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HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il)
Reynolds number: 200,000
Max Cl/Cd: 74.71 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq300gd2-il-200000.txt
Download as CSV file: xf-hq300gd2-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HORSTMANN AND QUAST HQ-300 GD(MOD 2) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1404   0.09466   0.09130  -0.0775   0.8908   0.0583
 -10.750  -0.1667   0.08765   0.08432  -0.0843   0.8846   0.0602
 -10.500  -0.1960   0.07918   0.07582  -0.0919   0.8790   0.0605
 -10.250  -0.1767   0.07718   0.07383  -0.0868   0.8707   0.0618
 -10.000  -0.1614   0.07598   0.07258  -0.0841   0.8624   0.0631
  -9.750  -0.2896   0.07521   0.07165  -0.0960   0.8818   0.0601
  -9.500  -0.3195   0.07136   0.06758  -0.0987   0.8696   0.0603
  -9.250  -0.3405   0.06856   0.06441  -0.1004   0.8598   0.0605
  -9.000  -0.3269   0.06167   0.05770  -0.1009   0.8535   0.0620
  -8.750  -0.3116   0.05911   0.05517  -0.1006   0.8467   0.0633
  -8.500  -0.3050   0.05644   0.05240  -0.1008   0.8403   0.0649
  -8.250  -0.3006   0.05348   0.04927  -0.1016   0.8327   0.0675
  -8.000  -0.3109   0.05009   0.04508  -0.1026   0.8264   0.0733
  -7.750  -0.2919   0.04654   0.04169  -0.1029   0.8199   0.0751
  -7.500  -0.2743   0.04427   0.03934  -0.1029   0.8142   0.0780
  -7.250  -0.2626   0.04187   0.03639  -0.1034   0.8096   0.0876
  -7.000  -0.2410   0.03315   0.02627  -0.1018   0.8042   0.0509
  -6.750  -0.2173   0.02994   0.02295  -0.1017   0.7991   0.0485
  -6.500  -0.1924   0.02752   0.02017  -0.1015   0.7949   0.0476
  -6.250  -0.1659   0.02609   0.01843  -0.1014   0.7897   0.0490
  -6.000  -0.1387   0.02499   0.01702  -0.1014   0.7845   0.0500
  -5.750  -0.1116   0.02361   0.01541  -0.1012   0.7804   0.0506
  -5.500  -0.0861   0.02187   0.01359  -0.1007   0.7771   0.0520
  -5.250  -0.0602   0.02112   0.01289  -0.1007   0.7716   0.0548
  -5.000  -0.0335   0.02041   0.01212  -0.1005   0.7669   0.0573
  -4.750  -0.0065   0.01972   0.01132  -0.1002   0.7632   0.0592
  -4.500   0.0195   0.01896   0.01054  -0.0999   0.7596   0.0618
  -4.250   0.0453   0.01835   0.01004  -0.1000   0.7548   0.0665
  -4.000   0.0729   0.01789   0.00953  -0.1002   0.7506   0.0712
  -3.750   0.1012   0.01715   0.00882  -0.1009   0.7471   0.0787
  -3.500   0.1311   0.01661   0.00828  -0.1018   0.7436   0.0957
  -3.250   0.1640   0.01384   0.00798  -0.1058   0.7391   0.6065
  -3.000   0.1810   0.01454   0.00890  -0.1020   0.7351   0.7089
  -2.750   0.2041   0.01528   0.00954  -0.0999   0.7317   0.7451
  -2.500   0.2209   0.01617   0.01035  -0.0958   0.7289   0.7641
  -2.250   0.2353   0.01707   0.01128  -0.0917   0.7240   0.7807
  -2.000   0.2510   0.01780   0.01197  -0.0878   0.7200   0.7959
  -1.750   0.2682   0.01834   0.01244  -0.0843   0.7166   0.8106
  -1.500   0.2866   0.01876   0.01278  -0.0811   0.7138   0.8253
  -1.250   0.3030   0.01903   0.01303  -0.0779   0.7099   0.8342
  -1.000   0.3277   0.01914   0.01309  -0.0776   0.7055   0.8421
  -0.750   0.3503   0.01914   0.01302  -0.0763   0.7019   0.8481
  -0.500   0.3798   0.01914   0.01291  -0.0770   0.6989   0.8559
  -0.250   0.4016   0.01909   0.01279  -0.0753   0.6961   0.8613
   0.000   0.4263   0.01930   0.01301  -0.0755   0.6911   0.8694
   0.250   0.4463   0.01921   0.01290  -0.0737   0.6871   0.8751
   0.500   0.4731   0.01917   0.01279  -0.0736   0.6840   0.8819
   0.750   0.4998   0.01906   0.01259  -0.0734   0.6813   0.8873
   1.000   0.5206   0.01915   0.01271  -0.0725   0.6766   0.8926
   1.250   0.5479   0.01926   0.01280  -0.0731   0.6721   0.8976
   1.500   0.5735   0.01907   0.01257  -0.0727   0.6685   0.9014
   1.750   0.6018   0.01891   0.01234  -0.0729   0.6657   0.9050
   2.000   0.6260   0.01907   0.01253  -0.0729   0.6606   0.9091
   2.250   0.6543   0.01914   0.01260  -0.0737   0.6556   0.9125
   2.500   0.6806   0.01890   0.01231  -0.0734   0.6520   0.9155
   2.750   0.7111   0.01874   0.01208  -0.0740   0.6490   0.9183
   3.000   0.7331   0.01895   0.01239  -0.0738   0.6427   0.9219
   3.250   0.7634   0.01893   0.01235  -0.0747   0.6381   0.9247
   3.500   0.7938   0.01872   0.01210  -0.0754   0.6346   0.9269
   3.750   0.8172   0.01875   0.01217  -0.0749   0.6296   0.9300
   4.000   0.8427   0.01877   0.01224  -0.0750   0.6240   0.9329
   4.250   0.8745   0.01864   0.01208  -0.0760   0.6199   0.9350
   4.500   0.9057   0.01864   0.01207  -0.0771   0.6157   0.9375
   4.750   0.9273   0.01870   0.01223  -0.0765   0.6091   0.9403
   5.000   0.9570   0.01852   0.01204  -0.0770   0.6046   0.9425
   5.250   0.9872   0.01843   0.01195  -0.0777   0.6001   0.9447
   5.500   1.0107   0.01855   0.01217  -0.0776   0.5929   0.9476
   5.750   1.0431   0.01838   0.01199  -0.0787   0.5880   0.9499
   6.000   1.0679   0.01839   0.01208  -0.0786   0.5815   0.9522
   6.250   1.0945   0.01828   0.01202  -0.0787   0.5748   0.9545
   6.500   1.1261   0.01809   0.01180  -0.0795   0.5694   0.9568
   6.750   1.1478   0.01817   0.01201  -0.0790   0.5607   0.9600
   7.000   1.1816   0.01794   0.01173  -0.0802   0.5548   0.9621
   7.250   1.2006   0.01800   0.01195  -0.0792   0.5451   0.9649
   7.500   1.2295   0.01786   0.01182  -0.0796   0.5375   0.9673
   7.750   1.2527   0.01786   0.01192  -0.0793   0.5276   0.9704
   8.000   1.2763   0.01790   0.01203  -0.0790   0.5175   0.9738
   8.250   1.3031   0.01779   0.01193  -0.0791   0.5078   0.9770
   8.500   1.3243   0.01790   0.01214  -0.0786   0.4955   0.9807
   8.750   1.3455   0.01808   0.01240  -0.0781   0.4825   0.9846
   9.000   1.3672   0.01830   0.01267  -0.0777   0.4686   0.9898
   9.250   1.3864   0.01857   0.01300  -0.0770   0.4538   1.0000
   9.500   1.4035   0.01903   0.01347  -0.0760   0.4384   1.0000
   9.750   1.4194   0.01964   0.01409  -0.0751   0.4223   1.0000
  10.000   1.4343   0.02041   0.01485  -0.0741   0.4059   1.0000
  10.250   1.4476   0.02135   0.01577  -0.0732   0.3893   1.0000
  10.500   1.4594   0.02244   0.01684  -0.0722   0.3728   1.0000
  10.750   1.4686   0.02375   0.01811  -0.0711   0.3557   1.0000
  11.000   1.4754   0.02529   0.01966  -0.0701   0.3377   1.0000
  11.250   1.4807   0.02703   0.02139  -0.0691   0.3199   1.0000
  11.500   1.4853   0.02892   0.02327  -0.0682   0.3029   1.0000
  11.750   1.4898   0.03090   0.02527  -0.0675   0.2872   1.0000
  12.000   1.4941   0.03297   0.02735  -0.0668   0.2725   1.0000
  12.250   1.4979   0.03515   0.02954  -0.0662   0.2584   1.0000
  12.500   1.5009   0.03744   0.03185  -0.0657   0.2449   1.0000
  12.750   1.5029   0.03985   0.03428  -0.0651   0.2317   1.0000
  13.000   1.5039   0.04243   0.03687  -0.0647   0.2187   1.0000
  13.250   1.5039   0.04519   0.03963  -0.0643   0.2057   1.0000
  13.500   1.5043   0.04801   0.04249  -0.0641   0.1923   1.0000
  13.750   1.5040   0.05099   0.04551  -0.0639   0.1790   1.0000
  14.000   1.5025   0.05415   0.04870  -0.0638   0.1656   1.0000
  14.250   1.4994   0.05754   0.05210  -0.0638   0.1520   1.0000
  14.500   1.4950   0.06117   0.05573  -0.0638   0.1382   1.0000
  14.750   1.4885   0.06512   0.05966  -0.0639   0.1240   1.0000
  15.000   1.4794   0.06943   0.06393  -0.0641   0.1096   1.0000
  15.250   1.4699   0.07391   0.06840  -0.0644   0.0939   1.0000
  15.500   1.4574   0.07884   0.07329  -0.0648   0.0799   1.0000
  15.750   1.4441   0.08396   0.07838  -0.0653   0.0689   1.0000
  16.000   1.4308   0.08919   0.08359  -0.0660   0.0607   1.0000
  16.250   1.4182   0.09445   0.08884  -0.0669   0.0547   1.0000
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