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HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il)
Reynolds number: 100,000
Max Cl/Cd: 42.8 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq300gd2-il-100000.txt
Download as CSV file: xf-hq300gd2-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2908   0.12578   0.12134  -0.0501   1.0000   0.0956
 -11.250  -0.3253   0.12834   0.12407  -0.0428   1.0000   0.0953
 -11.000  -0.3396   0.12373   0.11951  -0.0545   0.9935   0.0996
 -10.750  -0.3151   0.11769   0.11346  -0.0560   0.9894   0.1020
 -10.500  -0.2841   0.11394   0.10966  -0.0576   0.9855   0.1078
 -10.250  -0.2948   0.10860   0.10436  -0.0689   0.9774   0.1146
 -10.000  -0.2622   0.10400   0.09972  -0.0687   0.9744   0.1199
  -9.750  -0.2549   0.09896   0.09468  -0.0771   0.9698   0.1292
  -9.500  -0.2437   0.09393   0.08967  -0.0807   0.9626   0.1341
  -9.250  -0.2252   0.08991   0.08561  -0.0851   0.9573   0.1436
  -9.000  -0.2228   0.08488   0.08061  -0.0899   0.9486   0.1504
  -8.750  -0.2324   0.07941   0.07513  -0.0989   0.9388   0.1610
  -8.500  -0.2028   0.07725   0.07296  -0.0959   0.9329   0.1694
  -8.250  -0.2519   0.07249   0.06814  -0.1038   0.9160   0.1772
  -8.000  -0.2179   0.06985   0.06556  -0.1017   0.9123   0.1896
  -7.750  -0.2141   0.06680   0.06248  -0.1028   0.9049   0.2028
  -7.500  -0.2147   0.06449   0.06015  -0.1025   0.8957   0.2186
  -7.250  -0.2194   0.06241   0.05801  -0.1027   0.8876   0.2392
  -6.750  -0.2422   0.04474   0.03792  -0.1101   0.8675   0.1022
  -6.500  -0.2135   0.04179   0.03402  -0.1099   0.8625   0.0858
  -6.250  -0.1828   0.03795   0.03000  -0.1110   0.8594   0.0828
  -6.000  -0.1710   0.03664   0.02844  -0.1091   0.8513   0.0816
  -5.750  -0.1429   0.03508   0.02650  -0.1093   0.8468   0.0832
  -5.500  -0.1089   0.03347   0.02451  -0.1101   0.8438   0.0845
  -5.250  -0.0936   0.03289   0.02374  -0.1083   0.8364   0.0850
  -5.000  -0.0685   0.03151   0.02225  -0.1078   0.8315   0.0868
  -4.750  -0.0385   0.03027   0.02106  -0.1080   0.8284   0.0922
  -4.500  -0.0125   0.02962   0.02035  -0.1075   0.8246   0.0964
  -4.250  -0.0006   0.02973   0.02042  -0.1053   0.8170   0.0993
  -4.000   0.0256   0.02874   0.01961  -0.1049   0.8132   0.1070
  -3.750   0.0568   0.02786   0.01879  -0.1053   0.8106   0.1201
  -3.500   0.0642   0.02837   0.01935  -0.1033   0.8030   0.1318
  -3.250   0.0897   0.02571   0.01876  -0.1051   0.7990   0.4766
  -3.000   0.0823   0.02745   0.02133  -0.0929   0.7951   0.7298
  -2.750   0.0741   0.02957   0.02343  -0.0857   0.7876   0.7640
  -2.500   0.0731   0.03115   0.02495  -0.0783   0.7822   0.7955
  -2.250   0.0806   0.03213   0.02582  -0.0709   0.7790   0.8270
  -2.000   0.0645   0.03355   0.02725  -0.0639   0.7712   0.8450
  -1.750   0.0626   0.03425   0.02788  -0.0575   0.7660   0.8710
  -1.500   0.0813   0.03415   0.02765  -0.0524   0.7633   0.9045
  -1.250   0.2042   0.03333   0.02644  -0.0662   0.7636   0.9432
  -1.000   0.2658   0.03277   0.02566  -0.0724   0.7619   0.9517
  -0.750   0.2644   0.03421   0.02709  -0.0706   0.7529   0.9635
  -0.500   0.3268   0.03388   0.02659  -0.0775   0.7498   0.9706
  -0.250   0.3895   0.03332   0.02587  -0.0841   0.7476   0.9770
   0.000   0.4463   0.03273   0.02515  -0.0895   0.7456   0.9832
   0.250   0.4542   0.03456   0.02700  -0.0898   0.7359   0.9913
   0.500   0.5044   0.03427   0.02662  -0.0944   0.7326   0.9961
   0.750   0.5578   0.03367   0.02592  -0.0990   0.7303   1.0000
   1.000   0.5081   0.03653   0.02885  -0.0894   0.7183   1.0000
   1.250   0.5379   0.03626   0.02851  -0.0897   0.7150   1.0000
   1.500   0.5691   0.03597   0.02816  -0.0901   0.7120   1.0000
   2.000   0.4311   0.04111   0.03341  -0.0647   0.6871   1.0000
   2.250   0.4632   0.04092   0.03316  -0.0652   0.6832   1.0000
   2.500   0.5008   0.04067   0.03286  -0.0664   0.6799   1.0000
   2.750   0.4479   0.04254   0.03476  -0.0564   0.6678   1.0000
   3.000   0.4754   0.04264   0.03482  -0.0565   0.6631   1.0000
   3.250   0.4678   0.04407   0.03626  -0.0535   0.6527   1.0000
   3.500   0.5141   0.04355   0.03570  -0.0555   0.6499   1.0000
   3.750   0.5074   0.04557   0.03775  -0.0535   0.6378   1.0000
   4.000   0.5526   0.04504   0.03719  -0.0554   0.6345   1.0000
   4.250   0.5541   0.04698   0.03918  -0.0545   0.6227   1.0000
   4.500   0.5980   0.04645   0.03863  -0.0562   0.6192   1.0000
   4.750   0.6459   0.04561   0.03780  -0.0580   0.6170   1.0000
   5.000   0.6468   0.04775   0.03999  -0.0573   0.6039   1.0000
   5.250   0.6554   0.04955   0.04183  -0.0571   0.5923   1.0000
   5.500   0.6977   0.04891   0.04121  -0.0585   0.5885   1.0000
   5.750   0.7471   0.04763   0.03998  -0.0601   0.5866   1.0000
   6.000   0.7500   0.04990   0.04230  -0.0597   0.5731   1.0000
   6.250   0.7603   0.05168   0.04414  -0.0597   0.5614   1.0000
   6.500   0.8035   0.05067   0.04320  -0.0608   0.5578   1.0000
   6.750   0.8384   0.05032   0.04291  -0.0615   0.5525   1.0000
   7.000   0.9035   0.04701   0.03966  -0.0631   0.5546   1.0000
   7.250   0.9077   0.04924   0.04199  -0.0627   0.5408   1.0000
   7.500   0.9610   0.04671   0.03954  -0.0637   0.5400   1.0000
   7.750   1.0172   0.04375   0.03669  -0.0647   0.5395   1.0000
   8.000   0.9706   0.05118   0.04418  -0.0631   0.5126   1.0000
   8.250   1.0240   0.04824   0.04136  -0.0637   0.5116   1.0000
   8.500   1.0826   0.04471   0.03795  -0.0645   0.5111   1.0000
   8.750   1.1507   0.04062   0.03398  -0.0661   0.5107   1.0000
   9.000   1.2342   0.03594   0.02941  -0.0696   0.5095   1.0000
   9.250   1.2379   0.03730   0.03089  -0.0679   0.4964   1.0000
   9.500   1.2556   0.03773   0.03143  -0.0674   0.4849   1.0000
   9.750   1.3457   0.03303   0.02677  -0.0719   0.4791   1.0000
  10.000   1.3595   0.03355   0.02740  -0.0707   0.4659   1.0000
  10.250   1.3808   0.03367   0.02760  -0.0702   0.4526   1.0000
  10.500   1.4059   0.03359   0.02759  -0.0700   0.4390   1.0000
  10.750   1.4300   0.03364   0.02769  -0.0697   0.4246   1.0000
  11.000   1.4512   0.03391   0.02799  -0.0692   0.4095   1.0000
  11.250   1.4694   0.03444   0.02854  -0.0685   0.3941   1.0000
  11.500   1.4840   0.03523   0.02933  -0.0676   0.3782   1.0000
  11.750   1.4954   0.03623   0.03036  -0.0664   0.3621   1.0000
  12.000   1.5035   0.03748   0.03159  -0.0651   0.3458   1.0000
  12.250   1.5083   0.03897   0.03308  -0.0637   0.3297   1.0000
  12.500   1.5102   0.04074   0.03485  -0.0623   0.3139   1.0000
  12.750   1.5097   0.04278   0.03691  -0.0610   0.2987   1.0000
  13.000   1.5074   0.04505   0.03921  -0.0597   0.2840   1.0000
  13.250   1.5040   0.04752   0.04172  -0.0585   0.2698   1.0000
  13.500   1.4996   0.05016   0.04442  -0.0575   0.2560   1.0000
  13.750   1.4946   0.05296   0.04725  -0.0566   0.2425   1.0000
  14.000   1.4890   0.05591   0.05027  -0.0559   0.2292   1.0000
  14.250   1.4827   0.05909   0.05348  -0.0554   0.2159   1.0000
  14.500   1.4753   0.06252   0.05693  -0.0550   0.2027   1.0000
  14.750   1.4667   0.06623   0.06066  -0.0549   0.1893   1.0000
  15.000   1.4566   0.07030   0.06474  -0.0549   0.1757   1.0000
  15.250   1.4449   0.07471   0.06916  -0.0552   0.1618   1.0000
  15.500   1.4322   0.07941   0.07385  -0.0556   0.1478   1.0000
  15.750   1.4185   0.08438   0.07881  -0.0562   0.1338   1.0000
  16.000   1.4048   0.08948   0.08387  -0.0569   0.1202   1.0000
  16.250   1.3926   0.09443   0.08875  -0.0576   0.1077   1.0000
  16.500   1.3838   0.09889   0.09308  -0.0582   0.0965   1.0000
  16.750   1.3757   0.10355   0.09780  -0.0592   0.0874   1.0000
  17.000   1.3718   0.10753   0.10180  -0.0599   0.0794   1.0000
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