HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.33 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq259b-il-1000000-n5.txt Download as CSV file: xf-hq259b-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5064 0.15188 0.15006 -0.0082 1.0000 0.0038
-13.750 -0.5029 0.14779 0.14597 -0.0096 1.0000 0.0039
-11.750 -0.9005 0.02977 0.02718 -0.0713 1.0000 0.0052
-11.500 -0.8957 0.02658 0.02369 -0.0706 0.9997 0.0054
-11.250 -0.8726 0.02399 0.02081 -0.0726 0.9971 0.0055
-11.000 -0.8473 0.02205 0.01862 -0.0741 0.9940 0.0057
-10.750 -0.8224 0.02046 0.01681 -0.0751 0.9903 0.0058
-10.500 -0.7951 0.01909 0.01526 -0.0763 0.9869 0.0060
-10.250 -0.7657 0.01804 0.01408 -0.0776 0.9843 0.0064
-10.000 -0.7351 0.01754 0.01354 -0.0788 0.9817 0.0067
-9.750 -0.7062 0.01702 0.01295 -0.0795 0.9775 0.0070
-9.500 -0.6757 0.01646 0.01232 -0.0806 0.9736 0.0073
-9.250 -0.6444 0.01578 0.01153 -0.0819 0.9700 0.0077
-9.000 -0.6157 0.01504 0.01067 -0.0826 0.9639 0.0080
-8.750 -0.5858 0.01436 0.00986 -0.0835 0.9575 0.0083
-8.500 -0.5574 0.01378 0.00916 -0.0840 0.9496 0.0085
-8.000 -0.5026 0.01285 0.00809 -0.0844 0.9315 0.0093
-7.750 -0.4756 0.01255 0.00773 -0.0843 0.9224 0.0097
-7.500 -0.4490 0.01229 0.00740 -0.0842 0.9129 0.0102
-7.250 -0.4225 0.01200 0.00702 -0.0841 0.9035 0.0107
-7.000 -0.3961 0.01167 0.00660 -0.0839 0.8947 0.0112
-6.750 -0.3697 0.01135 0.00618 -0.0837 0.8856 0.0115
-6.500 -0.3430 0.01107 0.00581 -0.0835 0.8772 0.0117
-6.000 -0.2906 0.01013 0.00472 -0.0832 0.8610 0.0129
-5.500 -0.2364 0.00965 0.00414 -0.0830 0.8473 0.0140
-5.250 -0.2094 0.00937 0.00380 -0.0829 0.8407 0.0145
-5.000 -0.1820 0.00911 0.00348 -0.0828 0.8348 0.0150
-4.750 -0.1545 0.00891 0.00322 -0.0827 0.8285 0.0155
-4.500 -0.1270 0.00874 0.00300 -0.0827 0.8228 0.0158
-4.250 -0.0996 0.00839 0.00260 -0.0827 0.8168 0.0165
-4.000 -0.0721 0.00817 0.00231 -0.0826 0.8107 0.0173
-3.750 -0.0444 0.00799 0.00210 -0.0825 0.8027 0.0181
-3.500 -0.0170 0.00785 0.00191 -0.0824 0.7925 0.0190
-3.250 0.0105 0.00773 0.00173 -0.0823 0.7825 0.0200
-3.000 0.0384 0.00763 0.00159 -0.0823 0.7745 0.0211
-2.750 0.0661 0.00750 0.00143 -0.0822 0.7669 0.0241
-2.500 0.0941 0.00738 0.00131 -0.0822 0.7599 0.0279
-2.250 0.1219 0.00728 0.00120 -0.0822 0.7527 0.0360
-2.000 0.1499 0.00716 0.00112 -0.0822 0.7456 0.0490
-1.750 0.1777 0.00706 0.00104 -0.0822 0.7380 0.0652
-1.500 0.2057 0.00691 0.00097 -0.0822 0.7307 0.0951
-1.000 0.2604 0.00615 0.00080 -0.0826 0.7145 0.3155
-0.750 0.2872 0.00565 0.00077 -0.0827 0.7074 0.4869
-0.500 0.3150 0.00549 0.00077 -0.0827 0.6999 0.5476
-0.250 0.3426 0.00542 0.00079 -0.0826 0.6914 0.5877
0.000 0.3703 0.00536 0.00083 -0.0825 0.6816 0.6308
0.250 0.3979 0.00535 0.00086 -0.0824 0.6698 0.6610
0.500 0.4255 0.00540 0.00088 -0.0823 0.6541 0.6716
0.750 0.4528 0.00549 0.00089 -0.0821 0.6306 0.6799
1.000 0.4783 0.00571 0.00094 -0.0816 0.5782 0.6875
1.250 0.5028 0.00609 0.00106 -0.0810 0.5125 0.6953
1.500 0.5281 0.00640 0.00119 -0.0806 0.4647 0.7031
1.750 0.5538 0.00668 0.00131 -0.0802 0.4237 0.7106
2.000 0.5792 0.00698 0.00145 -0.0799 0.3796 0.7184
2.250 0.6052 0.00723 0.00157 -0.0795 0.3465 0.7268
2.500 0.6315 0.00742 0.00169 -0.0793 0.3219 0.7363
2.750 0.6579 0.00760 0.00181 -0.0791 0.3012 0.7455
3.000 0.6846 0.00775 0.00193 -0.0789 0.2854 0.7556
3.250 0.7109 0.00792 0.00207 -0.0786 0.2640 0.7679
3.500 0.7366 0.00815 0.00223 -0.0783 0.2387 0.7820
3.750 0.7622 0.00836 0.00239 -0.0779 0.2156 0.7974
4.000 0.7873 0.00862 0.00259 -0.0774 0.1889 0.8144
4.250 0.8105 0.00906 0.00288 -0.0767 0.1453 0.8343
4.500 0.8342 0.00942 0.00314 -0.0760 0.1144 0.8556
4.750 0.8582 0.00968 0.00338 -0.0753 0.0950 0.8782
5.000 0.8811 0.00992 0.00362 -0.0744 0.0781 0.9082
5.250 0.9094 0.01011 0.00386 -0.0746 0.0654 1.0000
5.500 0.9353 0.01038 0.00409 -0.0743 0.0582 1.0000
5.750 0.9610 0.01065 0.00434 -0.0741 0.0519 1.0000
6.000 0.9865 0.01095 0.00461 -0.0737 0.0449 1.0000
6.250 1.0117 0.01126 0.00490 -0.0734 0.0376 1.0000
6.500 1.0363 0.01165 0.00523 -0.0729 0.0289 1.0000
6.750 1.0610 0.01202 0.00557 -0.0725 0.0239 1.0000
7.000 1.0858 0.01235 0.00590 -0.0721 0.0217 1.0000
7.250 1.1102 0.01273 0.00628 -0.0716 0.0198 1.0000
7.500 1.1344 0.01312 0.00669 -0.0710 0.0180 1.0000
7.750 1.1590 0.01344 0.00705 -0.0706 0.0174 1.0000
8.000 1.1832 0.01379 0.00743 -0.0701 0.0166 1.0000
8.250 1.2070 0.01417 0.00785 -0.0696 0.0158 1.0000
8.500 1.2303 0.01459 0.00829 -0.0689 0.0148 1.0000
8.750 1.2527 0.01510 0.00882 -0.0682 0.0136 1.0000
9.000 1.2755 0.01554 0.00930 -0.0675 0.0131 1.0000
9.250 1.2986 0.01592 0.00974 -0.0669 0.0126 1.0000
9.500 1.3212 0.01633 0.01020 -0.0662 0.0120 1.0000
9.750 1.3433 0.01677 0.01068 -0.0655 0.0112 1.0000
10.000 1.3648 0.01725 0.01117 -0.0647 0.0104 1.0000
10.250 1.3852 0.01782 0.01177 -0.0637 0.0095 1.0000
10.500 1.4063 0.01827 0.01228 -0.0628 0.0089 1.0000
10.750 1.4265 0.01879 0.01284 -0.0618 0.0083 1.0000
11.000 1.4458 0.01935 0.01343 -0.0607 0.0076 1.0000
11.250 1.4638 0.01999 0.01411 -0.0594 0.0069 1.0000
11.500 1.4811 0.02063 0.01481 -0.0580 0.0065 1.0000
11.750 1.4968 0.02127 0.01552 -0.0563 0.0061 1.0000
12.000 1.5101 0.02194 0.01626 -0.0543 0.0058 1.0000
12.250 1.5221 0.02267 0.01704 -0.0521 0.0054 1.0000
12.500 1.5330 0.02348 0.01791 -0.0498 0.0051 1.0000
12.750 1.5425 0.02440 0.01890 -0.0475 0.0048 1.0000
13.000 1.5506 0.02543 0.02003 -0.0452 0.0045 1.0000
13.250 1.5597 0.02643 0.02111 -0.0432 0.0044 1.0000
13.500 1.5680 0.02751 0.02230 -0.0412 0.0043 1.0000
13.750 1.5755 0.02869 0.02358 -0.0393 0.0041 1.0000
14.000 1.5819 0.03001 0.02500 -0.0374 0.0039 1.0000
14.250 1.5874 0.03146 0.02653 -0.0357 0.0038 1.0000
14.500 1.5914 0.03309 0.02827 -0.0341 0.0036 1.0000
14.750 1.5943 0.03490 0.03018 -0.0326 0.0035 1.0000
15.000 1.5961 0.03690 0.03228 -0.0313 0.0034 1.0000
15.250 1.5963 0.03916 0.03465 -0.0302 0.0033 1.0000
15.500 1.5945 0.04173 0.03734 -0.0293 0.0033 1.0000
15.750 1.5907 0.04467 0.04040 -0.0287 0.0031 1.0000
16.000 1.5845 0.04805 0.04391 -0.0285 0.0031 1.0000
16.250 1.5759 0.05194 0.04794 -0.0287 0.0030 1.0000
16.500 1.5632 0.05670 0.05286 -0.0297 0.0029 1.0000
16.750 1.5519 0.06165 0.05795 -0.0312 0.0029 1.0000
17.000 1.5402 0.06714 0.06359 -0.0334 0.0029 1.0000
17.250 1.5242 0.07385 0.07046 -0.0366 0.0029 1.0000
17.500 1.5071 0.08122 0.07799 -0.0406 0.0029 1.0000
17.750 1.4854 0.08989 0.08683 -0.0454 0.0029 1.0000
18.000 1.4559 0.10038 0.09751 -0.0514 0.0029 1.0000
18.250 1.4228 0.11195 0.10925 -0.0582 0.0029 1.0000
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Polar data table (+)
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