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DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il)
Reynolds number: 200,000
Max Cl/Cd: 62.07 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du84132v-il-200000-n5.txt
Download as CSV file: xf-du84132v-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4468   0.08733   0.08354  -0.0534   1.0000   0.0281
 -10.500  -0.4694   0.08019   0.07645  -0.0557   1.0000   0.0276
 -10.250  -0.5613   0.05832   0.05432  -0.0724   0.9968   0.0265
 -10.000  -0.5883   0.05038   0.04599  -0.0804   0.9855   0.0261
  -9.750  -0.5979   0.04430   0.03945  -0.0846   0.9749   0.0258
  -9.500  -0.5920   0.03934   0.03397  -0.0875   0.9683   0.0256
  -9.250  -0.5834   0.03593   0.03014  -0.0879   0.9607   0.0255
  -9.000  -0.5638   0.03323   0.02709  -0.0891   0.9559   0.0255
  -8.750  -0.5385   0.03088   0.02441  -0.0907   0.9531   0.0255
  -8.500  -0.5206   0.02917   0.02246  -0.0902   0.9464   0.0256
  -8.250  -0.4948   0.02748   0.02053  -0.0910   0.9416   0.0257
  -8.000  -0.4643   0.02589   0.01873  -0.0925   0.9386   0.0258
  -7.750  -0.4384   0.02460   0.01726  -0.0928   0.9335   0.0260
  -7.500  -0.4125   0.02345   0.01597  -0.0930   0.9282   0.0262
  -7.250  -0.3817   0.02232   0.01472  -0.0941   0.9249   0.0265
  -7.000  -0.3485   0.02126   0.01354  -0.0956   0.9225   0.0268
  -6.750  -0.3229   0.02041   0.01262  -0.0955   0.9167   0.0271
  -6.500  -0.2943   0.01956   0.01171  -0.0960   0.9116   0.0275
  -6.250  -0.2621   0.01873   0.01080  -0.0972   0.9080   0.0279
  -6.000  -0.2281   0.01796   0.00996  -0.0988   0.9052   0.0285
  -5.750  -0.2061   0.01744   0.00940  -0.0979   0.8973   0.0292
  -5.500  -0.1756   0.01685   0.00882  -0.0988   0.8926   0.0303
  -5.250  -0.1417   0.01632   0.00827  -0.1003   0.8892   0.0315
  -5.000  -0.1176   0.01592   0.00783  -0.0997   0.8814   0.0325
  -4.750  -0.0870   0.01544   0.00730  -0.1005   0.8761   0.0338
  -4.500  -0.0545   0.01499   0.00681  -0.1016   0.8717   0.0355
  -4.250  -0.0284   0.01467   0.00646  -0.1013   0.8641   0.0383
  -4.000   0.0035   0.01427   0.00600  -0.1022   0.8588   0.0432
  -3.750   0.0322   0.01391   0.00558  -0.1025   0.8520   0.0506
  -3.500   0.0611   0.01352   0.00521  -0.1028   0.8446   0.0610
  -3.250   0.0889   0.01298   0.00488  -0.1031   0.8368   0.1009
  -3.000   0.1154   0.01248   0.00463  -0.1032   0.8272   0.1711
  -2.750   0.1408   0.01202   0.00444  -0.1031   0.8172   0.2440
  -2.500   0.1689   0.01157   0.00423  -0.1034   0.8082   0.3138
  -2.250   0.1947   0.01119   0.00411  -0.1032   0.7982   0.3969
  -2.000   0.2196   0.01078   0.00401  -0.1028   0.7874   0.4778
  -1.750   0.2436   0.01049   0.00411  -0.1017   0.7761   0.5763
  -1.500   0.2679   0.01062   0.00447  -0.1002   0.7661   0.6488
  -1.250   0.2960   0.01076   0.00454  -0.0998   0.7564   0.6857
  -1.000   0.3233   0.01093   0.00463  -0.0993   0.7462   0.7048
  -0.750   0.3499   0.01108   0.00470  -0.0988   0.7345   0.7202
  -0.500   0.3771   0.01121   0.00473  -0.0985   0.7225   0.7333
  -0.250   0.4037   0.01140   0.00484  -0.0978   0.7123   0.7425
   0.000   0.4295   0.01160   0.00498  -0.0971   0.7015   0.7539
   0.250   0.4551   0.01181   0.00514  -0.0963   0.6907   0.7666
   0.500   0.4783   0.01199   0.00530  -0.0949   0.6783   0.7754
   0.750   0.5042   0.01213   0.00535  -0.0943   0.6663   0.7842
   1.000   0.5289   0.01224   0.00538  -0.0934   0.6538   0.7896
   1.250   0.5544   0.01232   0.00541  -0.0928   0.6397   0.7948
   1.500   0.5807   0.01240   0.00542  -0.0925   0.6273   0.7988
   1.750   0.6059   0.01246   0.00543  -0.0919   0.6168   0.8015
   2.000   0.6315   0.01254   0.00547  -0.0914   0.6064   0.8044
   2.250   0.6566   0.01263   0.00553  -0.0908   0.5927   0.8083
   2.500   0.6820   0.01277   0.00557  -0.0904   0.5777   0.8126
   3.000   0.7281   0.01300   0.00570  -0.0882   0.5488   0.8206
   3.250   0.7519   0.01314   0.00580  -0.0874   0.5329   0.8251
   3.500   0.7762   0.01332   0.00590  -0.0868   0.5160   0.8282
   3.750   0.7986   0.01348   0.00599  -0.0858   0.4992   0.8303
   4.000   0.8207   0.01365   0.00611  -0.0847   0.4790   0.8323
   4.250   0.8418   0.01383   0.00622  -0.0835   0.4454   0.8344
   4.500   0.8605   0.01413   0.00636  -0.0819   0.4144   0.8365
   4.750   0.8787   0.01450   0.00655  -0.0803   0.3888   0.8384
   5.000   0.8996   0.01482   0.00679  -0.0792   0.3731   0.8400
   5.250   0.9220   0.01509   0.00705  -0.0783   0.3598   0.8416
   5.500   0.9444   0.01538   0.00731  -0.0775   0.3473   0.8431
   5.750   0.9658   0.01565   0.00757  -0.0765   0.3352   0.8445
   6.000   0.9865   0.01592   0.00783  -0.0754   0.3226   0.8461
   6.250   1.0062   0.01621   0.00812  -0.0741   0.3114   0.8480
   6.500   1.0245   0.01653   0.00842  -0.0725   0.3005   0.8501
   6.750   1.0421   0.01689   0.00875  -0.0709   0.2882   0.8520
   7.000   1.0615   0.01719   0.00907  -0.0695   0.2754   0.8540
   7.250   1.0798   0.01756   0.00946  -0.0681   0.2655   0.8563
   7.500   1.0968   0.01801   0.00987  -0.0665   0.2563   0.8582
   7.750   1.1156   0.01838   0.01028  -0.0651   0.2463   0.8599
   8.000   1.1337   0.01877   0.01072  -0.0637   0.2357   0.8616
   8.250   1.1519   0.01918   0.01118  -0.0623   0.2203   0.8635
   8.500   1.1663   0.01976   0.01171  -0.0605   0.1985   0.8655
   8.750   1.1790   0.02047   0.01232  -0.0585   0.1772   0.8678
   9.250   1.1989   0.02232   0.01395  -0.0541   0.1402   0.8726
   9.500   1.2125   0.02307   0.01475  -0.0525   0.1303   0.8751
   9.750   1.2259   0.02382   0.01557  -0.0508   0.1215   0.8781
  10.000   1.2390   0.02462   0.01641  -0.0493   0.1101   0.8815
  10.250   1.2497   0.02560   0.01738  -0.0475   0.1021   0.8852
  10.500   1.2603   0.02662   0.01843  -0.0459   0.0958   0.8890
  10.750   1.2708   0.02767   0.01953  -0.0444   0.0912   0.8942
  11.000   1.2797   0.02887   0.02080  -0.0428   0.0873   0.9013
  11.250   1.2911   0.02996   0.02202  -0.0416   0.0844   0.9130
  11.500   1.3021   0.03100   0.02322  -0.0406   0.0813   0.9875
  12.000   1.3151   0.03391   0.02625  -0.0376   0.0749   1.0000
  12.250   1.3231   0.03544   0.02787  -0.0365   0.0718   1.0000
  12.500   1.3336   0.03681   0.02937  -0.0357   0.0682   1.0000
  12.750   1.3409   0.03848   0.03111  -0.0348   0.0645   1.0000
  13.000   1.3462   0.04037   0.03306  -0.0340   0.0613   1.0000
  13.250   1.3555   0.04196   0.03479  -0.0334   0.0571   1.0000
  13.500   1.3612   0.04392   0.03682  -0.0328   0.0533   1.0000
  13.750   1.3662   0.04602   0.03899  -0.0323   0.0502   1.0000
  14.000   1.3701   0.04830   0.04133  -0.0319   0.0474   1.0000
  14.250   1.3716   0.05089   0.04396  -0.0317   0.0450   1.0000
  14.500   1.3721   0.05369   0.04684  -0.0316   0.0433   1.0000
  14.750   1.3716   0.05670   0.04995  -0.0316   0.0417   1.0000
  15.000   1.3692   0.06006   0.05339  -0.0319   0.0404   1.0000
  15.250   1.3644   0.06382   0.05722  -0.0324   0.0391   1.0000
  15.500   1.3588   0.06782   0.06128  -0.0331   0.0379   1.0000
  15.750   1.3575   0.07135   0.06497  -0.0338   0.0367   1.0000
  16.000   1.3547   0.07518   0.06894  -0.0347   0.0355   1.0000
  16.250   1.3505   0.07930   0.07317  -0.0359   0.0343   1.0000
  16.500   1.3451   0.08369   0.07766  -0.0373   0.0333   1.0000
  16.750   1.3382   0.08838   0.08241  -0.0389   0.0325   1.0000
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