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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 1,000,000
Max Cl/Cd: 58.4 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du861372-il-1000000.txt
Download as CSV file: xf-du861372-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8843   0.04044   0.03534  -0.0297   0.2973   0.0099
 -10.750  -0.8717   0.03709   0.03197  -0.0293   0.2959   0.0101
 -10.500  -0.8657   0.03445   0.02926  -0.0279   0.2953   0.0102
 -10.250  -0.8638   0.03209   0.02678  -0.0256   0.2948   0.0103
 -10.000  -0.8597   0.02994   0.02450  -0.0235   0.2944   0.0105
  -9.750  -0.8538   0.02792   0.02234  -0.0214   0.2934   0.0108
  -9.500  -0.8462   0.02607   0.02032  -0.0194   0.2931   0.0111
  -9.250  -0.8369   0.02457   0.01862  -0.0174   0.2923   0.0115
  -9.000  -0.8282   0.02382   0.01763  -0.0149   0.2918   0.0119
  -8.750  -0.8190   0.02331   0.01683  -0.0123   0.2914   0.0121
  -8.500  -0.8068   0.02227   0.01553  -0.0102   0.2910   0.0121
  -8.250  -0.7927   0.02108   0.01408  -0.0085   0.2905   0.0122
  -8.000  -0.7765   0.01996   0.01272  -0.0071   0.2897   0.0122
  -7.750  -0.7573   0.01898   0.01152  -0.0062   0.2892   0.0122
  -7.500  -0.7352   0.01770   0.01013  -0.0057   0.2857   0.0122
  -7.250  -0.7129   0.01674   0.00904  -0.0053   0.2850   0.0123
  -7.000  -0.6901   0.01587   0.00803  -0.0049   0.2844   0.0123
  -6.750  -0.6664   0.01510   0.00716  -0.0047   0.2837   0.0123
  -6.500  -0.6422   0.01439   0.00636  -0.0045   0.2834   0.0123
  -5.750  -0.5724   0.02265   0.01431  -0.0067   0.2801   0.0128
  -5.500  -0.5441   0.02168   0.01337  -0.0071   0.2801   0.0129
  -5.250  -0.5162   0.02077   0.01250  -0.0073   0.2800   0.0132
  -5.000  -0.4895   0.02003   0.01178  -0.0074   0.2798   0.0136
  -4.750  -0.4631   0.01925   0.01105  -0.0073   0.2791   0.0140
  -4.500  -0.4376   0.01887   0.01065  -0.0071   0.2788   0.0144
  -4.250  -0.4137   0.01895   0.01061  -0.0066   0.2785   0.0148
  -4.000  -0.3895   0.01912   0.01067  -0.0061   0.2784   0.0150
  -3.750  -0.3643   0.01910   0.01057  -0.0058   0.2783   0.0150
  -3.500  -0.3384   0.01889   0.01033  -0.0057   0.2782   0.0151
  -3.250  -0.3121   0.01863   0.01007  -0.0057   0.2781   0.0151
  -3.000  -0.2855   0.01716   0.00883  -0.0058   0.2775   0.0154
  -2.750  -0.2627   0.01640   0.00819  -0.0052   0.2767   0.0156
  -2.500  -0.2402   0.01592   0.00777  -0.0045   0.2759   0.0158
  -2.250  -0.2171   0.01559   0.00745  -0.0040   0.2757   0.0161
  -2.000  -0.1932   0.01532   0.00720  -0.0036   0.2755   0.0165
  -1.750  -0.1685   0.01516   0.00704  -0.0033   0.2751   0.0169
  -1.500  -0.1423   0.01516   0.00702  -0.0032   0.2745   0.0176
  -1.250  -0.1129   0.01550   0.00729  -0.0036   0.2743   0.0180
  -1.000  -0.0924   0.01483   0.00669  -0.0027   0.2743   0.0187
  -0.750  -0.0678   0.01458   0.00645  -0.0025   0.2741   0.0197
  -0.500  -0.0392   0.01482   0.00666  -0.0027   0.2740   0.0212
  -0.250  -0.0160   0.01442   0.00626  -0.0023   0.2736   0.0237
   0.000   0.0098   0.01440   0.00620  -0.0022   0.2730   0.0268
   0.250   0.1190   0.00777   0.00009  -0.0190   0.2723   0.0176
   1.250   0.6913   0.02422   0.01883  -0.0276   0.2500   0.3772
   1.500   0.1734   0.01639   0.00805  -0.0034   0.2708   0.0269
   1.750   0.2010   0.01609   0.00781  -0.0035   0.2706   0.0258
   2.000   0.2280   0.01506   0.00690  -0.0032   0.2642   0.0275
   2.250   0.2537   0.01528   0.00719  -0.0031   0.2530   0.0268
   2.500   0.2794   0.01532   0.00730  -0.0030   0.2453   0.0260
   2.750   0.3059   0.01522   0.00726  -0.0029   0.2415   0.0256
   3.000   0.3324   0.01527   0.00736  -0.0029   0.2395   0.0255
   3.250   0.3586   0.01538   0.00752  -0.0028   0.2378   0.0283
   3.500   0.3844   0.01526   0.00755  -0.0027   0.2349   0.0730
   3.750   0.3990   0.01279   0.00700  -0.0014   0.2311   0.7108
   4.000   0.4250   0.01263   0.00702  -0.0010   0.2282   0.7451
   4.250   0.4510   0.01252   0.00703  -0.0005   0.2259   0.7686
   4.500   0.4801   0.01186   0.00656  -0.0006   0.2235   0.7739
   4.750   0.5069   0.01230   0.00696  -0.0007   0.2104   0.7787
   5.000   0.5482   0.01073   0.00536  -0.0024   0.1721   0.7832
   5.250   0.5746   0.01090   0.00542  -0.0023   0.1514   0.7888
   5.500   0.5986   0.01121   0.00569  -0.0019   0.1358   0.7932
   5.750   0.6217   0.01163   0.00596  -0.0014   0.1119   0.7962
   6.000   0.6455   0.01200   0.00619  -0.0011   0.0908   0.7982
   6.250   0.6701   0.01232   0.00642  -0.0008   0.0762   0.8001
   6.500   0.6950   0.01262   0.00664  -0.0006   0.0648   0.8017
   6.750   0.7198   0.01294   0.00688  -0.0004   0.0549   0.8031
   7.000   0.7446   0.01316   0.00710  -0.0002   0.0485   0.8054
   7.250   0.7687   0.01348   0.00737   0.0002   0.0411   0.8075
   7.500   0.7929   0.01378   0.00765   0.0006   0.0362   0.8094
   7.750   0.8167   0.01413   0.00799   0.0010   0.0317   0.8113
   8.000   0.8407   0.01443   0.00830   0.0013   0.0288   0.8132
   8.250   0.8625   0.01494   0.00879   0.0021   0.0250   0.8153
   8.500   0.8866   0.01523   0.00911   0.0024   0.0239   0.8173
   8.750   0.9099   0.01558   0.00948   0.0028   0.0224   0.8191
   9.000   0.9323   0.01598   0.00988   0.0034   0.0211   0.8209
   9.250   0.9496   0.01666   0.01062   0.0048   0.0192   0.8233
   9.500   0.9711   0.01704   0.01106   0.0055   0.0187   0.8256
   9.750   0.9932   0.01740   0.01146   0.0061   0.0181   0.8278
  10.000   1.0136   0.01784   0.01195   0.0069   0.0174   0.8302
  10.250   1.0339   0.01830   0.01245   0.0078   0.0167   0.8324
  10.500   1.0532   0.01880   0.01298   0.0087   0.0162   0.8346
  10.750   1.0716   0.01935   0.01355   0.0098   0.0155   0.8365
  11.000   1.0794   0.02009   0.01437   0.0126   0.0148   0.8397
  11.250   1.0757   0.02119   0.01562   0.0171   0.0143   0.8435
  11.500   1.0964   0.02158   0.01605   0.0178   0.0140   0.8464
  11.750   1.1122   0.02217   0.01670   0.0191   0.0138   0.8494
  12.000   1.1277   0.02280   0.01739   0.0203   0.0134   0.8523
  12.250   1.1401   0.02355   0.01823   0.0219   0.0131   0.8557
  12.500   1.1545   0.02424   0.01899   0.0231   0.0127   0.8594
  12.750   1.1680   0.02500   0.01982   0.0244   0.0124   0.8635
  13.000   1.1826   0.02576   0.02064   0.0255   0.0121   0.8676
  13.250   1.1972   0.02654   0.02147   0.0265   0.0117   0.8720
  13.500   1.2063   0.02755   0.02258   0.0280   0.0114   0.8774
  13.750   1.2098   0.02891   0.02404   0.0298   0.0112   0.8840
  14.000   1.2044   0.03080   0.02610   0.0322   0.0109   0.8933
  14.250   1.1908   0.03333   0.02887   0.0350   0.0105   0.9086
  14.500   1.2098   0.03395   0.02966   0.0352   0.0104   0.9395
  14.750   1.2365   0.03521   0.03105   0.0328   0.0102   1.0000
  15.000   1.2441   0.03674   0.03268   0.0335   0.0100   1.0000
  15.250   1.2554   0.03804   0.03405   0.0339   0.0098   1.0000
  15.500   1.2583   0.03997   0.03610   0.0346   0.0096   1.0000
  15.750   1.2653   0.04164   0.03785   0.0351   0.0093   1.0000
  16.000   1.2678   0.04369   0.04000   0.0355   0.0092   1.0000
  16.250   1.2708   0.04577   0.04216   0.0358   0.0090   1.0000
  16.500   1.2694   0.04830   0.04479   0.0360   0.0089   1.0000
  16.750   1.2635   0.05138   0.04800   0.0359   0.0088   1.0000
  17.000   1.2559   0.05481   0.05154   0.0355   0.0087   1.0000
  17.250   1.2552   0.05770   0.05450   0.0348   0.0085   1.0000
  17.500   1.2391   0.06263   0.05957   0.0333   0.0084   1.0000
  17.750   1.2129   0.06947   0.06658   0.0304   0.0085   1.0000
  18.000   1.1654   0.08096   0.07831   0.0242   0.0086   1.0000
  18.250   1.0810   0.10151   0.09919   0.0115   0.0090   1.0000
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