386
  -5.000  -0.4841   0.02112   0.01036  -0.0067   0.2662   0.0391
  -4.750  -0.4654   0.02067   0.00986  -0.0055   0.2663   0.0394
  -4.500  -0.4457   0.02029   0.00938  -0.0045   0.2664   0.0398
  -4.250  -0.4247   0.01999   0.00898  -0.0036   0.2666   0.0401
  -4.000  -0.4028   0.01977   0.00864  -0.0029   0.2668   0.0403
  -3.750  -0.3802   0.01960   0.00837  -0.0022   0.2669   0.0404
  -3.500  -0.3571   0.01947   0.00814  -0.0017   0.2671   0.0404
  -3.250  -0.3335   0.01937   0.00792  -0.0012   0.2672   0.0403
  -3.000  -0.3091   0.01932   0.00778  -0.0008   0.2673   0.0399
  -2.750  -0.2847   0.01926   0.00763  -0.0004   0.2674   0.0398
  -2.500  -0.2602   0.01918   0.00748  -0.0001   0.2674   0.0398
  -2.250  -0.2350   0.01915   0.00739   0.0001   0.2674   0.0392
  -2.000  -0.2096   0.01911   0.00731   0.0003   0.2676   0.0382
  -1.750  -0.1843   0.01904   0.00720   0.0005   0.2677   0.0374
  -1.500  -0.1589   0.01895   0.00710   0.0007   0.2680   0.0366
  -1.250  -0.1331   0.01889   0.00701   0.0009   0.2684   0.0356
  -1.000  -0.1072   0.01885   0.00695   0.0010   0.2687   0.0348
  -0.750  -0.0812   0.01883   0.00691   0.0010   0.2691   0.0339
  -0.500  -0.0554   0.01878   0.00683   0.0012   0.2695   0.0333
  -0.250  -0.0295   0.01875   0.00677   0.0012   0.2699   0.0327
   0.000  -0.0034   0.01873   0.00672   0.0013   0.2703   0.0320
   0.250   0.0228   0.01874   0.00672   0.0013   0.2705   0.0313
   0.500   0.0493   0.01884   0.00679   0.0013   0.2701   0.0306
   0.750   0.0760   0.01904   0.00694   0.0012   0.2692   0.0300
   1.000   0.1029   0.01925   0.00711   0.0011   0.2685   0.0296
   1.250   0.1297   0.01944   0.00725   0.0010   0.2681   0.0294
   1.500   0.1563   0.01947   0.00728   0.0010   0.2683   0.0297
   1.750   0.1831   0.01955   0.00733   0.0009   0.2682   0.0322
   2.000   0.2104   0.01984   0.00760   0.0007   0.2677   0.0327
   2.250   0.2370   0.01995   0.00774   0.0007   0.2668   0.0334
   2.750   0.2895   0.01990   0.00790   0.0008   0.2645   0.0710
   3.000   0.3165   0.02002   0.00807   0.0007   0.2640   0.0752
   3.250   0.3434   0.02014   0.00828   0.0007   0.2633   0.0833
   3.500   0.3525   0.01826   0.00850   0.0032   0.2628   0.6884
   3.750   0.3776   0.01861   0.00904   0.0038   0.2605   0.7375
   4.000   0.4043   0.01982   0.01026   0.0037   0.2553   0.7562
   4.250   0.4261   0.01955   0.01029   0.0052   0.2497   0.7792
   4.500   0.4480   0.02026   0.01114   0.0066   0.2444   0.8048
   4.750   0.4674   0.02060   0.01169   0.0088   0.2403   0.8264
   5.000   0.4893   0.02053   0.01182   0.0100   0.2347   0.8323
   5.250   0.5132   0.02062   0.01205   0.0105   0.2289   0.8353
   5.500   0.5363   0.02015   0.01180   0.0112   0.2206   0.8382
   5.750   0.5606   0.01961   0.01150   0.0117   0.2088   0.8409
   6.000   0.5847   0.01880   0.01084   0.0123   0.1638   0.8437
   6.250   0.6032   0.01827   0.01032   0.0138   0.1392   0.8464
   6.500   0.6261   0.01859   0.01054   0.0144   0.1093   0.8489
   6.750   0.6485   0.01898   0.01079   0.0149   0.0845   0.8515
   7.000   0.6707   0.01938   0.01113   0.0154   0.0679   0.8541
   7.250   0.6922   0.01977   0.01153   0.0161   0.0569   0.8571
   7.500   0.7121   0.02026   0.01200   0.0169   0.0483   0.8604
   7.750   0.7321   0.02064   0.01251   0.0179   0.0428   0.8632
   8.000   0.7486   0.02119   0.01308   0.0193   0.0374   0.8660
   8.250   0.7661   0.02173   0.01372   0.0206   0.0343   0.8690
   8.500   0.7834   0.02232   0.01442   0.0219   0.0316   0.8722
   8.750   0.7995   0.02300   0.01516   0.0232   0.0295   0.8760
   9.000   0.8106   0.02391   0.01612   0.0251   0.0276   0.8801
   9.250   0.8222   0.02460   0.01693   0.0273   0.0262   0.8838
   9.500   0.8353   0.02528   0.01774   0.0291   0.0247   0.8878
   9.750   0.8485   0.02605   0.01860   0.0307   0.0233   0.8922
  10.250   0.8718   0.02790   0.02064   0.0339   0.0216   0.9022
  10.500   0.8817   0.02903   0.02186   0.0355   0.0209   0.9086
  10.750   0.8887   0.03062   0.02353   0.0372   0.0201   0.9153
  11.000   0.9019   0.03188   0.02497   0.0382   0.0197   0.9225
  11.250   0.9158   0.03328   0.02657   0.0389   0.0192   0.9315
  11.750   0.9493   0.03677   0.03054   0.0382   0.0179   0.9683
  12.000   0.9582   0.03834   0.03227   0.0388   0.0172   1.0000
  12.250   0.9659   0.04007   0.03414   0.0393   0.0167   1.0000
  12.500   0.9721   0.04188   0.03607   0.0398   0.0162   1.0000
  12.750   0.9764   0.04385   0.03815   0.0402   0.0158   1.0000
  13.000   0.9780   0.04613   0.04056   0.0407   0.0155   1.0000
  13.250   0.9775   0.04867   0.04322   0.0410   0.0153   1.0000
  13.500   0.9733   0.05170   0.04641   0.0412   0.0151   1.0000
  13.750   0.9658   0.05518   0.05008   0.0410   0.0150   1.0000
  14.000   0.9536   0.05936   0.05445   0.0404   0.0148   1.0000
  14.250   0.9384   0.06416   0.05945   0.0391   0.0147   1.0000
  14.500   0.9231   0.06933   0.06483   0.0369   0.0147   1.0000
  14.750   0.9053   0.07544   0.07114   0.0337   0.0147   1.0000
  15.000   0.8835   0.08329   0.07921   0.0288   0.0147   1.0000
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