HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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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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Polar data table (+)
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