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DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: DU 86-137/25 AIRFOIL (du861372-il)
Reynolds number: 500,000
Max Cl/Cd: 48.86 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du861372-il-500000-n5.txt
Download as CSV file: xf-du861372-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7030   0.08909   0.08462  -0.0372   0.2388   0.0108
 -13.250  -0.7217   0.08321   0.07865  -0.0405   0.2387   0.0107
 -13.000  -0.7441   0.07785   0.07317  -0.0430   0.2388   0.0107
 -12.750  -0.7647   0.07342   0.06861  -0.0444   0.2389   0.0108
 -12.500  -0.7795   0.06945   0.06454  -0.0448   0.2389   0.0107
 -12.250  -0.7995   0.06602   0.06097  -0.0444   0.2389   0.0107
 -12.000  -0.8254   0.06339   0.05815  -0.0426   0.2389   0.0108
 -11.750  -0.8402   0.06083   0.05545  -0.0408   0.2388   0.0108
 -11.500  -0.8622   0.05888   0.05332  -0.0374   0.2390   0.0108
 -11.250  -0.8850   0.05749   0.05175  -0.0325   0.2388   0.0109
 -11.000  -0.8979   0.05586   0.04994  -0.0285   0.2387   0.0109
 -10.750  -0.9125   0.05456   0.04835  -0.0242   0.2388   0.0109
 -10.500  -0.9212   0.05330   0.04679  -0.0203   0.2386   0.0109
 -10.250  -0.9291   0.05233   0.04543  -0.0163   0.2385   0.0110
 -10.000  -0.9330   0.05147   0.04415  -0.0126   0.2385   0.0110
  -9.750  -0.8938   0.04466   0.03762  -0.0160   0.2382   0.0112
  -9.500  -0.8745   0.04159   0.03451  -0.0160   0.2379   0.0115
  -9.250  -0.8600   0.03958   0.03236  -0.0150   0.2378   0.0117
  -9.000  -0.8459   0.03791   0.03051  -0.0137   0.2378   0.0121
  -8.750  -0.8314   0.03662   0.02901  -0.0123   0.2376   0.0126
  -8.500  -0.8180   0.03613   0.02824  -0.0104   0.2374   0.0131
  -8.250  -0.8054   0.03620   0.02798  -0.0082   0.2374   0.0133
  -8.000  -0.7924   0.03623   0.02765  -0.0061   0.2373   0.0134
  -7.750  -0.7768   0.03593   0.02700  -0.0044   0.2373   0.0135
  -7.500  -0.7560   0.03516   0.02601  -0.0036   0.2372   0.0135
  -7.250  -0.7338   0.03432   0.02497  -0.0030   0.2372   0.0135
  -7.000  -0.7107   0.03346   0.02395  -0.0026   0.2371   0.0135
  -6.750  -0.6865   0.03257   0.02293  -0.0023   0.2371   0.0135
  -6.500  -0.6586   0.02976   0.02021  -0.0029   0.2371   0.0136
  -6.250  -0.6283   0.02735   0.01793  -0.0039   0.2371   0.0138
  -6.000  -0.5980   0.02565   0.01631  -0.0047   0.2372   0.0140
  -5.750  -0.5705   0.02459   0.01525  -0.0051   0.2373   0.0142
  -5.500  -0.5439   0.02376   0.01439  -0.0052   0.2373   0.0144
  -5.250  -0.5177   0.02308   0.01368  -0.0052   0.2372   0.0145
  -5.000  -0.4916   0.02245   0.01303  -0.0052   0.2370   0.0146
  -4.750  -0.4656   0.02189   0.01245  -0.0052   0.2369   0.0148
  -4.500  -0.4399   0.02138   0.01193  -0.0051   0.2369   0.0150
  -4.250  -0.4145   0.02094   0.01147  -0.0049   0.2369   0.0153
  -4.000  -0.3895   0.02061   0.01111  -0.0047   0.2370   0.0156
  -3.750  -0.3650   0.02043   0.01087  -0.0044   0.2371   0.0159
  -3.500  -0.3413   0.02058   0.01089  -0.0039   0.2373   0.0161
  -3.250  -0.3176   0.02073   0.01089  -0.0034   0.2374   0.0162
  -3.000  -0.2923   0.02055   0.01068  -0.0032   0.2375   0.0163
  -2.750  -0.2660   0.01926   0.00965  -0.0033   0.2377   0.0165
  -2.500  -0.2440   0.01854   0.00905  -0.0026   0.2378   0.0168
  -2.250  -0.2228   0.01799   0.00856  -0.0018   0.2380   0.0175
  -2.000  -0.1995   0.01775   0.00832  -0.0013   0.2381   0.0181
  -1.750  -0.1716   0.01802   0.00850  -0.0015   0.2383   0.0191
  -1.500  -0.1501   0.01757   0.00810  -0.0008   0.2385   0.0197
  -1.250  -0.1290   0.01704   0.00762  -0.0001   0.2384   0.0210
  -1.000  -0.0996   0.01739   0.00790  -0.0004   0.2378   0.0225
  -0.750  -0.0801   0.01662   0.00723   0.0005   0.2371   0.0236
  -0.250  -0.0301   0.01631   0.00688   0.0009   0.2368   0.0279
   0.000  -0.0038   0.01632   0.00687   0.0010   0.2369   0.0295
   1.000   0.1020   0.01636   0.00684   0.0009   0.2354   0.0315
   1.250   0.1289   0.01645   0.00694   0.0008   0.2352   0.0307
   1.500   0.1560   0.01656   0.00707   0.0007   0.2351   0.0290
   1.750   0.1831   0.01667   0.00721   0.0006   0.2348   0.0265
   2.000   0.2100   0.01676   0.00731   0.0005   0.2342   0.0245
   2.250   0.2368   0.01686   0.00745   0.0004   0.2335   0.0228
   2.500   0.2638   0.01697   0.00757   0.0003   0.2331   0.0221
   2.750   0.2908   0.01708   0.00766   0.0002   0.2327   0.0255
   3.000   0.3174   0.01724   0.00785   0.0002   0.2315   0.0250
   3.250   0.3434   0.01723   0.00792   0.0003   0.2287   0.0246
   3.500   0.3700   0.01693   0.00771   0.0004   0.2248   0.0244
   3.750   0.3961   0.01681   0.00767   0.0005   0.2217   0.0243
   4.000   0.4220   0.01671   0.00766   0.0007   0.2196   0.0247
   4.250   0.4476   0.01647   0.00754   0.0010   0.2168   0.0264
   4.500   0.4754   0.01632   0.00751   0.0008   0.2105   0.0838
   4.750   0.4924   0.01439   0.00728   0.0016   0.2053   0.6708
   5.000   0.5174   0.01398   0.00716   0.0022   0.1680   0.7448
   5.250   0.5436   0.01311   0.00638   0.0030   0.1437   0.7769
   5.500   0.5698   0.01324   0.00644   0.0032   0.1202   0.7821
   5.750   0.5942   0.01361   0.00661   0.0035   0.0904   0.7868
   6.000   0.6190   0.01395   0.00685   0.0037   0.0737   0.7905
   6.250   0.6431   0.01428   0.00714   0.0041   0.0601   0.7949
   6.500   0.6674   0.01464   0.00744   0.0045   0.0486   0.7992
   6.750   0.6922   0.01495   0.00773   0.0047   0.0413   0.8023
   7.000   0.7168   0.01529   0.00804   0.0050   0.0350   0.8044
   7.250   0.7413   0.01564   0.00837   0.0052   0.0301   0.8062
   7.500   0.7653   0.01601   0.00873   0.0056   0.0261   0.8079
   7.750   0.7891   0.01634   0.00910   0.0060   0.0233   0.8096
   8.000   0.8119   0.01677   0.00954   0.0065   0.0206   0.8116
   8.250   0.8348   0.01717   0.00999   0.0070   0.0193   0.8137
   8.500   0.8577   0.01757   0.01045   0.0075   0.0181   0.8158
   8.750   0.8799   0.01801   0.01094   0.0081   0.0170   0.8178
   9.000   0.9014   0.01850   0.01146   0.0088   0.0161   0.8199
   9.250   0.9207   0.01912   0.01213   0.0097   0.0150   0.8220
   9.500   0.9396   0.01972   0.01279   0.0108   0.0145   0.8243
   9.750   0.9594   0.02022   0.01338   0.0117   0.0139   0.8265
  10.000   0.9783   0.02073   0.01397   0.0127   0.0133   0.8287
  10.250   0.9965   0.02128   0.01460   0.0138   0.0127   0.8310
  10.500   1.0130   0.02190   0.01530   0.0151   0.0123   0.8334
  10.750   1.0285   0.02251   0.01598   0.0166   0.0119   0.8360
  11.000   1.0400   0.02319   0.01674   0.0187   0.0116   0.8389
  11.250   1.0501   0.02399   0.01760   0.0208   0.0113   0.8421
  11.500   1.0552   0.02500   0.01871   0.0235   0.0108   0.8454
  11.750   1.0562   0.02623   0.02007   0.0265   0.0106   0.8491
  12.000   1.0667   0.02712   0.02107   0.0281   0.0105   0.8526
  12.250   1.0754   0.02815   0.02222   0.0298   0.0103   0.8563
  12.500   1.0831   0.02929   0.02349   0.0313   0.0102   0.8602
  12.750   1.0902   0.03050   0.02483   0.0329   0.0100   0.8642
  13.000   1.0960   0.03181   0.02630   0.0344   0.0098   0.8694
  13.250   1.1021   0.03319   0.02781   0.0357   0.0096   0.8751
  13.500   1.1055   0.03478   0.02955   0.0371   0.0095   0.8812
  13.750   1.1083   0.03643   0.03136   0.0384   0.0094   0.8888
  14.250   1.1158   0.03977   0.03504   0.0403   0.0089   0.9117
  14.500   1.1259   0.04173   0.03719   0.0395   0.0087   0.9360
  15.500   1.1252   0.05252   0.04850   0.0379   0.0082   1.0000
  15.750   1.1203   0.05590   0.05201   0.0371   0.0081   1.0000
  16.000   1.1109   0.06008   0.05631   0.0356   0.0079   1.0000
  16.250   1.0950   0.06563   0.06203   0.0332   0.0080   1.0000
  16.500   1.0785   0.07198   0.06855   0.0298   0.0079   1.0000
  16.750   1.0529   0.08095   0.07772   0.0243   0.0079   1.0000
  17.000   1.0201   0.09172   0.08867   0.0177   0.0080   1.0000
  17.250   0.9903   0.10201   0.09910   0.0114   0.0080   1.0000
  17.500   0.9624   0.11176   0.10899   0.0056   0.0081   1.0000
  17.750   0.9292   0.12327   0.12066  -0.0012   0.0082   1.0000
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