HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.2 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2512-il-1000000.txt Download as CSV file: xf-hq2512-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/12 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5844 0.09747 0.09575 -0.0375 1.0000 0.0068
-13.000 -0.6012 0.08976 0.08802 -0.0412 1.0000 0.0066
-12.750 -0.7395 0.05390 0.05181 -0.0643 1.0000 0.0062
-12.500 -0.7736 0.04439 0.04208 -0.0720 1.0000 0.0059
-12.250 -0.7915 0.03920 0.03672 -0.0752 1.0000 0.0060
-12.000 -0.8087 0.03517 0.03251 -0.0765 1.0000 0.0060
-11.750 -0.8210 0.03277 0.02999 -0.0754 1.0000 0.0062
-11.500 -0.8415 0.03091 0.02801 -0.0710 1.0000 0.0060
-11.250 -0.8481 0.02911 0.02604 -0.0679 0.9995 0.0062
-11.000 -0.8253 0.02643 0.02309 -0.0707 0.9957 0.0063
-10.750 -0.7998 0.02462 0.02107 -0.0727 0.9915 0.0064
-10.500 -0.7718 0.02330 0.01958 -0.0743 0.9875 0.0066
-10.250 -0.7419 0.02206 0.01818 -0.0762 0.9846 0.0067
-10.000 -0.7213 0.01846 0.01417 -0.0780 0.9795 0.0071
-9.750 -0.6934 0.01721 0.01278 -0.0792 0.9737 0.0074
-9.500 -0.6622 0.01626 0.01173 -0.0808 0.9694 0.0076
-9.250 -0.6364 0.01554 0.01093 -0.0809 0.9601 0.0079
-9.000 -0.6103 0.01486 0.01014 -0.0811 0.9512 0.0082
-8.750 -0.5859 0.01421 0.00938 -0.0807 0.9411 0.0084
-8.500 -0.5627 0.01361 0.00867 -0.0801 0.9302 0.0088
-8.250 -0.5386 0.01311 0.00807 -0.0796 0.9206 0.0092
-8.000 -0.5140 0.01269 0.00755 -0.0791 0.9118 0.0094
-7.750 -0.4923 0.01181 0.00654 -0.0782 0.9024 0.0104
-7.500 -0.4673 0.01142 0.00608 -0.0778 0.8947 0.0112
-7.250 -0.4419 0.01107 0.00567 -0.0775 0.8867 0.0122
-7.000 -0.4160 0.01076 0.00528 -0.0771 0.8796 0.0130
-6.750 -0.3912 0.01025 0.00470 -0.0767 0.8720 0.0150
-6.500 -0.3648 0.00998 0.00440 -0.0764 0.8653 0.0174
-6.250 -0.3387 0.00965 0.00409 -0.0762 0.8583 0.0224
-6.000 -0.3122 0.00942 0.00384 -0.0760 0.8520 0.0277
-5.750 -0.2846 0.00932 0.00372 -0.0760 0.8453 0.0310
-5.250 -0.2306 0.00891 0.00328 -0.0757 0.8326 0.0387
-5.000 -0.2031 0.00881 0.00311 -0.0756 0.8262 0.0408
-4.750 -0.1760 0.00858 0.00285 -0.0755 0.8200 0.0451
-4.500 -0.1486 0.00840 0.00267 -0.0754 0.8134 0.0500
-4.250 -0.1210 0.00829 0.00251 -0.0754 0.8073 0.0543
-4.000 -0.0937 0.00806 0.00231 -0.0753 0.8006 0.0640
-3.750 -0.0664 0.00788 0.00213 -0.0752 0.7944 0.0765
-3.500 -0.0391 0.00763 0.00196 -0.0752 0.7874 0.0999
-3.250 -0.0124 0.00736 0.00179 -0.0751 0.7806 0.1414
-3.000 0.0144 0.00700 0.00164 -0.0751 0.7735 0.2048
-2.750 0.0410 0.00669 0.00150 -0.0750 0.7669 0.2687
-2.500 0.0671 0.00618 0.00135 -0.0750 0.7605 0.3800
-2.250 0.0937 0.00587 0.00127 -0.0749 0.7543 0.4643
-2.000 0.1211 0.00571 0.00123 -0.0748 0.7479 0.5170
-1.750 0.1489 0.00563 0.00121 -0.0748 0.7402 0.5490
-1.500 0.1769 0.00559 0.00118 -0.0747 0.7324 0.5734
-1.250 0.2046 0.00557 0.00118 -0.0747 0.7245 0.5983
-1.000 0.2329 0.00556 0.00117 -0.0747 0.7164 0.6123
-0.500 0.2889 0.00558 0.00118 -0.0746 0.6995 0.6477
-0.250 0.3168 0.00560 0.00120 -0.0745 0.6919 0.6605
0.000 0.3450 0.00561 0.00121 -0.0745 0.6841 0.6690
0.250 0.3732 0.00566 0.00122 -0.0745 0.6767 0.6775
0.500 0.4012 0.00567 0.00124 -0.0745 0.6681 0.6858
0.750 0.4293 0.00571 0.00126 -0.0745 0.6596 0.6947
1.250 0.4851 0.00578 0.00132 -0.0744 0.6408 0.7102
1.500 0.5129 0.00582 0.00135 -0.0743 0.6309 0.7165
1.750 0.5406 0.00589 0.00139 -0.0743 0.6197 0.7228
2.000 0.5680 0.00594 0.00144 -0.0742 0.6074 0.7292
2.250 0.5955 0.00603 0.00148 -0.0741 0.5931 0.7360
2.500 0.6225 0.00610 0.00155 -0.0739 0.5753 0.7426
2.750 0.6493 0.00622 0.00161 -0.0737 0.5552 0.7499
3.000 0.6755 0.00636 0.00170 -0.0734 0.5328 0.7570
3.250 0.7016 0.00654 0.00180 -0.0731 0.5079 0.7651
3.500 0.7271 0.00672 0.00193 -0.0727 0.4808 0.7729
3.750 0.7519 0.00698 0.00207 -0.0722 0.4491 0.7816
4.000 0.7765 0.00724 0.00224 -0.0716 0.4185 0.7907
4.250 0.8008 0.00752 0.00242 -0.0711 0.3856 0.8003
4.500 0.8241 0.00788 0.00264 -0.0703 0.3457 0.8112
4.750 0.8477 0.00818 0.00285 -0.0697 0.3142 0.8237
5.250 0.8949 0.00867 0.00327 -0.0682 0.2705 0.8563
5.500 0.9176 0.00880 0.00346 -0.0672 0.2562 0.8877
5.750 0.9512 0.00890 0.00368 -0.0686 0.2418 1.0000
6.000 0.9762 0.00916 0.00388 -0.0683 0.2290 1.0000
6.250 1.0005 0.00948 0.00412 -0.0678 0.2098 1.0000
6.500 1.0240 0.00983 0.00436 -0.0672 0.1907 1.0000
6.750 1.0475 0.01017 0.00462 -0.0666 0.1732 1.0000
7.000 1.0712 0.01049 0.00489 -0.0660 0.1597 1.0000
7.250 1.0941 0.01085 0.00519 -0.0653 0.1439 1.0000
7.500 1.1168 0.01122 0.00549 -0.0646 0.1301 1.0000
7.750 1.1389 0.01162 0.00582 -0.0638 0.1160 1.0000
8.000 1.1603 0.01205 0.00618 -0.0628 0.1016 1.0000
8.250 1.1809 0.01252 0.00657 -0.0618 0.0871 1.0000
8.500 1.2001 0.01307 0.00701 -0.0606 0.0713 1.0000
8.750 1.2183 0.01366 0.00751 -0.0592 0.0555 1.0000
9.000 1.2330 0.01447 0.00816 -0.0572 0.0348 1.0000
9.250 1.2396 0.01574 0.00922 -0.0541 0.0092 1.0000
9.500 1.2537 0.01635 0.00984 -0.0519 0.0067 1.0000
9.750 1.2677 0.01694 0.01046 -0.0497 0.0058 1.0000
10.000 1.2816 0.01754 0.01112 -0.0475 0.0053 1.0000
10.250 1.2961 0.01811 0.01174 -0.0456 0.0052 1.0000
10.500 1.3101 0.01872 0.01242 -0.0437 0.0050 1.0000
10.750 1.3229 0.01943 0.01319 -0.0417 0.0048 1.0000
11.000 1.3352 0.02018 0.01401 -0.0397 0.0046 1.0000
11.250 1.3468 0.02099 0.01488 -0.0377 0.0044 1.0000
11.500 1.3567 0.02194 0.01590 -0.0357 0.0042 1.0000
11.750 1.3648 0.02305 0.01708 -0.0336 0.0040 1.0000
12.000 1.3693 0.02444 0.01857 -0.0312 0.0038 1.0000
12.250 1.3790 0.02549 0.01970 -0.0296 0.0039 1.0000
12.500 1.3796 0.02728 0.02160 -0.0273 0.0038 1.0000
12.750 1.3755 0.02952 0.02399 -0.0249 0.0037 1.0000
13.000 1.3772 0.03139 0.02597 -0.0232 0.0036 1.0000
13.250 1.3831 0.03300 0.02766 -0.0220 0.0035 1.0000
13.500 1.3869 0.03487 0.02962 -0.0209 0.0034 1.0000
13.750 1.3862 0.03721 0.03207 -0.0198 0.0034 1.0000
14.000 1.3857 0.03967 0.03463 -0.0189 0.0034 1.0000
14.250 1.3830 0.04245 0.03753 -0.0183 0.0034 1.0000
14.500 1.3801 0.04539 0.04057 -0.0179 0.0034 1.0000
14.750 1.3749 0.04877 0.04407 -0.0178 0.0034 1.0000
15.000 1.3698 0.05230 0.04771 -0.0180 0.0034 1.0000
15.250 1.3617 0.05644 0.05198 -0.0186 0.0033 1.0000
15.500 1.3552 0.06058 0.05623 -0.0195 0.0033 1.0000
15.750 1.3465 0.06525 0.06102 -0.0208 0.0033 1.0000
16.000 1.3384 0.07004 0.06593 -0.0224 0.0033 1.0000
16.250 1.3281 0.07542 0.07144 -0.0244 0.0033 1.0000
16.500 1.3190 0.08079 0.07693 -0.0267 0.0033 1.0000
16.750 1.3061 0.08704 0.08331 -0.0294 0.0032 1.0000
17.000 1.2965 0.09295 0.08935 -0.0322 0.0032 1.0000
17.250 1.2840 0.09944 0.09596 -0.0353 0.0033 1.0000
17.500 1.2721 0.10599 0.10263 -0.0386 0.0033 1.0000
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