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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 100,000
Max Cl/Cd: 27.08 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du861372-il-100000-n5.txt
Download as CSV file: xf-du861372-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7491   0.08943   0.08318  -0.0385   0.3024   0.0468
 -12.750  -0.7668   0.08395   0.07762  -0.0408   0.3026   0.0465
 -12.500  -0.7855   0.07896   0.07253  -0.0424   0.3027   0.0462
 -12.250  -0.8079   0.07426   0.06768  -0.0431   0.3029   0.0460
 -12.000  -0.8295   0.07012   0.06336  -0.0428   0.3029   0.0459
 -11.750  -0.8481   0.06654   0.05957  -0.0417   0.3029   0.0458
 -11.250  -0.8844   0.06032   0.05288  -0.0369   0.3028   0.0460
 -11.000  -0.8979   0.05783   0.05012  -0.0336   0.3026   0.0461
 -10.750  -0.9091   0.05510   0.04704  -0.0303   0.3026   0.0464
 -10.500  -0.9153   0.05238   0.04387  -0.0272   0.3020   0.0467
 -10.250  -0.9074   0.04965   0.04089  -0.0257   0.3013   0.0475
 -10.000  -0.8926   0.04755   0.03867  -0.0249   0.3008   0.0488
  -9.750  -0.8835   0.04546   0.03626  -0.0232   0.3005   0.0503
  -9.500  -0.8744   0.04325   0.03362  -0.0212   0.3001   0.0514
  -9.250  -0.8588   0.04097   0.03096  -0.0198   0.2998   0.0518
  -9.000  -0.8370   0.03868   0.02838  -0.0192   0.2995   0.0517
  -8.750  -0.8107   0.03651   0.02597  -0.0191   0.2992   0.0516
  -8.500  -0.7802   0.03444   0.02372  -0.0194   0.2988   0.0511
  -8.000  -0.7133   0.03095   0.01996  -0.0209   0.2983   0.0501
  -7.750  -0.6824   0.02954   0.01848  -0.0213   0.2982   0.0491
  -7.500  -0.6572   0.02843   0.01722  -0.0208   0.2981   0.0476
  -7.250  -0.6383   0.02762   0.01629  -0.0195   0.2979   0.0466
  -7.000  -0.6217   0.02685   0.01541  -0.0181   0.2979   0.0459
  -6.750  -0.6048   0.02618   0.01461  -0.0166   0.2978   0.0451
  -6.500  -0.5869   0.02560   0.01389  -0.0153   0.2978   0.0444
  -6.250  -0.5679   0.02511   0.01325  -0.0141   0.2978   0.0436
  -6.000  -0.5479   0.02469   0.01269  -0.0131   0.2978   0.0429
  -5.750  -0.5273   0.02431   0.01218  -0.0122   0.2978   0.0423
  -5.500  -0.5072   0.02388   0.01162  -0.0112   0.2979   0.0419
  -5.250  -0.4865   0.02349   0.01112  -0.0102   0.2979   0.0414
  -5.000  -0.4654   0.02313   0.01066  -0.0094   0.2980   0.0410
  -4.750  -0.4442   0.02276   0.01020  -0.0085   0.2981   0.0409
  -4.500  -0.4231   0.02237   0.00969  -0.0077   0.2982   0.0413
  -4.250  -0.4015   0.02204   0.00927  -0.0069   0.2982   0.0415
  -4.000  -0.3791   0.02176   0.00892  -0.0062   0.2984   0.0413
  -3.750  -0.3562   0.02154   0.00862  -0.0055   0.2985   0.0409
  -3.500  -0.3330   0.02134   0.00832  -0.0050   0.2987   0.0405
  -3.250  -0.3097   0.02115   0.00807  -0.0044   0.2988   0.0401
  -3.000  -0.2861   0.02097   0.00784  -0.0039   0.2990   0.0397
  -2.750  -0.2623   0.02081   0.00763  -0.0034   0.2992   0.0393
  -2.500  -0.2385   0.02065   0.00742  -0.0030   0.2994   0.0390
  -2.250  -0.2145   0.02050   0.00721  -0.0025   0.2997   0.0387
  -2.000  -0.1905   0.02034   0.00702  -0.0021   0.3000   0.0384
  -1.750  -0.1662   0.02021   0.00685  -0.0017   0.3002   0.0382
  -1.500  -0.1418   0.02008   0.00670  -0.0013   0.3005   0.0380
  -1.000  -0.0927   0.01985   0.00640  -0.0006   0.3012   0.0377
  -0.750  -0.0680   0.01974   0.00629  -0.0003   0.3016   0.0377
  -0.500  -0.0432   0.01963   0.00618   0.0000   0.3020   0.0377
  -0.250  -0.0183   0.01953   0.00609   0.0003   0.3025   0.0380
   0.000   0.0062   0.01938   0.00604   0.0007   0.3029   0.0411
   0.500   0.0555   0.01919   0.00593   0.0014   0.3034   0.0809
   0.750   0.0805   0.01914   0.00592   0.0016   0.3036   0.0832
   1.250   0.1195   0.01780   0.00563   0.0033   0.3040   0.3602
   1.500   0.1286   0.01683   0.00613   0.0071   0.3044   0.6497
   1.750   0.1525   0.01693   0.00642   0.0080   0.3049   0.6892
   2.000   0.1755   0.01711   0.00672   0.0091   0.3050   0.7268
   2.250   0.1991   0.01729   0.00688   0.0098   0.3042   0.7421
   2.500   0.2213   0.01757   0.00715   0.0109   0.3032   0.7606
   2.750   0.2427   0.01788   0.00749   0.0123   0.3026   0.7796
   3.000   0.2633   0.01820   0.00786   0.0140   0.3020   0.7970
   3.250   0.2859   0.01840   0.00805   0.0149   0.3014   0.8076
   3.500   0.3076   0.01873   0.00836   0.0161   0.3001   0.8137
   3.750   0.3246   0.01931   0.00888   0.0190   0.2986   0.8339
   4.000   0.3451   0.01968   0.00925   0.0209   0.2973   0.8480
   4.250   0.3617   0.02005   0.00970   0.0245   0.2966   0.8718
   4.500   0.3849   0.02038   0.01004   0.0259   0.2955   0.8849
   4.750   0.4187   0.02119   0.01060   0.0246   0.2917   0.8874
   5.000   0.4534   0.02245   0.01169   0.0229   0.2831   0.8900
   5.250   0.4826   0.02360   0.01285   0.0221   0.2724   0.8931
   5.500   0.5073   0.02440   0.01380   0.0221   0.2627   0.8966
   5.750   0.5324   0.02506   0.01466   0.0221   0.2524   0.8994
   6.000   0.5550   0.02546   0.01531   0.0226   0.2414   0.9030
   6.250   0.5712   0.02524   0.01546   0.0243   0.2295   0.9078
   6.750   0.5996   0.02314   0.01446   0.0288   0.1678   0.9180
   7.000   0.6125   0.02288   0.01420   0.0307   0.1446   0.9241
   7.250   0.6296   0.02332   0.01457   0.0318   0.1157   0.9296
   7.500   0.6499   0.02400   0.01510   0.0323   0.0929   0.9337
   7.750   0.6692   0.02472   0.01574   0.0329   0.0777   0.9388
   8.000   0.6883   0.02544   0.01653   0.0336   0.0671   0.9447
   8.250   0.7087   0.02638   0.01749   0.0338   0.0586   0.9502
   8.500   0.7289   0.02727   0.01849   0.0341   0.0527   0.9569
   8.750   0.7469   0.02859   0.01985   0.0340   0.0484   0.9635
   9.000   0.7699   0.02967   0.02114   0.0337   0.0445   0.9707
   9.250   0.7924   0.03081   0.02241   0.0330   0.0404   0.9805
   9.500   0.8094   0.03210   0.02377   0.0331   0.0381   1.0000
   9.750   0.8158   0.03360   0.02526   0.0351   0.0366   1.0000
  10.000   0.8327   0.03504   0.02691   0.0360   0.0354   1.0000
  10.250   0.8501   0.03672   0.02881   0.0366   0.0340   1.0000
  10.500   0.8652   0.03842   0.03072   0.0373   0.0324   1.0000
  10.750   0.8761   0.03989   0.03234   0.0382   0.0305   1.0000
  11.000   0.8864   0.04164   0.03423   0.0391   0.0294   1.0000
  11.250   0.8945   0.04353   0.03623   0.0399   0.0285   1.0000
  11.500   0.9004   0.04598   0.03881   0.0407   0.0277   1.0000
  11.750   0.9015   0.04911   0.04213   0.0416   0.0272   1.0000
  12.000   0.8980   0.05200   0.04532   0.0425   0.0270   1.0000
  12.250   0.8899   0.05527   0.04888   0.0432   0.0268   1.0000
  12.500   0.8784   0.05891   0.05279   0.0435   0.0267   1.0000
  12.750   0.8631   0.06301   0.05715   0.0432   0.0266   1.0000
  13.000   0.8448   0.06772   0.06209   0.0422   0.0266   1.0000
  13.250   0.8236   0.07324   0.06782   0.0401   0.0266   1.0000
  13.500   0.8007   0.07969   0.07446   0.0367   0.0267   1.0000
  13.750   0.7761   0.08758   0.08250   0.0317   0.0269   1.0000
  14.000   0.7479   0.09789   0.09293   0.0246   0.0271   1.0000
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