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NACA 5-H-20 AIRFOIL (n5h20-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 5-H-20 AIRFOIL (n5h20-il)
Reynolds number: 100,000
Max Cl/Cd: 14.81 at α=14.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n5h20-il-100000-n5.txt
Download as CSV file: xf-n5h20-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 5-H-20 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2273   0.12125   0.11541  -0.0619   0.7073   0.0820
 -12.250  -0.2412   0.11654   0.11072  -0.0660   0.7054   0.0824
 -12.000  -0.2498   0.11185   0.10603  -0.0692   0.7036   0.0825
 -11.500  -0.2442   0.09711   0.09113  -0.0727   0.7007   0.0557
 -11.250  -0.2457   0.09298   0.08698  -0.0744   0.6992   0.0554
 -11.000  -0.2515   0.08780   0.08183  -0.0782   0.6960   0.0551
 -10.750  -0.2607   0.08288   0.07690  -0.0811   0.6933   0.0544
 -10.500  -0.2773   0.07802   0.07198  -0.0829   0.6910   0.0536
 -10.250  -0.3005   0.07338   0.06723  -0.0831   0.6889   0.0530
 -10.000  -0.3239   0.06940   0.06310  -0.0817   0.6870   0.0524
  -9.750  -0.3491   0.06568   0.05919  -0.0787   0.6852   0.0517
  -9.500  -0.3770   0.06209   0.05533  -0.0742   0.6836   0.0508
  -9.000  -0.4383   0.05597   0.04832  -0.0615   0.6781   0.0491
  -8.750  -0.4369   0.05400   0.04616  -0.0588   0.6751   0.0490
  -8.500  -0.4359   0.05199   0.04390  -0.0558   0.6725   0.0490
  -8.250  -0.4327   0.05004   0.04167  -0.0527   0.6703   0.0489
  -8.000  -0.4276   0.04811   0.03943  -0.0496   0.6685   0.0489
  -7.750  -0.4209   0.04624   0.03720  -0.0465   0.6670   0.0490
  -7.500  -0.4076   0.04460   0.03536  -0.0446   0.6657   0.0495
  -7.250  -0.3903   0.04371   0.03444  -0.0441   0.6623   0.0501
  -7.000  -0.3741   0.04297   0.03363  -0.0433   0.6590   0.0509
  -6.750  -0.3584   0.04194   0.03241  -0.0419   0.6564   0.0515
  -6.500  -0.3411   0.04081   0.03103  -0.0406   0.6543   0.0520
  -6.250  -0.3214   0.03957   0.02954  -0.0394   0.6526   0.0523
  -6.000  -0.2990   0.03836   0.02808  -0.0387   0.6511   0.0527
  -5.750  -0.2740   0.03718   0.02666  -0.0382   0.6499   0.0531
  -5.500  -0.2462   0.03604   0.02528  -0.0382   0.6488   0.0537
  -5.250  -0.2156   0.03492   0.02395  -0.0387   0.6478   0.0544
  -5.000  -0.1950   0.03532   0.02428  -0.0392   0.6424   0.0552
  -4.750  -0.1685   0.03509   0.02397  -0.0400   0.6394   0.0563
  -4.500  -0.1388   0.03467   0.02360  -0.0411   0.6374   0.0579
  -4.250  -0.1071   0.03422   0.02313  -0.0424   0.6357   0.0595
  -4.000  -0.0716   0.03367   0.02254  -0.0441   0.6345   0.0609
  -3.750  -0.0338   0.03309   0.02191  -0.0462   0.6334   0.0624
  -3.500   0.0017   0.03257   0.02137  -0.0479   0.6324   0.0640
  -3.250   0.0315   0.03211   0.02098  -0.0486   0.6315   0.0662
  -3.000   0.0588   0.03184   0.02070  -0.0488   0.6306   0.0694
  -2.750   0.0341   0.03525   0.02423  -0.0441   0.6215   0.0695
  -2.500   0.0418   0.03605   0.02500  -0.0419   0.6185   0.0719
  -2.250   0.0561   0.03634   0.02531  -0.0404   0.6167   0.0745
  -2.000   0.3029   0.03477   0.02687  -0.0719   0.6224   0.7265
  -1.750   0.2735   0.03624   0.02833  -0.0645   0.6183   0.7700
  -1.500   0.2449   0.03709   0.02913  -0.0560   0.6156   0.7946
  -1.250   0.2185   0.03779   0.02975  -0.0472   0.6137   0.8155
  -1.000   0.2198   0.03942   0.03130  -0.0414   0.6125   0.8553
  -0.750   0.1467   0.04324   0.03534  -0.0328   0.6017   0.8122
  -0.500   0.1153   0.04405   0.03612  -0.0236   0.5990   0.8234
   0.000   0.0964   0.04620   0.03810  -0.0096   0.5958   0.8748
   2.000   0.4715   0.05485   0.04614  -0.0470   0.5786   0.9730
   2.250   0.4855   0.05505   0.04629  -0.0449   0.5772   0.9722
   2.500   0.5034   0.05503   0.04621  -0.0432   0.5760   0.9714
   3.000   0.4644   0.05871   0.04993  -0.0329   0.5638   0.9715
   3.250   0.4779   0.05904   0.05023  -0.0311   0.5617   0.9714
   3.500   0.4938   0.05901   0.05016  -0.0291   0.5599   0.9707
   3.750   0.5131   0.05877   0.04988  -0.0274   0.5584   0.9701
   4.250   0.4908   0.06137   0.05250  -0.0187   0.5458   0.9697
   4.500   0.5048   0.06142   0.05253  -0.0166   0.5436   0.9693
   4.750   0.5219   0.06129   0.05238  -0.0148   0.5418   0.9689
   5.000   0.5427   0.06102   0.05209  -0.0134   0.5405   0.9687
   5.250   0.5193   0.06331   0.05443  -0.0090   0.5296   0.9695
   5.500   0.5359   0.06309   0.05420  -0.0072   0.5267   0.9692
   5.750   0.5555   0.06269   0.05378  -0.0055   0.5248   0.9689
   6.000   0.5781   0.06207   0.05315  -0.0040   0.5231   0.9686
   6.250   0.5556   0.06395   0.05508   0.0007   0.5110   0.9689
   6.500   0.5764   0.06341   0.05454   0.0022   0.5087   0.9687
   6.750   0.5976   0.06286   0.05398   0.0036   0.5066   0.9686
   7.000   0.5838   0.06432   0.05549   0.0074   0.4945   0.9689
   7.250   0.6061   0.06363   0.05481   0.0087   0.4921   0.9689
   7.750   0.6235   0.06426   0.05550   0.0123   0.4771   0.9697
   8.250   0.6418   0.06474   0.05604   0.0160   0.4619   0.9703
   8.750   0.6598   0.06526   0.05662   0.0197   0.4466   0.9708
   9.000   0.6580   0.06661   0.05801   0.0218   0.4348   0.9712
   9.250   0.6788   0.06602   0.05745   0.0229   0.4315   0.9714
   9.500   0.6791   0.06736   0.05883   0.0248   0.4200   0.9719
   9.750   0.6993   0.06686   0.05835   0.0258   0.4166   0.9723
  10.250   0.7206   0.06790   0.05948   0.0283   0.4026   0.9732
  10.500   0.7314   0.06853   0.06015   0.0295   0.3964   0.9738
  10.750   0.7447   0.06901   0.06068   0.0304   0.3907   0.9744
  11.000   0.7658   0.06873   0.06044   0.0309   0.3876   0.9752
  11.250   0.7901   0.06812   0.05987   0.0314   0.3853   0.9760
  11.500   0.7952   0.06957   0.06138   0.0325   0.3771   0.9769
  11.750   0.8144   0.06935   0.06120   0.0332   0.3733   0.9777
  12.000   0.8388   0.06856   0.06045   0.0339   0.3705   0.9784
  12.250   0.8543   0.06876   0.06070   0.0348   0.3655   0.9792
  12.500   0.8651   0.06947   0.06147   0.0358   0.3595   0.9800
  12.750   0.8871   0.06897   0.06101   0.0365   0.3557   0.9809
  13.000   0.9206   0.06765   0.05972   0.0362   0.3525   0.9814
  13.250   0.9305   0.06896   0.06111   0.0365   0.3449   0.9821
  13.500   0.9554   0.06850   0.06067   0.0364   0.3374   0.9828
  13.750   0.9812   0.06792   0.06009   0.0364   0.3288   0.9836
  14.000   0.9947   0.06870   0.06090   0.0367   0.3187   0.9845
  14.250   1.0163   0.06863   0.06083   0.0367   0.3103   0.9854
  14.500   1.0183   0.07079   0.06309   0.0371   0.3006   0.9865
  14.750   1.0342   0.07133   0.06367   0.0373   0.2916   0.9877
  15.000   1.0297   0.07428   0.06675   0.0376   0.2808   0.9889
  15.250   1.0296   0.07678   0.06936   0.0378   0.2702   0.9902
  15.500   1.0346   0.07870   0.07134   0.0380   0.2594   0.9916
  15.750   1.0295   0.08203   0.07480   0.0379   0.2470   0.9932
  16.000   1.0319   0.08454   0.07738   0.0377   0.2344   0.9952
  16.250   1.0372   0.08677   0.07961   0.0374   0.2205   0.9972
  16.500   1.0406   0.08933   0.08213   0.0369   0.2042   0.9990
  16.750   1.0392   0.09201   0.08480   0.0370   0.1891   1.0000
  17.000   1.0295   0.09431   0.08710   0.0388   0.1759   1.0000
  17.250   1.0190   0.09665   0.08940   0.0406   0.1627   1.0000
  17.500   1.0077   0.09908   0.09175   0.0424   0.1515   1.0000
  17.750   0.9969   0.10163   0.09421   0.0438   0.1428   1.0000
  18.000   0.9875   0.10437   0.09687   0.0448   0.1349   1.0000
  18.250   0.9799   0.10713   0.09953   0.0454   0.1280   1.0000
  18.500   0.9747   0.10988   0.10229   0.0457   0.1211   1.0000
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