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HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il)
Reynolds number: 100,000
Max Cl/Cd: 44.61 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq300gd2-il-100000-n5.txt
Download as CSV file: xf-hq300gd2-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2825   0.08335   0.07850  -0.0846   0.9109   0.0330
 -10.250  -0.2895   0.07637   0.07146  -0.0900   0.8985   0.0327
 -10.000  -0.3024   0.07010   0.06509  -0.0947   0.8866   0.0324
  -9.750  -0.3185   0.06479   0.05960  -0.0978   0.8753   0.0321
  -9.500  -0.3345   0.06042   0.05505  -0.0993   0.8632   0.0319
  -9.250  -0.3484   0.05669   0.05109  -0.0997   0.8529   0.0317
  -9.000  -0.3552   0.05285   0.04693  -0.1000   0.8443   0.0316
  -8.750  -0.3568   0.04917   0.04290  -0.0999   0.8358   0.0316
  -8.500  -0.3528   0.04561   0.03891  -0.0996   0.8288   0.0317
  -8.250  -0.3437   0.04235   0.03519  -0.0993   0.8222   0.0321
  -8.000  -0.3312   0.03932   0.03163  -0.0989   0.8154   0.0328
  -7.750  -0.3142   0.03685   0.02870  -0.0987   0.8103   0.0342
  -7.500  -0.2935   0.03546   0.02723  -0.0988   0.8035   0.0354
  -7.250  -0.2717   0.03375   0.02524  -0.0986   0.7979   0.0365
  -7.000  -0.2482   0.03190   0.02303  -0.0984   0.7938   0.0374
  -6.750  -0.2247   0.03033   0.02116  -0.0982   0.7877   0.0386
  -6.500  -0.1996   0.02904   0.01952  -0.0979   0.7825   0.0407
  -6.250  -0.1742   0.02774   0.01806  -0.0977   0.7783   0.0425
  -6.000  -0.1494   0.02673   0.01698  -0.0974   0.7730   0.0440
  -5.750  -0.1243   0.02580   0.01596  -0.0971   0.7679   0.0457
  -5.500  -0.0984   0.02499   0.01502  -0.0967   0.7638   0.0482
  -5.250  -0.0727   0.02422   0.01414  -0.0964   0.7601   0.0511
  -5.000  -0.0492   0.02352   0.01351  -0.0960   0.7545   0.0536
  -4.750  -0.0244   0.02289   0.01284  -0.0957   0.7500   0.0565
  -4.500   0.0018   0.02235   0.01217  -0.0956   0.7464   0.0607
  -4.250   0.0268   0.02178   0.01163  -0.0957   0.7422   0.0666
  -4.000   0.0524   0.02136   0.01115  -0.0957   0.7374   0.0734
  -3.750   0.0790   0.02088   0.01063  -0.0959   0.7333   0.0854
  -3.500   0.1059   0.02021   0.01012  -0.0962   0.7300   0.1165
  -3.250   0.1280   0.01833   0.00981  -0.0972   0.7258   0.4294
  -3.000   0.1334   0.01862   0.01111  -0.0907   0.7212   0.6340
  -2.750   0.1542   0.01936   0.01184  -0.0879   0.7174   0.7079
  -2.500   0.1774   0.02007   0.01240  -0.0858   0.7142   0.7460
  -2.250   0.1947   0.02093   0.01318  -0.0821   0.7103   0.7731
  -2.000   0.2122   0.02159   0.01377  -0.0791   0.7055   0.7932
  -1.750   0.2333   0.02186   0.01392  -0.0771   0.7018   0.8035
  -1.500   0.2598   0.02189   0.01379  -0.0769   0.6988   0.8112
  -1.250   0.2846   0.02196   0.01373  -0.0761   0.6956   0.8181
  -1.000   0.3074   0.02217   0.01388  -0.0757   0.6905   0.8262
  -0.750   0.3300   0.02227   0.01390  -0.0746   0.6867   0.8328
  -0.500   0.3576   0.02231   0.01381  -0.0748   0.6835   0.8407
  -0.250   0.3824   0.02225   0.01364  -0.0739   0.6809   0.8461
   0.000   0.4041   0.02252   0.01390  -0.0735   0.6756   0.8529
   0.250   0.4279   0.02260   0.01394  -0.0731   0.6714   0.8579
   0.500   0.4536   0.02258   0.01383  -0.0728   0.6681   0.8623
   0.750   0.4831   0.02253   0.01368  -0.0734   0.6654   0.8668
   1.000   0.5059   0.02280   0.01396  -0.0733   0.6604   0.8712
   1.250   0.5281   0.02291   0.01406  -0.0726   0.6558   0.8749
   1.500   0.5555   0.02290   0.01400  -0.0728   0.6523   0.8784
   1.750   0.5861   0.02286   0.01389  -0.0737   0.6496   0.8819
   2.000   0.6081   0.02320   0.01427  -0.0735   0.6441   0.8856
   2.250   0.6309   0.02331   0.01439  -0.0730   0.6393   0.8886
   2.500   0.6592   0.02326   0.01430  -0.0733   0.6357   0.8917
   2.750   0.6911   0.02314   0.01412  -0.0742   0.6330   0.8945
   3.000   0.7097   0.02368   0.01477  -0.0737   0.6257   0.8981
   3.250   0.7357   0.02365   0.01473  -0.0736   0.6213   0.9008
   3.500   0.7660   0.02347   0.01452  -0.0741   0.6180   0.9033
   3.750   0.7842   0.02391   0.01505  -0.0733   0.6111   0.9065
   4.000   0.8115   0.02396   0.01512  -0.0736   0.6061   0.9094
   4.250   0.8449   0.02380   0.01495  -0.0748   0.6025   0.9119
   4.500   0.8614   0.02423   0.01548  -0.0736   0.5953   0.9148
   4.750   0.8879   0.02424   0.01553  -0.0737   0.5900   0.9173
   5.000   0.9207   0.02400   0.01527  -0.0746   0.5863   0.9197
   5.250   0.9363   0.02460   0.01603  -0.0736   0.5781   0.9233
   5.500   0.9665   0.02454   0.01600  -0.0743   0.5730   0.9256
   5.750   0.9894   0.02467   0.01620  -0.0739   0.5669   0.9280
   6.000   1.0098   0.02492   0.01656  -0.0732   0.5597   0.9310
   6.250   1.0430   0.02462   0.01627  -0.0741   0.5551   0.9335
   6.500   1.0559   0.02530   0.01711  -0.0727   0.5457   0.9372
   6.750   1.0874   0.02503   0.01687  -0.0733   0.5402   0.9395
   7.000   1.0988   0.02564   0.01765  -0.0716   0.5307   0.9428
   7.250   1.1304   0.02534   0.01738  -0.0722   0.5245   0.9454
   7.500   1.1402   0.02606   0.01825  -0.0704   0.5140   0.9496
   7.750   1.1620   0.02608   0.01836  -0.0697   0.5059   0.9531
   8.000   1.1769   0.02645   0.01884  -0.0684   0.4960   0.9572
   8.250   1.1902   0.02711   0.01961  -0.0672   0.4851   0.9613
   8.500   1.2109   0.02730   0.01987  -0.0666   0.4752   0.9653
   8.750   1.2286   0.02767   0.02033  -0.0658   0.4640   0.9706
   9.000   1.2397   0.02854   0.02132  -0.0646   0.4513   0.9778
   9.250   1.2508   0.02931   0.02217  -0.0635   0.4387   0.9928
   9.500   1.2686   0.03007   0.02300  -0.0633   0.4255   1.0000
   9.750   1.2863   0.03088   0.02385  -0.0631   0.4122   1.0000
  10.000   1.3033   0.03176   0.02479  -0.0628   0.3985   1.0000
  10.250   1.3191   0.03275   0.02579  -0.0625   0.3847   1.0000
  10.500   1.3338   0.03385   0.02691  -0.0621   0.3708   1.0000
  10.750   1.3462   0.03516   0.02826  -0.0617   0.3570   1.0000
  11.000   1.3565   0.03668   0.02985  -0.0612   0.3432   1.0000
  11.250   1.3660   0.03830   0.03152  -0.0607   0.3299   1.0000
  11.500   1.3749   0.04000   0.03326  -0.0602   0.3168   1.0000
  11.750   1.3830   0.04176   0.03507  -0.0597   0.3040   1.0000
  12.000   1.3902   0.04362   0.03696  -0.0592   0.2914   1.0000
  12.250   1.3960   0.04561   0.03897  -0.0587   0.2787   1.0000
  12.500   1.3992   0.04788   0.04129  -0.0582   0.2657   1.0000
  12.750   1.4003   0.05044   0.04392  -0.0578   0.2523   1.0000
  13.000   1.4005   0.05316   0.04670  -0.0575   0.2389   1.0000
  13.250   1.3998   0.05606   0.04964  -0.0572   0.2254   1.0000
  13.500   1.3984   0.05913   0.05275  -0.0571   0.2120   1.0000
  13.750   1.3963   0.06235   0.05601  -0.0571   0.1988   1.0000
  14.000   1.3937   0.06572   0.05941  -0.0573   0.1861   1.0000
  14.250   1.3904   0.06925   0.06297  -0.0575   0.1737   1.0000
  14.500   1.3863   0.07295   0.06670  -0.0578   0.1619   1.0000
  14.750   1.3818   0.07682   0.07061  -0.0583   0.1502   1.0000
  15.000   1.3772   0.08079   0.07466  -0.0588   0.1388   1.0000
  15.250   1.3718   0.08492   0.07886  -0.0595   0.1279   1.0000
  15.500   1.3654   0.08927   0.08326  -0.0604   0.1177   1.0000
  15.750   1.3575   0.09391   0.08793  -0.0614   0.1081   1.0000
  16.000   1.3494   0.09868   0.09275  -0.0626   0.0985   1.0000
  16.250   1.3417   0.10347   0.09761  -0.0639   0.0895   1.0000
  16.500   1.3328   0.10854   0.10272  -0.0654   0.0816   1.0000
  16.750   1.3227   0.11389   0.10810  -0.0673   0.0746   1.0000
  17.000   1.3152   0.11893   0.11323  -0.0691   0.0676   1.0000
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