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HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il)
Reynolds number: 50,000
Max Cl/Cd: 30.24 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3513-il-50000.txt
Download as CSV file: xf-hq3513-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/13 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3301   0.11952   0.11294  -0.0357   1.0000   0.2395
  -9.500  -0.3078   0.11450   0.10793  -0.0336   1.0000   0.2498
  -9.250  -0.3441   0.11581   0.10946  -0.0327   1.0000   0.2553
  -9.000  -0.3205   0.11090   0.10454  -0.0304   1.0000   0.2680
  -8.750  -0.3187   0.10819   0.10189  -0.0282   1.0000   0.2774
  -8.500  -0.3501   0.10886   0.10276  -0.0257   1.0000   0.2855
  -8.250  -0.3452   0.10608   0.10002  -0.0230   1.0000   0.2999
  -8.000  -0.3423   0.10361   0.09760  -0.0202   1.0000   0.3136
  -7.750  -0.3450   0.10162   0.09570  -0.0173   1.0000   0.3274
  -7.500  -0.3496   0.09976   0.09392  -0.0143   1.0000   0.3410
  -7.250  -0.3562   0.09803   0.09227  -0.0113   1.0000   0.3544
  -6.750  -0.3746   0.09496   0.08939  -0.0049   1.0000   0.3818
  -6.500  -0.3764   0.09305   0.08754  -0.0017   1.0000   0.3993
  -6.250  -0.3850   0.09174   0.08631   0.0020   1.0000   0.4193
  -6.000  -0.4035   0.09109   0.08578   0.0063   1.0000   0.4371
  -5.750  -0.4244   0.09048   0.08528   0.0111   1.0000   0.4535
  -5.500  -0.5154   0.06287   0.05666  -0.0392   1.0000   0.1634
  -5.250  -0.4998   0.05697   0.05052  -0.0409   1.0000   0.1512
  -5.000  -0.4804   0.05226   0.04536  -0.0428   1.0000   0.1439
  -4.750  -0.4565   0.04712   0.03949  -0.0454   1.0000   0.1375
  -4.500  -0.4344   0.04404   0.03600  -0.0461   1.0000   0.1410
  -4.250  -0.4097   0.04114   0.03251  -0.0469   1.0000   0.1445
  -4.000  -0.3854   0.03866   0.02953  -0.0472   1.0000   0.1516
  -3.750  -0.3620   0.03683   0.02741  -0.0471   1.0000   0.1596
  -3.500  -0.3388   0.03518   0.02550  -0.0468   1.0000   0.1692
  -3.250  -0.3144   0.03394   0.02383  -0.0464   1.0000   0.1784
  -3.000  -0.2928   0.03283   0.02272  -0.0458   1.0000   0.1911
  -2.750  -0.2707   0.03185   0.02169  -0.0449   1.0000   0.2028
  -2.500  -0.2494   0.03114   0.02096  -0.0441   1.0000   0.2222
  -2.250  -0.2278   0.03037   0.02032  -0.0433   1.0000   0.2469
  -2.000  -0.2027   0.02941   0.01973  -0.0433   1.0000   0.3020
  -1.750  -0.1956   0.02834   0.02096  -0.0370   1.0000   0.6697
  -1.500  -0.2020   0.02877   0.02152  -0.0277   1.0000   0.7780
  -1.250  -0.2043   0.02870   0.02147  -0.0203   1.0000   0.8464
  -1.000  -0.1902   0.02842   0.02125  -0.0164   1.0000   0.9315
  -0.750  -0.1582   0.02832   0.02089  -0.0196   1.0000   1.0000
  -0.500  -0.1349   0.02870   0.02095  -0.0215   1.0000   1.0000
  -0.250  -0.1106   0.02924   0.02117  -0.0234   1.0000   1.0000
   0.000  -0.0863   0.02988   0.02153  -0.0251   1.0000   1.0000
   0.250  -0.0624   0.03060   0.02200  -0.0268   1.0000   1.0000
   0.500  -0.0107   0.03248   0.02354  -0.0334   0.9863   1.0000
   0.750   0.0423   0.03440   0.02517  -0.0400   0.9706   1.0000
   1.000   0.0829   0.03579   0.02632  -0.0442   0.9572   1.0000
   1.250   0.1209   0.03709   0.02743  -0.0479   0.9435   1.0000
   1.500   0.1577   0.03836   0.02854  -0.0511   0.9294   1.0000
   1.750   0.1942   0.03962   0.02966  -0.0542   0.9146   1.0000
   2.000   0.2422   0.04109   0.03098  -0.0587   0.8963   1.0000
   2.250   0.2738   0.04190   0.03169  -0.0604   0.8753   1.0000
   2.500   0.3186   0.04287   0.03256  -0.0637   0.8540   1.0000
   2.750   0.3634   0.04376   0.03337  -0.0667   0.8345   1.0000
   3.000   0.3920   0.04452   0.03409  -0.0676   0.8158   1.0000
   3.250   0.4256   0.04528   0.03482  -0.0690   0.7977   1.0000
   3.500   0.4625   0.04595   0.03548  -0.0706   0.7801   1.0000
   3.750   0.5024   0.04647   0.03600  -0.0723   0.7629   1.0000
   4.000   0.5448   0.04679   0.03634  -0.0741   0.7461   1.0000
   4.250   0.5648   0.04751   0.03709  -0.0734   0.7259   1.0000
   4.500   0.5974   0.04787   0.03749  -0.0738   0.7072   1.0000
   4.750   0.6373   0.04781   0.03749  -0.0747   0.6894   1.0000
   5.000   0.6802   0.04745   0.03722  -0.0755   0.6725   1.0000
   5.250   0.7241   0.04680   0.03665  -0.0762   0.6563   1.0000
   5.500   0.7361   0.04780   0.03770  -0.0744   0.6335   1.0000
   5.750   0.7729   0.04733   0.03734  -0.0742   0.6165   1.0000
   6.000   0.8133   0.04642   0.03653  -0.0740   0.6007   1.0000
   6.250   0.8541   0.04529   0.03553  -0.0736   0.5857   1.0000
   6.500   0.8962   0.04411   0.03447  -0.0734   0.5709   1.0000
   6.750   0.9445   0.04258   0.03309  -0.0738   0.5560   1.0000
   7.000   0.9940   0.04119   0.03182  -0.0746   0.5409   1.0000
   7.250   1.0416   0.03992   0.03065  -0.0752   0.5252   1.0000
   7.500   1.0868   0.03901   0.02984  -0.0758   0.5092   1.0000
   7.750   1.1312   0.03832   0.02919  -0.0766   0.4928   1.0000
   8.000   1.1639   0.03849   0.02940  -0.0764   0.4766   1.0000
   8.250   1.1867   0.03932   0.03033  -0.0755   0.4609   1.0000
   8.500   1.2097   0.04019   0.03128  -0.0745   0.4455   1.0000
   8.750   1.2324   0.04116   0.03233  -0.0736   0.4303   1.0000
   9.000   1.2543   0.04221   0.03347  -0.0726   0.4153   1.0000
   9.250   1.2754   0.04337   0.03474  -0.0715   0.4004   1.0000
   9.500   1.2951   0.04462   0.03608  -0.0703   0.3855   1.0000
   9.750   1.3136   0.04594   0.03750  -0.0690   0.3707   1.0000
  10.000   1.3314   0.04736   0.03901  -0.0676   0.3559   1.0000
  10.250   1.3480   0.04883   0.04058  -0.0662   0.3413   1.0000
  10.500   1.3646   0.05040   0.04227  -0.0647   0.3268   1.0000
  10.750   1.3312   0.05441   0.04664  -0.0592   0.3205   1.0000
  11.000   1.3407   0.05640   0.04874  -0.0573   0.3079   1.0000
  11.250   1.3551   0.05821   0.05064  -0.0558   0.2949   1.0000
  11.500   1.3039   0.06353   0.05618  -0.0501   0.2934   1.0000
  11.750   1.2280   0.07275   0.06549  -0.0470   0.2954   1.0000
  12.250   1.3585   0.06838   0.06129  -0.0465   0.2532   1.0000
  12.500   1.3104   0.07467   0.06774  -0.0433   0.2529   1.0000
  12.750   0.8162   0.15578   0.14758  -0.0874   0.4203   1.0000
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