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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 100,000
Max Cl/Cd: 58.62 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3512-il-100000.txt
Download as CSV file: xf-hq3512-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3497   0.10542   0.10085  -0.0431   1.0000   0.0943
  -9.000  -0.3762   0.10450   0.10010  -0.0427   1.0000   0.0949
  -8.750  -0.4032   0.10355   0.09928  -0.0413   1.0000   0.0952
  -8.500  -0.3805   0.09838   0.09409  -0.0374   1.0000   0.0975
  -8.250  -0.3790   0.09640   0.09214  -0.0342   1.0000   0.0996
  -8.000  -0.3888   0.09481   0.09063  -0.0316   1.0000   0.1019
  -7.750  -0.4045   0.09333   0.08924  -0.0292   1.0000   0.1035
  -7.500  -0.4248   0.09196   0.08797  -0.0269   1.0000   0.1050
  -7.250  -0.4489   0.09069   0.08680  -0.0244   1.0000   0.1060
  -7.000  -0.4750   0.08825   0.08446  -0.0257   1.0000   0.1078
  -6.750  -0.5106   0.08368   0.07978  -0.0354   1.0000   0.1096
  -6.500  -0.5091   0.07934   0.07553  -0.0337   0.9998   0.1112
  -6.250  -0.4851   0.07710   0.07336  -0.0307   0.9967   0.1153
  -6.000  -0.4694   0.06959   0.06556  -0.0440   0.9886   0.1263
  -5.750  -0.4448   0.06670   0.06274  -0.0442   0.9844   0.1323
  -5.500  -0.4261   0.06192   0.05780  -0.0496   0.9780   0.1442
  -5.250  -0.4028   0.05837   0.05414  -0.0531   0.9725   0.1603
  -5.000  -0.3258   0.03246   0.02712  -0.0665   0.9544   0.0980
  -4.750  -0.3173   0.03854   0.03131  -0.0672   0.9637   0.0675
  -4.500  -0.3129   0.04500   0.03968  -0.0677   0.9567   0.1857
  -4.250  -0.2451   0.03173   0.02354  -0.0716   0.9564   0.0689
  -4.000  -0.2184   0.03045   0.02217  -0.0721   0.9507   0.0764
  -3.750  -0.1843   0.02860   0.01997  -0.0732   0.9459   0.0850
  -3.500  -0.1458   0.02748   0.01876  -0.0755   0.9420   0.1017
  -3.250  -0.1203   0.02662   0.01784  -0.0754   0.9358   0.1152
  -3.000  -0.0870   0.02577   0.01695  -0.0764   0.9306   0.1281
  -2.750  -0.0472   0.02506   0.01637  -0.0787   0.9268   0.1468
  -2.500  -0.0271   0.02456   0.01595  -0.0776   0.9190   0.1656
  -2.250   0.0084   0.02318   0.01536  -0.0798   0.9145   0.2802
  -2.000   0.0214   0.02268   0.01636  -0.0759   0.9078   0.6689
  -1.750   0.0433   0.02312   0.01680  -0.0736   0.9009   0.7306
  -1.500   0.0637   0.02345   0.01710  -0.0712   0.8940   0.7716
  -1.250   0.0838   0.02361   0.01722  -0.0690   0.8866   0.8055
  -1.000   0.1040   0.02369   0.01727  -0.0666   0.8800   0.8409
  -0.750   0.1151   0.02358   0.01722  -0.0622   0.8720   0.8873
  -0.500   0.1705   0.02344   0.01710  -0.0655   0.8688   0.9616
  -0.250   0.2190   0.02365   0.01717  -0.0708   0.8607   1.0000
   0.000   0.2603   0.02366   0.01702  -0.0742   0.8550   1.0000
   0.250   0.2813   0.02395   0.01719  -0.0745   0.8450   1.0000
   0.500   0.3295   0.02392   0.01702  -0.0786   0.8401   1.0000
   0.750   0.3560   0.02416   0.01715  -0.0793   0.8292   1.0000
   1.000   0.4170   0.02358   0.01646  -0.0845   0.8245   1.0000
   1.250   0.4483   0.02350   0.01630  -0.0853   0.8125   1.0000
   1.500   0.4873   0.02320   0.01593  -0.0870   0.8023   1.0000
   1.750   0.5397   0.02245   0.01512  -0.0904   0.7968   1.0000
   2.000   0.5675   0.02251   0.01513  -0.0905   0.7861   1.0000
   2.250   0.6155   0.02183   0.01443  -0.0931   0.7816   1.0000
   2.500   0.6416   0.02189   0.01447  -0.0928   0.7704   1.0000
   2.750   0.6876   0.02116   0.01371  -0.0949   0.7654   1.0000
   3.000   0.7150   0.02107   0.01364  -0.0946   0.7539   1.0000
   3.250   0.7444   0.02090   0.01347  -0.0944   0.7428   1.0000
   3.500   0.7832   0.02030   0.01286  -0.0953   0.7344   1.0000
   3.750   0.8173   0.01984   0.01244  -0.0955   0.7235   1.0000
   4.000   0.8467   0.01955   0.01217  -0.0951   0.7103   1.0000
   4.250   0.8771   0.01922   0.01184  -0.0948   0.6964   1.0000
   4.500   0.9081   0.01884   0.01150  -0.0945   0.6814   1.0000
   4.750   0.9395   0.01844   0.01109  -0.0942   0.6649   1.0000
   5.000   0.9648   0.01827   0.01094  -0.0931   0.6440   1.0000
   5.250   0.9931   0.01799   0.01064  -0.0924   0.6214   1.0000
   5.500   1.0171   0.01791   0.01052  -0.0911   0.5936   1.0000
   5.750   1.0414   0.01790   0.01041  -0.0898   0.5627   1.0000
   6.000   1.0628   0.01813   0.01050  -0.0882   0.5279   1.0000
   6.250   1.0840   0.01854   0.01075  -0.0867   0.4944   1.0000
   6.500   1.1053   0.01912   0.01114  -0.0855   0.4647   1.0000
   6.750   1.1269   0.01980   0.01165  -0.0844   0.4395   1.0000
   7.000   1.1490   0.02051   0.01223  -0.0835   0.4179   1.0000
   7.250   1.1714   0.02127   0.01292  -0.0827   0.3989   1.0000
   7.500   1.1928   0.02203   0.01366  -0.0817   0.3813   1.0000
   7.750   1.2142   0.02279   0.01441  -0.0808   0.3650   1.0000
   8.000   1.2352   0.02357   0.01518  -0.0799   0.3496   1.0000
   8.250   1.2557   0.02435   0.01600  -0.0788   0.3345   1.0000
   8.500   1.2760   0.02517   0.01684  -0.0778   0.3202   1.0000
   8.750   1.2957   0.02603   0.01772  -0.0767   0.3060   1.0000
   9.000   1.3151   0.02694   0.01867  -0.0756   0.2920   1.0000
   9.250   1.3337   0.02790   0.01967  -0.0744   0.2778   1.0000
   9.500   1.3514   0.02890   0.02075  -0.0731   0.2637   1.0000
   9.750   1.3673   0.02990   0.02181  -0.0715   0.2495   1.0000
  10.000   1.3809   0.03088   0.02285  -0.0696   0.2353   1.0000
  10.250   1.3924   0.03182   0.02387  -0.0674   0.2216   1.0000
  10.500   1.4008   0.03270   0.02481  -0.0648   0.2082   1.0000
  10.750   1.4066   0.03353   0.02568  -0.0618   0.1958   1.0000
  11.000   1.4064   0.03432   0.02655  -0.0581   0.1841   1.0000
  11.250   1.4030   0.03531   0.02770  -0.0542   0.1725   1.0000
  11.500   1.3995   0.03646   0.02898  -0.0507   0.1610   1.0000
  11.750   1.3954   0.03779   0.03038  -0.0476   0.1495   1.0000
  12.000   1.3903   0.03936   0.03200  -0.0449   0.1379   1.0000
  12.250   1.3839   0.04123   0.03391  -0.0425   0.1262   1.0000
  12.500   1.3768   0.04347   0.03616  -0.0405   0.1143   1.0000
  12.750   1.3691   0.04608   0.03877  -0.0388   0.1027   1.0000
  13.000   1.3602   0.04912   0.04190  -0.0375   0.0910   1.0000
  13.250   1.3500   0.05260   0.04546  -0.0364   0.0798   1.0000
  13.500   1.3381   0.05655   0.04948  -0.0357   0.0692   1.0000
  13.750   1.3254   0.06087   0.05386  -0.0353   0.0601   1.0000
  14.000   1.3151   0.06513   0.05807  -0.0350   0.0538   1.0000
  14.250   1.3082   0.06926   0.06238  -0.0350   0.0485   1.0000
  14.500   1.3052   0.07305   0.06606  -0.0346   0.0442   1.0000
  14.750   1.3017   0.07718   0.07048  -0.0348   0.0415   1.0000
  15.000   1.2997   0.08112   0.07459  -0.0351   0.0393   1.0000
  15.250   1.2987   0.08493   0.07850  -0.0354   0.0375   1.0000
  15.500   1.3043   0.08828   0.08183  -0.0350   0.0354   1.0000
  15.750   1.2954   0.09351   0.08731  -0.0363   0.0347   1.0000
  16.000   1.2836   0.09920   0.09332  -0.0384   0.0343   1.0000
  16.250   1.2702   0.10538   0.09977  -0.0410   0.0339   1.0000
  16.500   1.2552   0.11211   0.10676  -0.0443   0.0337   1.0000
  16.750   1.2386   0.11942   0.11431  -0.0483   0.0337   1.0000
  17.000   1.2201   0.12749   0.12258  -0.0531   0.0339   1.0000
  17.250   1.2000   0.13634   0.13163  -0.0586   0.0341   1.0000
  17.500   1.1796   0.14574   0.14120  -0.0647   0.0346   1.0000
  17.750   1.1588   0.15575   0.15134  -0.0712   0.0351   1.0000
  18.000   1.0578   0.19629   0.19194  -0.0968   0.0441   1.0000
  18.250   1.0547   0.20418   0.19979  -0.1007   0.0444   1.0000
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