HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.8 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2010-il-1000000-n5.txt Download as CSV file: xf-hq2010-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8680 0.04566 0.04362 -0.0594 1.0000 0.0023
-12.500 -0.9011 0.03830 0.03603 -0.0645 1.0000 0.0023
-12.250 -0.9252 0.03456 0.03209 -0.0639 1.0000 0.0022
-12.000 -0.9308 0.03187 0.02922 -0.0625 1.0000 0.0023
-11.750 -0.9296 0.02940 0.02652 -0.0613 1.0000 0.0023
-11.500 -0.9211 0.02758 0.02454 -0.0602 1.0000 0.0024
-11.250 -0.9078 0.02630 0.02315 -0.0591 1.0000 0.0025
-11.000 -0.8944 0.02498 0.02170 -0.0580 1.0000 0.0025
-10.750 -0.8790 0.02390 0.02051 -0.0568 1.0000 0.0026
-10.500 -0.8589 0.02242 0.01885 -0.0569 0.9979 0.0027
-10.250 -0.8324 0.02124 0.01754 -0.0579 0.9922 0.0028
-10.000 -0.8039 0.02010 0.01625 -0.0592 0.9878 0.0029
-9.750 -0.7749 0.01873 0.01469 -0.0606 0.9832 0.0030
-9.500 -0.7457 0.01780 0.01361 -0.0617 0.9767 0.0032
-9.250 -0.7158 0.01672 0.01237 -0.0630 0.9704 0.0033
-9.000 -0.6873 0.01586 0.01136 -0.0638 0.9607 0.0035
-8.750 -0.6596 0.01511 0.01049 -0.0643 0.9494 0.0036
-8.500 -0.6336 0.01445 0.00969 -0.0643 0.9360 0.0037
-8.250 -0.6083 0.01396 0.00909 -0.0640 0.9228 0.0038
-8.000 -0.5851 0.01313 0.00809 -0.0635 0.9105 0.0040
-7.750 -0.5609 0.01252 0.00736 -0.0630 0.9002 0.0043
-7.500 -0.5357 0.01210 0.00684 -0.0627 0.8910 0.0046
-7.250 -0.5099 0.01177 0.00645 -0.0624 0.8826 0.0050
-6.750 -0.4580 0.01114 0.00567 -0.0619 0.8661 0.0058
-6.500 -0.4320 0.01083 0.00527 -0.0616 0.8585 0.0061
-6.250 -0.4055 0.01052 0.00489 -0.0614 0.8509 0.0063
-6.000 -0.3796 0.01007 0.00434 -0.0611 0.8443 0.0068
-5.750 -0.3531 0.00970 0.00389 -0.0609 0.8381 0.0075
-5.500 -0.3263 0.00942 0.00356 -0.0608 0.8327 0.0082
-5.250 -0.2991 0.00918 0.00328 -0.0607 0.8274 0.0091
-5.000 -0.2719 0.00896 0.00301 -0.0606 0.8216 0.0098
-4.750 -0.2447 0.00871 0.00273 -0.0605 0.8160 0.0121
-4.500 -0.2173 0.00848 0.00249 -0.0604 0.8097 0.0160
-4.250 -0.1901 0.00829 0.00229 -0.0604 0.8036 0.0222
-4.000 -0.1625 0.00809 0.00212 -0.0603 0.7970 0.0297
-3.750 -0.1350 0.00797 0.00196 -0.0603 0.7902 0.0342
-3.500 -0.1073 0.00781 0.00181 -0.0603 0.7833 0.0418
-3.250 -0.0797 0.00767 0.00167 -0.0602 0.7766 0.0500
-3.000 -0.0519 0.00752 0.00154 -0.0602 0.7693 0.0622
-2.750 -0.0246 0.00736 0.00141 -0.0602 0.7617 0.0830
-2.500 0.0029 0.00715 0.00129 -0.0602 0.7530 0.1157
-2.250 0.0301 0.00695 0.00117 -0.0601 0.7421 0.1552
-2.000 0.0570 0.00672 0.00106 -0.0601 0.7291 0.2098
-1.750 0.0841 0.00653 0.00097 -0.0600 0.7163 0.2578
-1.500 0.1111 0.00631 0.00088 -0.0600 0.7041 0.3162
-1.250 0.1376 0.00600 0.00080 -0.0599 0.6925 0.4093
-1.000 0.1643 0.00576 0.00076 -0.0598 0.6793 0.4908
-0.750 0.1915 0.00564 0.00076 -0.0597 0.6663 0.5425
-0.500 0.2188 0.00557 0.00077 -0.0596 0.6537 0.5871
-0.250 0.2462 0.00558 0.00078 -0.0595 0.6388 0.6121
0.000 0.2737 0.00562 0.00079 -0.0594 0.6227 0.6284
0.250 0.3015 0.00565 0.00081 -0.0593 0.6094 0.6422
0.500 0.3291 0.00569 0.00084 -0.0593 0.5948 0.6563
0.750 0.3565 0.00575 0.00087 -0.0592 0.5773 0.6722
1.000 0.3838 0.00582 0.00091 -0.0590 0.5589 0.6845
1.250 0.4113 0.00592 0.00096 -0.0590 0.5409 0.6924
1.500 0.4384 0.00603 0.00102 -0.0588 0.5204 0.7003
1.750 0.4655 0.00617 0.00109 -0.0587 0.4971 0.7076
2.000 0.4921 0.00634 0.00117 -0.0585 0.4639 0.7158
2.250 0.5178 0.00662 0.00129 -0.0582 0.4198 0.7237
2.500 0.5441 0.00684 0.00142 -0.0579 0.3900 0.7324
2.750 0.5699 0.00709 0.00156 -0.0577 0.3548 0.7410
3.000 0.5952 0.00741 0.00173 -0.0573 0.3090 0.7499
3.250 0.6203 0.00774 0.00191 -0.0569 0.2705 0.7593
3.500 0.6460 0.00800 0.00208 -0.0566 0.2434 0.7689
3.750 0.6723 0.00818 0.00222 -0.0564 0.2264 0.7787
4.250 0.7254 0.00847 0.00253 -0.0560 0.2040 0.8007
4.500 0.7512 0.00866 0.00269 -0.0557 0.1876 0.8129
4.750 0.7760 0.00894 0.00290 -0.0553 0.1602 0.8266
5.000 0.7993 0.00935 0.00317 -0.0546 0.1219 0.8432
5.250 0.8219 0.00974 0.00349 -0.0538 0.0903 0.8643
5.500 0.8429 0.01001 0.00378 -0.0525 0.0675 0.9107
5.750 0.8755 0.01041 0.00413 -0.0539 0.0450 1.0000
6.000 0.9004 0.01076 0.00442 -0.0535 0.0353 1.0000
6.250 0.9256 0.01105 0.00468 -0.0531 0.0294 1.0000
6.500 0.9503 0.01140 0.00501 -0.0527 0.0227 1.0000
6.750 0.9749 0.01174 0.00533 -0.0523 0.0176 1.0000
7.000 0.9983 0.01222 0.00573 -0.0517 0.0097 1.0000
7.250 1.0214 0.01272 0.00621 -0.0510 0.0040 1.0000
7.500 1.0453 0.01311 0.00663 -0.0505 0.0034 1.0000
7.750 1.0688 0.01355 0.00711 -0.0499 0.0029 1.0000
8.000 1.0920 0.01399 0.00762 -0.0492 0.0026 1.0000
8.250 1.1149 0.01446 0.00815 -0.0485 0.0024 1.0000
8.500 1.1379 0.01489 0.00862 -0.0479 0.0023 1.0000
8.750 1.1603 0.01536 0.00914 -0.0471 0.0022 1.0000
9.000 1.1823 0.01586 0.00970 -0.0464 0.0021 1.0000
9.250 1.2037 0.01638 0.01027 -0.0455 0.0021 1.0000
9.500 1.2244 0.01697 0.01092 -0.0445 0.0019 1.0000
9.750 1.2445 0.01757 0.01161 -0.0435 0.0019 1.0000
10.000 1.2637 0.01822 0.01233 -0.0424 0.0018 1.0000
10.250 1.2822 0.01889 0.01307 -0.0411 0.0017 1.0000
10.500 1.2995 0.01963 0.01388 -0.0398 0.0016 1.0000
10.750 1.3157 0.02039 0.01472 -0.0382 0.0015 1.0000
11.000 1.3300 0.02120 0.01562 -0.0364 0.0015 1.0000
11.250 1.3411 0.02202 0.01652 -0.0341 0.0014 1.0000
11.500 1.3493 0.02300 0.01759 -0.0314 0.0013 1.0000
11.750 1.3559 0.02409 0.01878 -0.0288 0.0013 1.0000
12.000 1.3597 0.02541 0.02021 -0.0260 0.0012 1.0000
12.250 1.3651 0.02667 0.02160 -0.0237 0.0012 1.0000
12.500 1.3663 0.02830 0.02336 -0.0212 0.0012 1.0000
12.750 1.3694 0.02988 0.02505 -0.0192 0.0012 1.0000
13.000 1.3498 0.03347 0.02888 -0.0161 0.0011 1.0000
13.250 1.3439 0.03615 0.03171 -0.0145 0.0011 1.0000
13.750 1.3385 0.04144 0.03725 -0.0129 0.0011 1.0000
14.000 1.3334 0.04462 0.04057 -0.0126 0.0011 1.0000
14.250 1.3283 0.04803 0.04411 -0.0128 0.0011 1.0000
14.500 1.3199 0.05209 0.04830 -0.0136 0.0011 1.0000
14.750 1.3091 0.05679 0.05316 -0.0149 0.0011 1.0000
15.000 1.3002 0.06160 0.05810 -0.0168 0.0011 1.0000
15.250 1.2791 0.06876 0.06544 -0.0201 0.0011 1.0000
15.500 1.2708 0.07434 0.07114 -0.0229 0.0011 1.0000
15.750 1.2474 0.08311 0.08008 -0.0278 0.0011 1.0000
16.000 1.2296 0.09135 0.08847 -0.0324 0.0011 1.0000
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