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HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/9 AIRFOIL (hq109-il)
Reynolds number: 200,000
Max Cl/Cd: 55.28 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq109-il-200000-n5.txt
Download as CSV file: xf-hq109-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/9 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4730   0.11466   0.11130  -0.0038   1.0000   0.0110
 -11.250  -0.4789   0.10827   0.10493  -0.0062   1.0000   0.0105
 -10.500  -0.5767   0.10012   0.09654  -0.0080   1.0000   0.0098
 -10.250  -0.5803   0.09467   0.09114  -0.0106   1.0000   0.0097
 -10.000  -0.5857   0.08883   0.08534  -0.0136   1.0000   0.0096
  -9.750  -0.5916   0.08309   0.07965  -0.0169   1.0000   0.0095
  -9.500  -0.6016   0.07584   0.07245  -0.0215   1.0000   0.0094
  -9.250  -0.6140   0.06659   0.06327  -0.0294   1.0000   0.0092
  -9.000  -0.6324   0.05945   0.05606  -0.0349   1.0000   0.0091
  -8.750  -0.6497   0.05440   0.05087  -0.0363   1.0000   0.0090
  -8.500  -0.6608   0.04898   0.04523  -0.0371   1.0000   0.0089
  -8.250  -0.6680   0.04330   0.03919  -0.0369   1.0000   0.0089
  -8.000  -0.6686   0.03818   0.03362  -0.0361   1.0000   0.0089
  -7.750  -0.6631   0.03371   0.02864  -0.0349   1.0000   0.0090
  -7.500  -0.6523   0.03007   0.02450  -0.0336   1.0000   0.0091
  -7.250  -0.6375   0.02713   0.02110  -0.0322   1.0000   0.0094
  -7.000  -0.6200   0.02483   0.01834  -0.0309   1.0000   0.0097
  -6.750  -0.6033   0.02227   0.01543  -0.0294   1.0000   0.0103
  -6.500  -0.5840   0.02115   0.01422  -0.0285   1.0000   0.0118
  -6.250  -0.5635   0.02032   0.01327  -0.0274   1.0000   0.0133
  -6.000  -0.5440   0.01894   0.01170  -0.0260   1.0000   0.0143
  -5.750  -0.5249   0.01773   0.01033  -0.0245   1.0000   0.0153
  -5.500  -0.5060   0.01679   0.00925  -0.0229   1.0000   0.0163
  -5.250  -0.4775   0.01557   0.00798  -0.0236   0.9954   0.0195
  -5.000  -0.4440   0.01492   0.00719  -0.0251   0.9889   0.0247
  -4.750  -0.4103   0.01399   0.00620  -0.0267   0.9831   0.0325
  -4.500  -0.3772   0.01340   0.00558  -0.0281   0.9762   0.0454
  -4.250  -0.3433   0.01291   0.00509  -0.0296   0.9700   0.0635
  -4.000  -0.3115   0.01236   0.00462  -0.0308   0.9620   0.0889
  -3.750  -0.2794   0.01178   0.00419  -0.0321   0.9544   0.1282
  -3.500  -0.2477   0.01124   0.00381  -0.0333   0.9464   0.1893
  -3.250  -0.2186   0.01057   0.00347  -0.0341   0.9372   0.2752
  -3.000  -0.1907   0.00976   0.00323  -0.0346   0.9285   0.4241
  -2.750  -0.1630   0.00933   0.00314  -0.0346   0.9193   0.5265
  -2.500  -0.1350   0.00914   0.00306  -0.0345   0.9100   0.5865
  -2.250  -0.1069   0.00901   0.00302  -0.0342   0.9014   0.6360
  -2.000  -0.0799   0.00894   0.00300  -0.0337   0.8917   0.6744
  -1.750  -0.0530   0.00889   0.00295  -0.0332   0.8817   0.6990
  -1.500  -0.0261   0.00886   0.00289  -0.0327   0.8722   0.7199
  -1.250   0.0006   0.00884   0.00284  -0.0322   0.8629   0.7391
  -1.000   0.0268   0.00881   0.00281  -0.0316   0.8524   0.7555
  -0.750   0.0529   0.00879   0.00278  -0.0309   0.8418   0.7721
  -0.500   0.0789   0.00877   0.00274  -0.0302   0.8317   0.7882
  -0.250   0.1052   0.00875   0.00271  -0.0297   0.8221   0.8022
   0.000   0.1316   0.00874   0.00269  -0.0292   0.8117   0.8140
   0.250   0.1577   0.00872   0.00266  -0.0286   0.7993   0.8259
   0.500   0.1836   0.00870   0.00263  -0.0279   0.7854   0.8384
   0.750   0.2096   0.00868   0.00260  -0.0272   0.7711   0.8515
   1.000   0.2357   0.00866   0.00258  -0.0266   0.7564   0.8655
   1.250   0.2626   0.00865   0.00258  -0.0261   0.7425   0.8808
   1.500   0.2908   0.00864   0.00260  -0.0259   0.7283   0.8974
   1.750   0.3210   0.00865   0.00263  -0.0262   0.7137   0.9153
   2.000   0.3540   0.00868   0.00266  -0.0271   0.6978   0.9346
   2.250   0.3887   0.00871   0.00270  -0.0284   0.6793   0.9563
   2.500   0.4246   0.00877   0.00277  -0.0301   0.6575   0.9780
   2.750   0.4589   0.00887   0.00282  -0.0315   0.6300   1.0000
   3.000   0.4826   0.00903   0.00289  -0.0307   0.5978   1.0000
   3.250   0.5062   0.00924   0.00297  -0.0298   0.5582   1.0000
   3.500   0.5290   0.00957   0.00311  -0.0289   0.5025   1.0000
   3.750   0.5510   0.01003   0.00329  -0.0278   0.4360   1.0000
   4.000   0.5733   0.01054   0.00355  -0.0270   0.3732   1.0000
   4.250   0.5956   0.01112   0.00386  -0.0263   0.3123   1.0000
   4.750   0.6425   0.01214   0.00464  -0.0251   0.2340   1.0000
   5.000   0.6664   0.01263   0.00503  -0.0247   0.2002   1.0000
   5.250   0.6898   0.01318   0.00544  -0.0242   0.1597   1.0000
   5.500   0.7126   0.01384   0.00592  -0.0236   0.1195   1.0000
   5.750   0.7356   0.01450   0.00647  -0.0230   0.0898   1.0000
   6.000   0.7588   0.01514   0.00706  -0.0224   0.0706   1.0000
   6.250   0.7815   0.01585   0.00772  -0.0218   0.0541   1.0000
   6.500   0.8043   0.01653   0.00846  -0.0212   0.0397   1.0000
   6.750   0.8269   0.01725   0.00915  -0.0206   0.0271   1.0000
   7.000   0.8483   0.01818   0.01010  -0.0197   0.0199   1.0000
   7.250   0.8694   0.01915   0.01119  -0.0188   0.0153   1.0000
   7.500   0.8870   0.02067   0.01283  -0.0173   0.0127   1.0000
   7.750   0.9077   0.02166   0.01399  -0.0164   0.0111   1.0000
   8.000   0.9286   0.02256   0.01499  -0.0156   0.0093   1.0000
   8.250   0.9473   0.02378   0.01632  -0.0146   0.0084   1.0000
   8.500   0.9622   0.02570   0.01847  -0.0131   0.0078   1.0000
   8.750   0.9779   0.02761   0.02060  -0.0116   0.0075   1.0000
   9.000   0.9936   0.02953   0.02279  -0.0103   0.0072   1.0000
   9.250   1.0073   0.03173   0.02527  -0.0087   0.0070   1.0000
   9.500   1.0183   0.03419   0.02807  -0.0071   0.0068   1.0000
   9.750   1.0255   0.03692   0.03114  -0.0052   0.0067   1.0000
  10.000   1.0275   0.03995   0.03454  -0.0030   0.0065   1.0000
  10.250   1.0237   0.04294   0.03786  -0.0005   0.0065   1.0000
  10.500   1.0131   0.04605   0.04127   0.0023   0.0065   1.0000
  10.750   1.0000   0.04946   0.04494   0.0040   0.0065   1.0000
  11.000   0.9852   0.05334   0.04906   0.0044   0.0065   1.0000
  11.250   0.9677   0.05806   0.05401   0.0035   0.0065   1.0000
  11.500   0.9495   0.06359   0.05974   0.0009   0.0065   1.0000
  11.750   0.9319   0.06997   0.06630  -0.0031   0.0066   1.0000
  12.000   0.9119   0.07820   0.07470  -0.0092   0.0067   1.0000
  12.250   0.8899   0.08875   0.08539  -0.0170   0.0068   1.0000
  12.500   0.8667   0.10095   0.09767  -0.0248   0.0069   1.0000
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