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NACA 5-H-20 AIRFOIL (n5h20-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 5-H-20 AIRFOIL (n5h20-il)
Reynolds number: 200,000
Max Cl/Cd: 34.14 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n5h20-il-200000-n5.txt
Download as CSV file: xf-n5h20-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2689   0.10456   0.09961  -0.0596   0.6737   0.0376
 -12.250  -0.2667   0.10090   0.09594  -0.0610   0.6714   0.0375
 -12.000  -0.2644   0.09746   0.09248  -0.0624   0.6692   0.0372
 -11.750  -0.2649   0.09358   0.08857  -0.0640   0.6673   0.0369
 -11.500  -0.2718   0.08851   0.08349  -0.0666   0.6658   0.0364
 -11.250  -0.2889   0.08140   0.07639  -0.0711   0.6642   0.0359
 -11.000  -0.3351   0.07083   0.06573  -0.0773   0.6629   0.0353
 -10.750  -0.3792   0.06392   0.05865  -0.0770   0.6612   0.0348
 -10.500  -0.4172   0.05872   0.05324  -0.0740   0.6592   0.0344
 -10.250  -0.4454   0.05483   0.04913  -0.0699   0.6571   0.0343
 -10.000  -0.4684   0.05149   0.04555  -0.0650   0.6550   0.0342
  -9.750  -0.4862   0.04869   0.04250  -0.0599   0.6530   0.0342
  -9.500  -0.4976   0.04656   0.04014  -0.0550   0.6511   0.0343
  -9.250  -0.4998   0.04468   0.03803  -0.0513   0.6494   0.0346
  -8.750  -0.4960   0.04080   0.03366  -0.0447   0.6454   0.0353
  -8.500  -0.4913   0.03865   0.03123  -0.0416   0.6430   0.0355
  -8.250  -0.4823   0.03665   0.02895  -0.0391   0.6407   0.0357
  -8.000  -0.4702   0.03475   0.02675  -0.0369   0.6384   0.0359
  -7.750  -0.4548   0.03300   0.02471  -0.0351   0.6364   0.0361
  -7.500  -0.4364   0.03141   0.02283  -0.0337   0.6346   0.0364
  -7.250  -0.4152   0.02995   0.02108  -0.0328   0.6329   0.0367
  -7.000  -0.3915   0.02864   0.01948  -0.0322   0.6314   0.0371
  -6.750  -0.3656   0.02747   0.01802  -0.0321   0.6300   0.0374
  -6.500  -0.3376   0.02650   0.01692  -0.0324   0.6282   0.0380
  -6.250  -0.3097   0.02582   0.01625  -0.0329   0.6264   0.0386
  -6.000  -0.2810   0.02518   0.01557  -0.0334   0.6245   0.0392
  -5.750  -0.2501   0.02448   0.01480  -0.0343   0.6227   0.0398
  -5.500  -0.2166   0.02373   0.01397  -0.0356   0.6209   0.0404
  -5.250  -0.1792   0.02294   0.01310  -0.0377   0.6192   0.0411
  -5.000  -0.1412   0.02221   0.01230  -0.0398   0.6176   0.0418
  -4.750  -0.1051   0.02159   0.01162  -0.0416   0.6160   0.0425
  -4.500  -0.0719   0.02109   0.01105  -0.0427   0.6145   0.0432
  -4.250  -0.0412   0.02064   0.01063  -0.0435   0.6132   0.0441
  -4.000  -0.0132   0.02035   0.01033  -0.0438   0.6120   0.0454
  -3.750   0.0143   0.02010   0.01009  -0.0440   0.6107   0.0469
  -3.500   0.0413   0.01988   0.00988  -0.0442   0.6092   0.0482
  -3.250   0.0674   0.01965   0.00969  -0.0442   0.6077   0.0494
  -3.000   0.0922   0.01943   0.00953  -0.0440   0.6061   0.0507
  -2.750   0.1166   0.01927   0.00941  -0.0438   0.6046   0.0524
  -2.500   0.1407   0.01914   0.00928  -0.0434   0.6032   0.0546
  -2.250   0.1646   0.01899   0.00914  -0.0430   0.6017   0.0570
  -2.000   0.1886   0.01887   0.00903  -0.0425   0.6001   0.0611
  -1.750   0.2123   0.01871   0.00887  -0.0420   0.5986   0.0662
  -1.500   0.2358   0.01856   0.00871  -0.0414   0.5971   0.0735
  -1.250   0.2582   0.01836   0.00856  -0.0407   0.5958   0.0867
  -1.000   0.2715   0.01758   0.00850  -0.0385   0.5946   0.2635
   0.250   0.5013   0.02345   0.01619  -0.0499   0.5872   0.8932
   0.500   0.5495   0.02352   0.01623  -0.0540   0.5854   0.8987
   0.750   0.5727   0.02358   0.01626  -0.0536   0.5836   0.8999
   1.000   0.5940   0.02362   0.01627  -0.0529   0.5821   0.9004
   1.250   0.6147   0.02364   0.01627  -0.0521   0.5807   0.9005
   1.500   0.6358   0.02359   0.01617  -0.0512   0.5792   0.9005
   1.750   0.6567   0.02357   0.01612  -0.0504   0.5780   0.9006
   2.000   0.6791   0.02345   0.01593  -0.0497   0.5763   0.9010
   2.250   0.7006   0.02343   0.01586  -0.0488   0.5750   0.9014
   2.500   0.7146   0.02378   0.01631  -0.0472   0.5724   0.9016
   2.750   0.7284   0.02409   0.01668  -0.0455   0.5700   0.9019
   3.000   0.7419   0.02436   0.01699  -0.0436   0.5677   0.9022
   3.250   0.7550   0.02456   0.01721  -0.0416   0.5657   0.9026
   3.500   0.7686   0.02466   0.01732  -0.0395   0.5637   0.9030
   3.750   0.7848   0.02458   0.01723  -0.0377   0.5617   0.9033
   4.000   0.7996   0.02450   0.01713  -0.0356   0.5601   0.9042
   4.250   0.8167   0.02433   0.01692  -0.0338   0.5585   0.9047
   4.500   0.8296   0.02430   0.01689  -0.0314   0.5572   0.9051
   4.750   0.6144   0.03024   0.02323   0.0041   0.5449   0.9129
   5.000   0.6075   0.03020   0.02317   0.0099   0.5430   0.9142
   5.250   0.6138   0.02960   0.02253   0.0141   0.5418   0.9151
   5.500   0.6237   0.02886   0.02175   0.0179   0.5408   0.9161
   9.750   0.5539   0.04607   0.03931   0.0742   0.4088   0.9345
  10.000   0.5799   0.04575   0.03900   0.0741   0.4022   0.9349
  10.250   0.6061   0.04543   0.03866   0.0740   0.3943   0.9353
  10.500   0.6377   0.04470   0.03791   0.0735   0.3880   0.9357
  10.750   0.6698   0.04393   0.03709   0.0730   0.3812   0.9360
  11.000   0.7024   0.04310   0.03620   0.0724   0.3734   0.9364
  11.250   0.7336   0.04240   0.03544   0.0720   0.3657   0.9368
  11.500   0.7599   0.04211   0.03508   0.0718   0.3574   0.9372
  11.750   0.7850   0.04190   0.03480   0.0717   0.3496   0.9377
  12.000   0.8036   0.04221   0.03503   0.0719   0.3388   0.9383
  12.250   0.8239   0.04257   0.03532   0.0718   0.3300   0.9388
  12.500   0.8411   0.04333   0.03609   0.0716   0.3227   0.9393
  12.750   0.8608   0.04376   0.03644   0.0714   0.3139   0.9399
  13.000   0.8746   0.04492   0.03769   0.0712   0.3074   0.9405
  13.250   0.8895   0.04594   0.03872   0.0710   0.2998   0.9411
  13.500   0.9057   0.04682   0.03960   0.0708   0.2931   0.9418
  13.750   0.9166   0.04827   0.04116   0.0706   0.2852   0.9426
  14.000   0.9288   0.04952   0.04243   0.0705   0.2766   0.9435
  14.250   0.9374   0.05124   0.04423   0.0703   0.2643   0.9445
  14.500   0.9473   0.05283   0.04586   0.0701   0.2527   0.9455
  14.750   0.9544   0.05466   0.04768   0.0699   0.2380   0.9467
  15.000   0.9598   0.05668   0.04965   0.0698   0.2231   0.9478
  15.250   0.9642   0.05881   0.05175   0.0697   0.2090   0.9490
  15.500   0.9683   0.06100   0.05390   0.0695   0.1924   0.9501
  15.750   0.9710   0.06340   0.05626   0.0692   0.1716   0.9511
  16.000   0.9675   0.06643   0.05916   0.0691   0.1484   0.9521
  16.250   0.9664   0.06933   0.06199   0.0688   0.1368   0.9532
  16.750   0.9729   0.07473   0.06739   0.0672   0.1222   0.9551
  17.000   0.9760   0.07755   0.07023   0.0662   0.1167   0.9561
  17.250   0.9842   0.07991   0.07267   0.0651   0.1111   0.9572
  17.500   0.9886   0.08268   0.07549   0.0639   0.1059   0.9584
  17.750   0.9958   0.08523   0.07813   0.0626   0.1003   0.9596
  18.000   1.0020   0.08797   0.08094   0.0612   0.0929   0.9609
  18.250   1.0107   0.09048   0.08357   0.0598   0.0828   0.9623
  18.500   1.0132   0.09373   0.08681   0.0582   0.0717   0.9637
  18.750   1.0120   0.09746   0.09050   0.0566   0.0653   0.9651
  19.000   1.0122   0.10105   0.09412   0.0549   0.0615   0.9666
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