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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 200,000
Max Cl/Cd: 88.56 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq359-il-200000.txt
Download as CSV file: xf-hq359-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/9 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3749   0.08885   0.08578  -0.0284   1.0000   0.0323
  -7.250  -0.3913   0.08775   0.08476  -0.0252   1.0000   0.0325
  -7.000  -0.4100   0.08668   0.08377  -0.0219   1.0000   0.0326
  -6.750  -0.4220   0.08490   0.08205  -0.0205   1.0000   0.0329
  -6.500  -0.3973   0.07951   0.07664  -0.0293   0.9950   0.0344
  -6.250  -0.3714   0.07357   0.07067  -0.0397   0.9889   0.0362
  -6.000  -0.3325   0.06620   0.06315  -0.0554   0.9832   0.0388
  -5.750  -0.2929   0.06121   0.05771  -0.0675   0.9752   0.0403
  -5.500  -0.2698   0.05325   0.04961  -0.0738   0.9713   0.0414
  -5.250  -0.2430   0.04900   0.04540  -0.0772   0.9690   0.0432
  -5.000  -0.2222   0.04587   0.04217  -0.0790   0.9620   0.0452
  -4.750  -0.1863   0.04199   0.03798  -0.0837   0.9583   0.0494
  -4.500  -0.1431   0.03725   0.03263  -0.0895   0.9558   0.0554
  -4.250  -0.1215   0.03458   0.02992  -0.0900   0.9490   0.0578
  -4.000  -0.0820   0.03210   0.02681  -0.0932   0.9453   0.0685
  -3.750  -0.0364   0.02813   0.02217  -0.0942   0.9434   0.0404
  -3.500   0.0016   0.02350   0.01717  -0.0970   0.9420   0.0381
  -3.250   0.0269   0.02103   0.01433  -0.0962   0.9352   0.0345
  -3.000   0.0646   0.01887   0.01178  -0.0974   0.9325   0.0327
  -2.750   0.1037   0.01738   0.01011  -0.0993   0.9303   0.0339
  -2.500   0.1447   0.01620   0.00884  -0.1015   0.9287   0.0385
  -2.250   0.1698   0.01549   0.00814  -0.1010   0.9214   0.0521
  -2.000   0.2079   0.01434   0.00713  -0.1032   0.9182   0.1059
  -1.750   0.2399   0.01229   0.00698  -0.1048   0.9158   0.6262
  -1.500   0.2634   0.01224   0.00701  -0.1034   0.9083   0.7074
  -1.250   0.2950   0.01207   0.00688  -0.1034   0.9039   0.7620
  -1.000   0.3217   0.01188   0.00675  -0.1022   0.8985   0.8097
  -0.750   0.3442   0.01165   0.00658  -0.1002   0.8913   0.8509
  -0.500   0.3725   0.01119   0.00616  -0.0990   0.8873   0.8981
  -0.250   0.4074   0.01088   0.00588  -0.0999   0.8785   0.9533
   0.000   0.4547   0.01049   0.00537  -0.1035   0.8735   1.0000
   0.250   0.4832   0.01045   0.00522  -0.1039   0.8635   1.0000
   0.500   0.5135   0.01038   0.00505  -0.1043   0.8549   1.0000
   0.750   0.5454   0.01022   0.00479  -0.1049   0.8472   1.0000
   1.000   0.5728   0.01020   0.00470  -0.1047   0.8367   1.0000
   1.250   0.6013   0.01017   0.00462  -0.1046   0.8277   1.0000
   1.500   0.6309   0.01011   0.00449  -0.1047   0.8197   1.0000
   1.750   0.6575   0.01013   0.00448  -0.1044   0.8090   1.0000
   2.000   0.6849   0.01012   0.00444  -0.1041   0.7985   1.0000
   2.250   0.7127   0.01011   0.00442  -0.1038   0.7880   1.0000
   2.500   0.7405   0.01008   0.00436  -0.1035   0.7767   1.0000
   2.750   0.7677   0.01008   0.00433  -0.1031   0.7642   1.0000
   3.000   0.7943   0.01010   0.00434  -0.1027   0.7502   1.0000
   3.250   0.8202   0.01014   0.00437  -0.1021   0.7341   1.0000
   3.500   0.8461   0.01019   0.00445  -0.1014   0.7162   1.0000
   3.750   0.8723   0.01025   0.00448  -0.1008   0.6971   1.0000
   4.000   0.8973   0.01035   0.00456  -0.1000   0.6737   1.0000
   4.250   0.9220   0.01048   0.00465  -0.0992   0.6467   1.0000
   4.500   0.9458   0.01068   0.00479  -0.0981   0.6140   1.0000
   4.750   0.9681   0.01097   0.00496  -0.0969   0.5714   1.0000
   5.000   0.9887   0.01142   0.00519  -0.0954   0.5191   1.0000
   5.250   1.0074   0.01205   0.00554  -0.0936   0.4631   1.0000
   5.500   1.0259   0.01276   0.00600  -0.0921   0.4132   1.0000
   5.750   1.0453   0.01346   0.00654  -0.0907   0.3749   1.0000
   6.000   1.0659   0.01409   0.00706  -0.0896   0.3453   1.0000
   6.250   1.0869   0.01471   0.00760  -0.0885   0.3227   1.0000
   6.500   1.1083   0.01529   0.00816  -0.0876   0.3021   1.0000
   6.750   1.1285   0.01590   0.00871  -0.0865   0.2784   1.0000
   7.000   1.1479   0.01649   0.00924  -0.0853   0.2512   1.0000
   7.250   1.1674   0.01703   0.00974  -0.0841   0.2221   1.0000
   7.500   1.1874   0.01757   0.01030  -0.0830   0.1925   1.0000
   7.750   1.2044   0.01838   0.01091  -0.0816   0.1420   1.0000
   8.000   1.2034   0.02120   0.01276  -0.0779   0.0346   1.0000
   8.250   1.2131   0.02294   0.01449  -0.0750   0.0212   1.0000
   8.500   1.2186   0.02479   0.01651  -0.0717   0.0179   1.0000
   8.750   1.2268   0.02613   0.01800  -0.0687   0.0169   1.0000
   9.000   1.2339   0.02760   0.01962  -0.0657   0.0162   1.0000
   9.250   1.2405   0.02926   0.02142  -0.0628   0.0155   1.0000
   9.500   1.2481   0.03108   0.02337  -0.0602   0.0151   1.0000
   9.750   1.2575   0.03309   0.02552  -0.0579   0.0148   1.0000
  10.000   1.2698   0.03532   0.02790  -0.0561   0.0146   1.0000
  10.250   1.2840   0.03787   0.03072  -0.0545   0.0145   1.0000
  10.500   1.2977   0.04078   0.03391  -0.0529   0.0147   1.0000
  10.750   1.3073   0.04402   0.03747  -0.0510   0.0149   1.0000
  11.000   1.3106   0.04750   0.04129  -0.0487   0.0152   1.0000
  11.250   1.3077   0.05113   0.04526  -0.0462   0.0156   1.0000
  11.500   1.3000   0.05495   0.04939  -0.0438   0.0159   1.0000
  11.750   1.2883   0.05906   0.05380  -0.0418   0.0162   1.0000
  12.000   1.2739   0.06343   0.05846  -0.0403   0.0165   1.0000
  12.250   1.2579   0.06805   0.06333  -0.0395   0.0167   1.0000
  12.500   1.2397   0.07323   0.06875  -0.0396   0.0169   1.0000
  12.750   1.2202   0.07889   0.07463  -0.0405   0.0171   1.0000
  13.000   1.2003   0.08501   0.08096  -0.0424   0.0172   1.0000
  13.250   1.1783   0.09224   0.08837  -0.0452   0.0175   1.0000
  13.500   1.0360   0.09796   0.09459  -0.0450   0.0168   1.0000
  13.750   1.0085   0.10507   0.10189  -0.0495   0.0169   1.0000
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