HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.53 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq208-il-1000000-n5.txt Download as CSV file: xf-hq208-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4884 0.11982 0.11811 -0.0087 1.0000 0.0027
-10.750 -0.4848 0.11584 0.11414 -0.0102 1.0000 0.0028
-7.250 -0.4642 0.05182 0.05017 -0.0513 0.9877 0.0030
-7.000 -0.4430 0.04312 0.04120 -0.0593 0.9779 0.0029
-6.750 -0.4214 0.03442 0.03212 -0.0644 0.9653 0.0027
-6.250 -0.3895 0.01690 0.01304 -0.0651 0.9308 0.0025
-6.000 -0.3670 0.01430 0.00998 -0.0644 0.9185 0.0025
-5.750 -0.3429 0.01265 0.00800 -0.0638 0.9079 0.0025
-5.500 -0.3181 0.01142 0.00652 -0.0632 0.8985 0.0026
-5.250 -0.2926 0.01055 0.00546 -0.0628 0.8901 0.0028
-5.000 -0.2665 0.00994 0.00471 -0.0624 0.8819 0.0030
-4.750 -0.2398 0.00957 0.00425 -0.0622 0.8747 0.0032
-4.500 -0.2138 0.00889 0.00342 -0.0619 0.8672 0.0040
-4.250 -0.1867 0.00862 0.00310 -0.0618 0.8606 0.0046
-4.000 -0.1596 0.00834 0.00276 -0.0617 0.8537 0.0053
-3.750 -0.1322 0.00814 0.00249 -0.0616 0.8472 0.0061
-3.500 -0.1049 0.00791 0.00220 -0.0615 0.8403 0.0074
-3.250 -0.0774 0.00765 0.00188 -0.0614 0.8335 0.0092
-3.000 -0.0499 0.00749 0.00164 -0.0613 0.8260 0.0105
-2.750 -0.0222 0.00734 0.00145 -0.0612 0.8180 0.0127
-2.500 0.0051 0.00715 0.00129 -0.0611 0.8092 0.0284
-2.250 0.0327 0.00702 0.00116 -0.0611 0.7991 0.0423
-2.000 0.0600 0.00691 0.00104 -0.0610 0.7861 0.0579
-1.750 0.0871 0.00679 0.00094 -0.0608 0.7699 0.0824
-1.500 0.1138 0.00648 0.00081 -0.0608 0.7544 0.1634
-1.250 0.1400 0.00594 0.00070 -0.0608 0.7406 0.3198
-1.000 0.1666 0.00562 0.00063 -0.0608 0.7263 0.4251
-0.750 0.1936 0.00545 0.00060 -0.0607 0.7115 0.4933
-0.500 0.2204 0.00530 0.00059 -0.0606 0.6943 0.5655
-0.250 0.2469 0.00521 0.00062 -0.0603 0.6757 0.6328
0.000 0.2740 0.00520 0.00064 -0.0602 0.6594 0.6653
0.250 0.3014 0.00522 0.00066 -0.0600 0.6445 0.6880
0.500 0.3285 0.00525 0.00069 -0.0599 0.6261 0.7079
1.000 0.3831 0.00540 0.00075 -0.0596 0.5871 0.7303
1.250 0.4101 0.00552 0.00080 -0.0595 0.5608 0.7407
1.500 0.4369 0.00566 0.00087 -0.0593 0.5306 0.7513
1.750 0.4633 0.00584 0.00095 -0.0591 0.4946 0.7622
2.000 0.4895 0.00605 0.00104 -0.0588 0.4559 0.7738
2.250 0.5150 0.00635 0.00117 -0.0585 0.4042 0.7860
2.500 0.5390 0.00685 0.00136 -0.0580 0.3205 0.7991
2.750 0.5632 0.00730 0.00158 -0.0575 0.2531 0.8138
3.000 0.5883 0.00759 0.00174 -0.0571 0.2117 0.8309
3.250 0.6139 0.00775 0.00188 -0.0567 0.1884 0.8519
3.500 0.6384 0.00783 0.00202 -0.0560 0.1716 0.8863
3.750 0.6703 0.00793 0.00217 -0.0570 0.1463 1.0000
4.000 0.6961 0.00827 0.00240 -0.0568 0.1165 1.0000
4.250 0.7201 0.00886 0.00273 -0.0563 0.0647 1.0000
4.500 0.7452 0.00928 0.00302 -0.0560 0.0386 1.0000
4.750 0.7711 0.00958 0.00326 -0.0558 0.0269 1.0000
5.000 0.7965 0.00996 0.00355 -0.0555 0.0150 1.0000
5.250 0.8218 0.01035 0.00390 -0.0551 0.0053 1.0000
5.500 0.8477 0.01065 0.00422 -0.0548 0.0032 1.0000
5.750 0.8735 0.01096 0.00457 -0.0545 0.0027 1.0000
6.000 0.8990 0.01129 0.00495 -0.0542 0.0024 1.0000
6.250 0.9243 0.01166 0.00537 -0.0538 0.0022 1.0000
6.500 0.9490 0.01212 0.00590 -0.0534 0.0018 1.0000
6.750 0.9723 0.01281 0.00670 -0.0526 0.0015 1.0000
7.000 0.9960 0.01340 0.00736 -0.0520 0.0013 1.0000
7.250 1.0200 0.01393 0.00799 -0.0515 0.0013 1.0000
7.500 1.0429 0.01463 0.00878 -0.0507 0.0012 1.0000
7.750 1.0654 0.01536 0.00960 -0.0500 0.0011 1.0000
8.000 1.0869 0.01622 0.01058 -0.0490 0.0011 1.0000
8.250 1.1075 0.01718 0.01167 -0.0480 0.0011 1.0000
8.500 1.1270 0.01830 0.01292 -0.0468 0.0011 1.0000
8.750 1.1460 0.01946 0.01424 -0.0456 0.0010 1.0000
9.000 1.1637 0.02081 0.01576 -0.0442 0.0010 1.0000
9.250 1.1801 0.02231 0.01745 -0.0427 0.0010 1.0000
9.500 1.1954 0.02391 0.01924 -0.0411 0.0010 1.0000
9.750 1.2081 0.02579 0.02136 -0.0392 0.0010 1.0000
10.000 1.2189 0.02777 0.02360 -0.0372 0.0010 1.0000
10.250 1.2262 0.02998 0.02607 -0.0349 0.0010 1.0000
10.500 1.2281 0.03257 0.02893 -0.0321 0.0010 1.0000
10.750 1.2235 0.03496 0.03156 -0.0284 0.0010 1.0000
11.000 1.2155 0.03727 0.03408 -0.0247 0.0010 1.0000
11.250 1.2027 0.04021 0.03724 -0.0215 0.0010 1.0000
11.500 1.1907 0.04332 0.04054 -0.0195 0.0010 1.0000
11.750 1.1739 0.04738 0.04481 -0.0185 0.0010 1.0000
12.000 1.1576 0.05192 0.04953 -0.0188 0.0010 1.0000
12.250 1.1399 0.05735 0.05514 -0.0206 0.0010 1.0000
12.500 1.1222 0.06371 0.06165 -0.0240 0.0011 1.0000
12.750 1.1035 0.07154 0.06964 -0.0291 0.0011 1.0000
13.000 1.0822 0.08170 0.07995 -0.0363 0.0011 1.0000
13.250 1.0620 0.09311 0.09149 -0.0438 0.0011 1.0000
13.500 1.0420 0.10438 0.10284 -0.0503 0.0011 1.0000
13.750 1.0165 0.11709 0.11563 -0.0569 0.0011 1.0000
14.000 0.9882 0.13092 0.12947 -0.0635 0.0011 1.0000
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Polar data table (+)
Polar graphs
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