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HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 100,000
Max Cl/Cd: 52.65 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2195-il-100000-n5.txt
Download as CSV file: xf-hq2195-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.1/9.5 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4878   0.07648   0.07142  -0.0455   1.0000   0.0330
  -8.750  -0.4970   0.07182   0.06680  -0.0479   1.0000   0.0327
  -8.500  -0.5077   0.06769   0.06269  -0.0498   1.0000   0.0324
  -8.250  -0.5164   0.06350   0.05845  -0.0509   1.0000   0.0321
  -8.000  -0.5242   0.05936   0.05423  -0.0514   1.0000   0.0319
  -7.750  -0.5296   0.05537   0.05011  -0.0513   1.0000   0.0317
  -7.500  -0.5329   0.05153   0.04608  -0.0506   1.0000   0.0315
  -7.250  -0.5339   0.04784   0.04216  -0.0495   1.0000   0.0315
  -7.000  -0.5323   0.04431   0.03833  -0.0482   1.0000   0.0315
  -6.750  -0.5275   0.04090   0.03451  -0.0468   1.0000   0.0321
  -6.500  -0.5186   0.03807   0.03108  -0.0453   1.0000   0.0332
  -6.250  -0.4926   0.03436   0.02708  -0.0476   0.9955   0.0343
  -6.000  -0.4632   0.03148   0.02378  -0.0494   0.9906   0.0348
  -5.750  -0.4322   0.02908   0.02099  -0.0510   0.9858   0.0356
  -5.500  -0.4002   0.02703   0.01858  -0.0526   0.9816   0.0366
  -5.250  -0.3698   0.02560   0.01689  -0.0536   0.9763   0.0390
  -5.000  -0.3372   0.02413   0.01509  -0.0548   0.9722   0.0414
  -4.750  -0.3041   0.02270   0.01339  -0.0559   0.9688   0.0427
  -4.500  -0.2755   0.02142   0.01197  -0.0562   0.9634   0.0441
  -4.250  -0.2443   0.02028   0.01085  -0.0573   0.9592   0.0465
  -4.000  -0.2103   0.01951   0.01005  -0.0588   0.9559   0.0513
  -3.750  -0.1824   0.01885   0.00930  -0.0590   0.9502   0.0558
  -3.500  -0.1520   0.01805   0.00850  -0.0599   0.9457   0.0616
  -3.250  -0.1181   0.01741   0.00784  -0.0614   0.9423   0.0733
  -3.000  -0.0881   0.01683   0.00729  -0.0621   0.9373   0.0950
  -2.750  -0.0596   0.01599   0.00680  -0.0628   0.9322   0.1616
  -2.500  -0.0335   0.01439   0.00668  -0.0636   0.9284   0.4958
  -2.250  -0.0068   0.01421   0.00686  -0.0629   0.9239   0.6174
  -2.000   0.0173   0.01424   0.00698  -0.0617   0.9178   0.6799
  -1.750   0.0436   0.01428   0.00711  -0.0605   0.9135   0.7373
  -1.500   0.0664   0.01434   0.00724  -0.0586   0.9083   0.7814
  -1.250   0.0899   0.01437   0.00726  -0.0573   0.9022   0.8077
  -1.000   0.1216   0.01432   0.00712  -0.0578   0.8979   0.8231
  -0.750   0.1499   0.01423   0.00696  -0.0575   0.8888   0.8374
  -0.500   0.1851   0.01399   0.00665  -0.0582   0.8800   0.8511
  -0.250   0.2145   0.01380   0.00640  -0.0579   0.8685   0.8657
   0.000   0.2420   0.01368   0.00626  -0.0574   0.8588   0.8816
   0.250   0.2742   0.01354   0.00609  -0.0579   0.8522   0.8979
   0.500   0.3040   0.01346   0.00603  -0.0581   0.8433   0.9164
   0.750   0.3423   0.01332   0.00587  -0.0598   0.8368   0.9352
   1.000   0.3804   0.01326   0.00583  -0.0619   0.8273   0.9596
   1.250   0.4205   0.01316   0.00572  -0.0644   0.8187   1.0000
   1.500   0.4475   0.01317   0.00570  -0.0642   0.8085   1.0000
   1.750   0.4736   0.01322   0.00575  -0.0640   0.7968   1.0000
   2.000   0.5008   0.01324   0.00576  -0.0637   0.7852   1.0000
   2.250   0.5283   0.01326   0.00578  -0.0635   0.7727   1.0000
   2.500   0.5554   0.01329   0.00582  -0.0631   0.7588   1.0000
   2.750   0.5820   0.01332   0.00587  -0.0626   0.7430   1.0000
   3.000   0.6084   0.01336   0.00593  -0.0621   0.7250   1.0000
   3.250   0.6350   0.01339   0.00597  -0.0615   0.7046   1.0000
   3.500   0.6602   0.01345   0.00607  -0.0606   0.6786   1.0000
   3.750   0.6853   0.01351   0.00609  -0.0597   0.6441   1.0000
   4.000   0.7094   0.01361   0.00606  -0.0585   0.5906   1.0000
   4.250   0.7323   0.01391   0.00602  -0.0570   0.5255   1.0000
   4.500   0.7538   0.01447   0.00623  -0.0556   0.4699   1.0000
   4.750   0.7758   0.01504   0.00659  -0.0546   0.4266   1.0000
   5.000   0.7983   0.01560   0.00700  -0.0537   0.3913   1.0000
   5.250   0.8210   0.01614   0.00748  -0.0529   0.3587   1.0000
   5.500   0.8434   0.01669   0.00795  -0.0521   0.3253   1.0000
   5.750   0.8654   0.01729   0.00845  -0.0512   0.2909   1.0000
   6.000   0.8868   0.01793   0.00899  -0.0503   0.2483   1.0000
   6.250   0.9066   0.01877   0.00962  -0.0493   0.1963   1.0000
   6.500   0.9252   0.01982   0.01037  -0.0482   0.1505   1.0000
   6.750   0.9440   0.02091   0.01124  -0.0472   0.1195   1.0000
   7.000   0.9636   0.02189   0.01216  -0.0462   0.0994   1.0000
   7.250   0.9828   0.02289   0.01315  -0.0452   0.0856   1.0000
   7.500   1.0012   0.02396   0.01427  -0.0440   0.0754   1.0000
   7.750   1.0182   0.02513   0.01541  -0.0427   0.0668   1.0000
   8.000   1.0367   0.02617   0.01658  -0.0415   0.0595   1.0000
   8.250   1.0517   0.02755   0.01794  -0.0400   0.0549   1.0000
   8.500   1.0696   0.02880   0.01938  -0.0386   0.0513   1.0000
   8.750   1.0870   0.03012   0.02082  -0.0374   0.0479   1.0000
   9.000   1.1029   0.03151   0.02223  -0.0362   0.0449   1.0000
   9.250   1.1203   0.03306   0.02393  -0.0350   0.0423   1.0000
   9.500   1.1385   0.03472   0.02581  -0.0339   0.0401   1.0000
   9.750   1.1557   0.03648   0.02776  -0.0328   0.0384   1.0000
  10.000   1.1707   0.03812   0.02956  -0.0316   0.0366   1.0000
  10.250   1.1838   0.03991   0.03139  -0.0304   0.0348   1.0000
  10.500   1.1954   0.04214   0.03390  -0.0289   0.0333   1.0000
  10.750   1.2041   0.04458   0.03669  -0.0271   0.0323   1.0000
  11.000   1.2084   0.04714   0.03958  -0.0249   0.0313   1.0000
  11.250   1.2086   0.04963   0.04236  -0.0227   0.0303   1.0000
  11.500   1.2062   0.05211   0.04509  -0.0205   0.0294   1.0000
  11.750   1.2024   0.05455   0.04774  -0.0188   0.0285   1.0000
  12.000   1.1979   0.05715   0.05051  -0.0175   0.0278   1.0000
  12.250   1.1927   0.06004   0.05354  -0.0166   0.0273   1.0000
  12.500   1.1849   0.06351   0.05717  -0.0161   0.0268   1.0000
  12.750   1.1725   0.06780   0.06166  -0.0162   0.0265   1.0000
  13.000   1.1556   0.07283   0.06691  -0.0172   0.0264   1.0000
  13.250   1.1352   0.07865   0.07299  -0.0192   0.0263   1.0000
  13.500   1.1140   0.08520   0.07977  -0.0224   0.0263   1.0000
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