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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 100,000
Max Cl/Cd: 47.79 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1010-il-100000.txt
Download as CSV file: xf-hq1010-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5673   0.09756   0.09283  -0.0204   1.0000   0.1211
  -9.250  -0.5383   0.09463   0.08985  -0.0151   1.0000   0.1292
  -9.000  -0.5561   0.09000   0.08533  -0.0203   1.0000   0.1339
  -8.750  -0.5579   0.08538   0.08078  -0.0215   1.0000   0.1382
  -8.500  -0.5502   0.08220   0.07762  -0.0211   1.0000   0.1437
  -8.250  -0.5887   0.07652   0.07204  -0.0290   1.0000   0.1479
  -7.750  -0.6373   0.05186   0.04636  -0.0384   1.0000   0.0643
  -7.500  -0.6343   0.04718   0.04137  -0.0375   1.0000   0.0622
  -7.250  -0.6293   0.04266   0.03640  -0.0361   1.0000   0.0606
  -7.000  -0.6212   0.03836   0.03157  -0.0343   1.0000   0.0591
  -6.750  -0.6106   0.03422   0.02672  -0.0320   1.0000   0.0575
  -6.500  -0.5950   0.03125   0.02334  -0.0302   1.0000   0.0579
  -6.250  -0.5773   0.02885   0.02068  -0.0285   1.0000   0.0602
  -6.000  -0.5593   0.02721   0.01866  -0.0267   1.0000   0.0659
  -5.750  -0.5411   0.02488   0.01616  -0.0251   1.0000   0.0712
  -5.500  -0.5219   0.02339   0.01446  -0.0233   1.0000   0.0792
  -5.250  -0.5040   0.02186   0.01291  -0.0217   1.0000   0.0905
  -5.000  -0.4860   0.02050   0.01156  -0.0200   1.0000   0.1034
  -4.750  -0.4684   0.01936   0.01044  -0.0182   1.0000   0.1188
  -4.500  -0.4514   0.01830   0.00949  -0.0166   1.0000   0.1379
  -4.250  -0.4345   0.01731   0.00864  -0.0148   1.0000   0.1621
  -4.000  -0.4187   0.01617   0.00791  -0.0132   1.0000   0.2109
  -3.750  -0.4080   0.01412   0.00719  -0.0110   1.0000   0.4131
  -3.500  -0.3971   0.01372   0.00753  -0.0073   1.0000   0.5947
  -3.250  -0.3831   0.01387   0.00778  -0.0041   1.0000   0.6660
  -3.000  -0.3689   0.01408   0.00797  -0.0010   1.0000   0.7143
  -2.750  -0.3555   0.01427   0.00817   0.0023   1.0000   0.7503
  -2.500  -0.3426   0.01442   0.00829   0.0055   1.0000   0.7840
  -2.250  -0.3309   0.01452   0.00836   0.0091   1.0000   0.8155
  -2.000  -0.3199   0.01457   0.00842   0.0128   1.0000   0.8477
  -1.750  -0.3002   0.01471   0.00853   0.0150   0.9966   0.8843
  -1.500  -0.2596   0.01505   0.00879   0.0132   0.9899   0.9180
  -1.250  -0.2031   0.01546   0.00903   0.0076   0.9847   0.9429
  -1.000  -0.1306   0.01595   0.00934  -0.0011   0.9823   0.9637
  -0.750  -0.0545   0.01626   0.00948  -0.0108   0.9799   0.9804
  -0.500   0.0122   0.01635   0.00947  -0.0193   0.9749   0.9915
  -0.250   0.0758   0.01643   0.00946  -0.0275   0.9700   1.0000
   0.000   0.1142   0.01641   0.00940  -0.0311   0.9590   1.0000
   0.250   0.1527   0.01642   0.00938  -0.0345   0.9483   1.0000
   0.500   0.2047   0.01642   0.00937  -0.0400   0.9409   1.0000
   0.750   0.2505   0.01630   0.00926  -0.0441   0.9287   1.0000
   1.000   0.3079   0.01596   0.00897  -0.0495   0.9157   1.0000
   1.250   0.3547   0.01559   0.00863  -0.0528   0.9014   1.0000
   1.500   0.3863   0.01541   0.00848  -0.0536   0.8873   1.0000
   1.750   0.4114   0.01532   0.00843  -0.0531   0.8730   1.0000
   2.000   0.4332   0.01526   0.00843  -0.0518   0.8584   1.0000
   2.250   0.4533   0.01523   0.00842  -0.0501   0.8436   1.0000
   2.500   0.4736   0.01519   0.00841  -0.0482   0.8285   1.0000
   2.750   0.4925   0.01520   0.00844  -0.0461   0.8120   1.0000
   3.000   0.5118   0.01520   0.00850  -0.0439   0.7941   1.0000
   3.250   0.5337   0.01510   0.00843  -0.0419   0.7759   1.0000
   3.500   0.5573   0.01489   0.00824  -0.0399   0.7572   1.0000
   3.750   0.5783   0.01477   0.00816  -0.0377   0.7331   1.0000
   4.000   0.6008   0.01459   0.00804  -0.0356   0.7072   1.0000
   4.250   0.6233   0.01440   0.00786  -0.0335   0.6769   1.0000
   4.500   0.6455   0.01427   0.00771  -0.0314   0.6399   1.0000
   4.750   0.6668   0.01423   0.00761  -0.0293   0.5920   1.0000
   5.000   0.6872   0.01438   0.00757  -0.0271   0.5319   1.0000
   5.250   0.7063   0.01486   0.00777  -0.0250   0.4625   1.0000
   5.500   0.7247   0.01561   0.00818  -0.0232   0.3965   1.0000
   5.750   0.7428   0.01650   0.00875  -0.0216   0.3386   1.0000
   6.000   0.7607   0.01755   0.00949  -0.0200   0.2859   1.0000
   6.250   0.7779   0.01876   0.01039  -0.0185   0.2366   1.0000
   6.500   0.7959   0.01998   0.01138  -0.0171   0.1927   1.0000
   6.750   0.8145   0.02112   0.01242  -0.0157   0.1570   1.0000
   7.000   0.8336   0.02244   0.01360  -0.0145   0.1304   1.0000
   7.250   0.8534   0.02407   0.01509  -0.0134   0.1102   1.0000
   7.500   0.8736   0.02563   0.01669  -0.0122   0.0924   1.0000
   7.750   0.8954   0.02765   0.01875  -0.0112   0.0795   1.0000
   8.000   0.9162   0.02971   0.02088  -0.0102   0.0684   1.0000
   8.250   0.9366   0.03223   0.02341  -0.0095   0.0597   1.0000
   8.500   0.9555   0.03435   0.02600  -0.0080   0.0536   1.0000
   8.750   0.9742   0.03732   0.02906  -0.0071   0.0497   1.0000
   9.000   0.9851   0.04080   0.03306  -0.0052   0.0470   1.0000
   9.250   0.9930   0.04379   0.03661  -0.0030   0.0447   1.0000
   9.500   0.9969   0.04745   0.04075  -0.0009   0.0436   1.0000
   9.750   0.9949   0.05158   0.04533   0.0014   0.0437   1.0000
  10.000   0.9861   0.05589   0.05004   0.0037   0.0439   1.0000
  10.250   0.9726   0.06001   0.05448   0.0058   0.0444   1.0000
  10.500   0.9532   0.06387   0.05857   0.0081   0.0448   1.0000
  10.750   0.9325   0.06804   0.06293   0.0088   0.0453   1.0000
  11.000   0.9113   0.07276   0.06780   0.0080   0.0458   1.0000
  11.250   0.8878   0.07851   0.07368   0.0055   0.0464   1.0000
  11.500   0.8677   0.08482   0.08008   0.0020   0.0470   1.0000
  11.750   0.8525   0.09154   0.08683  -0.0016   0.0478   1.0000
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