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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 100,000
Max Cl/Cd: 43.55 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e171-il-100000.txt
Download as CSV file: xf-e171-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: (Dicke 12.28%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5643   0.10508   0.10057  -0.0134   1.0000   0.0731
 -11.750  -0.6654   0.10392   0.09906  -0.0112   1.0000   0.0664
 -11.500  -0.7489   0.08281   0.07783  -0.0292   1.0000   0.0577
 -11.250  -0.7645   0.07689   0.07186  -0.0316   1.0000   0.0566
 -11.000  -0.7830   0.07174   0.06663  -0.0337   1.0000   0.0556
 -10.750  -0.8059   0.06695   0.06169  -0.0347   1.0000   0.0547
 -10.500  -0.8274   0.06282   0.05741  -0.0342   1.0000   0.0536
 -10.250  -0.8494   0.05907   0.05344  -0.0318   1.0000   0.0524
 -10.000  -0.8714   0.05460   0.04857  -0.0290   1.0000   0.0506
  -9.750  -0.8916   0.05044   0.04372  -0.0251   1.0000   0.0483
  -9.500  -0.8894   0.04736   0.04014  -0.0226   1.0000   0.0477
  -9.250  -0.8826   0.04398   0.03637  -0.0206   1.0000   0.0476
  -9.000  -0.8721   0.04005   0.03211  -0.0190   1.0000   0.0482
  -8.750  -0.8569   0.03740   0.02938  -0.0180   1.0000   0.0510
  -8.500  -0.8403   0.03524   0.02701  -0.0166   1.0000   0.0541
  -8.250  -0.8216   0.03276   0.02416  -0.0151   1.0000   0.0564
  -8.000  -0.8007   0.03071   0.02173  -0.0136   1.0000   0.0590
  -7.750  -0.7786   0.02823   0.01938  -0.0131   1.0000   0.0658
  -7.500  -0.7561   0.02642   0.01736  -0.0119   1.0000   0.0722
  -7.250  -0.7367   0.02473   0.01579  -0.0106   1.0000   0.0822
  -7.000  -0.7200   0.02313   0.01428  -0.0088   1.0000   0.0960
  -6.750  -0.7083   0.02143   0.01284  -0.0063   1.0000   0.1172
  -6.500  -0.7005   0.01970   0.01150  -0.0033   1.0000   0.1588
  -6.250  -0.6964   0.01788   0.01029   0.0002   1.0000   0.2333
  -6.000  -0.6922   0.01639   0.00951   0.0037   1.0000   0.3351
  -5.750  -0.6837   0.01570   0.00937   0.0072   1.0000   0.4358
  -5.500  -0.6704   0.01568   0.00950   0.0103   1.0000   0.5008
  -5.250  -0.6554   0.01585   0.00967   0.0132   1.0000   0.5431
  -5.000  -0.6406   0.01605   0.00984   0.0160   1.0000   0.5743
  -4.750  -0.6265   0.01627   0.01004   0.0189   1.0000   0.5997
  -4.500  -0.6143   0.01644   0.01014   0.0218   1.0000   0.6230
  -4.250  -0.6008   0.01668   0.01039   0.0247   1.0000   0.6420
  -4.000  -0.5881   0.01687   0.01052   0.0273   1.0000   0.6604
  -3.750  -0.5752   0.01702   0.01060   0.0298   1.0000   0.6784
  -3.500  -0.5448   0.01731   0.01083   0.0291   0.9944   0.6970
  -3.250  -0.5014   0.01764   0.01108   0.0263   0.9842   0.7152
  -3.000  -0.4606   0.01784   0.01117   0.0239   0.9735   0.7319
  -2.750  -0.4206   0.01797   0.01122   0.0216   0.9634   0.7475
  -2.500  -0.3758   0.01809   0.01123   0.0184   0.9554   0.7618
  -2.250  -0.3385   0.01810   0.01118   0.0166   0.9448   0.7745
  -2.000  -0.2990   0.01809   0.01110   0.0143   0.9358   0.7867
  -1.750  -0.2543   0.01805   0.01097   0.0110   0.9286   0.7987
  -1.500  -0.2191   0.01800   0.01087   0.0095   0.9187   0.8101
  -1.250  -0.1719   0.01799   0.01083   0.0062   0.9128   0.8190
  -1.000  -0.1403   0.01792   0.01072   0.0053   0.9021   0.8292
  -0.750  -0.1072   0.01783   0.01059   0.0042   0.8929   0.8401
  -0.500  -0.0652   0.01783   0.01058   0.0018   0.8853   0.8476
  -0.250  -0.0356   0.01781   0.01054   0.0014   0.8750   0.8575
   0.000   0.0000   0.01777   0.01049   0.0000   0.8670   0.8669
   0.250   0.0356   0.01781   0.01054  -0.0014   0.8575   0.8751
   0.500   0.0652   0.01783   0.01058  -0.0018   0.8475   0.8853
   0.750   0.1072   0.01783   0.01059  -0.0041   0.8401   0.8929
   1.000   0.1402   0.01792   0.01072  -0.0053   0.8292   0.9021
   1.250   0.1719   0.01799   0.01082  -0.0062   0.8190   0.9128
   1.500   0.2191   0.01800   0.01087  -0.0095   0.8103   0.9187
   1.750   0.2543   0.01805   0.01097  -0.0110   0.7987   0.9286
   2.000   0.2989   0.01809   0.01110  -0.0143   0.7867   0.9359
   2.250   0.3385   0.01810   0.01117  -0.0166   0.7745   0.9449
   2.500   0.3757   0.01808   0.01122  -0.0184   0.7617   0.9554
   2.750   0.4205   0.01797   0.01122  -0.0216   0.7474   0.9634
   3.000   0.4606   0.01784   0.01117  -0.0239   0.7319   0.9736
   3.250   0.5014   0.01763   0.01107  -0.0263   0.7151   0.9842
   3.500   0.5449   0.01731   0.01082  -0.0291   0.6970   0.9945
   3.750   0.5751   0.01702   0.01060  -0.0298   0.6785   1.0000
   4.000   0.5879   0.01687   0.01052  -0.0273   0.6606   1.0000
   4.250   0.6007   0.01668   0.01039  -0.0247   0.6420   1.0000
   4.500   0.6142   0.01644   0.01014  -0.0218   0.6230   1.0000
   4.750   0.6264   0.01626   0.01003  -0.0189   0.5997   1.0000
   5.000   0.6405   0.01605   0.00984  -0.0160   0.5744   1.0000
   5.250   0.6553   0.01584   0.00967  -0.0132   0.5431   1.0000
   5.500   0.6703   0.01568   0.00950  -0.0103   0.5009   1.0000
   5.750   0.6837   0.01570   0.00937  -0.0072   0.4360   1.0000
   6.000   0.6921   0.01639   0.00951  -0.0037   0.3348   1.0000
   6.250   0.6964   0.01788   0.01029  -0.0002   0.2334   1.0000
   6.500   0.7005   0.01970   0.01150   0.0033   0.1588   1.0000
   6.750   0.7082   0.02144   0.01284   0.0063   0.1170   1.0000
   7.000   0.7200   0.02313   0.01428   0.0088   0.0959   1.0000
   7.250   0.7367   0.02473   0.01578   0.0106   0.0822   1.0000
   7.500   0.7561   0.02643   0.01736   0.0119   0.0722   1.0000
   7.750   0.7786   0.02823   0.01939   0.0131   0.0656   1.0000
   8.000   0.8008   0.03071   0.02172   0.0136   0.0590   1.0000
   8.250   0.8218   0.03276   0.02415   0.0151   0.0565   1.0000
   8.500   0.8404   0.03524   0.02700   0.0166   0.0541   1.0000
   8.750   0.8568   0.03745   0.02944   0.0180   0.0511   1.0000
   9.000   0.8722   0.04003   0.03209   0.0190   0.0483   1.0000
   9.250   0.8828   0.04395   0.03633   0.0205   0.0476   1.0000
   9.500   0.8894   0.04743   0.04021   0.0226   0.0476   1.0000
   9.750   0.8919   0.05038   0.04361   0.0251   0.0483   1.0000
  10.000   0.8711   0.05466   0.04863   0.0290   0.0506   1.0000
  10.250   0.8501   0.05906   0.05343   0.0317   0.0525   1.0000
  10.500   0.8270   0.06291   0.05750   0.0341   0.0536   1.0000
  10.750   0.8064   0.06703   0.06178   0.0346   0.0548   1.0000
  11.000   0.7830   0.07183   0.06671   0.0336   0.0556   1.0000
  11.250   0.7626   0.07718   0.07216   0.0313   0.0565   1.0000
  11.500   0.7517   0.08276   0.07776   0.0294   0.0578   1.0000
  11.750   0.6655   0.10419   0.09933   0.0110   0.0664   1.0000
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