HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 AIRFOIL (hq259-il) Reynolds number: 1,000,000 Max Cl/Cd: 122 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259-il-1000000.txt Download as CSV file: xf-hq259-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4089 0.08265 0.08110 -0.0336 1.0000 0.0073
-8.250 -0.4106 0.07901 0.07749 -0.0349 1.0000 0.0072
-8.000 -0.4161 0.07542 0.07394 -0.0359 1.0000 0.0073
-7.750 -0.4306 0.07272 0.07130 -0.0348 1.0000 0.0073
-7.500 -0.4191 0.06578 0.06436 -0.0457 0.9959 0.0073
-7.250 -0.3968 0.05618 0.05465 -0.0610 0.9884 0.0075
-7.000 -0.3719 0.04828 0.04657 -0.0706 0.9837 0.0080
-6.750 -0.3442 0.04212 0.04021 -0.0764 0.9788 0.0087
-6.500 -0.3141 0.03829 0.03620 -0.0791 0.9729 0.0092
-6.250 -0.2902 0.03309 0.03070 -0.0819 0.9646 0.0093
-6.000 -0.2922 0.01648 0.01253 -0.0812 0.9451 0.0055
-5.750 -0.2711 0.01364 0.00930 -0.0804 0.9360 0.0062
-5.500 -0.2455 0.01303 0.00858 -0.0801 0.9284 0.0068
-5.250 -0.2201 0.01220 0.00761 -0.0797 0.9202 0.0073
-5.000 -0.1945 0.01132 0.00657 -0.0792 0.9128 0.0076
-4.750 -0.1689 0.01052 0.00564 -0.0787 0.9050 0.0079
-4.500 -0.1427 0.00996 0.00497 -0.0784 0.8979 0.0084
-4.250 -0.1162 0.00950 0.00441 -0.0780 0.8905 0.0089
-4.000 -0.0900 0.00886 0.00364 -0.0777 0.8834 0.0091
-3.750 -0.0632 0.00841 0.00309 -0.0774 0.8761 0.0093
-3.500 -0.0366 0.00770 0.00220 -0.0770 0.8689 0.0128
-3.250 -0.0094 0.00741 0.00189 -0.0767 0.8614 0.0226
-3.000 0.0180 0.00720 0.00172 -0.0766 0.8532 0.0414
-2.750 0.0452 0.00706 0.00157 -0.0765 0.8454 0.0564
-2.500 0.0728 0.00688 0.00143 -0.0765 0.8374 0.0770
-2.250 0.0998 0.00653 0.00129 -0.0765 0.8303 0.1476
-2.000 0.1257 0.00582 0.00112 -0.0766 0.8227 0.3232
-1.750 0.1519 0.00531 0.00102 -0.0766 0.8152 0.4756
-1.500 0.1789 0.00512 0.00098 -0.0764 0.8065 0.5458
-1.250 0.2064 0.00503 0.00095 -0.0763 0.7966 0.5878
-1.000 0.2339 0.00498 0.00093 -0.0762 0.7864 0.6168
-0.750 0.2612 0.00495 0.00091 -0.0760 0.7758 0.6487
-0.500 0.2886 0.00494 0.00091 -0.0758 0.7654 0.6724
-0.250 0.3161 0.00491 0.00092 -0.0757 0.7558 0.6996
0.000 0.3433 0.00490 0.00095 -0.0755 0.7462 0.7265
0.250 0.3707 0.00492 0.00096 -0.0753 0.7353 0.7422
0.500 0.3981 0.00495 0.00097 -0.0751 0.7231 0.7555
0.750 0.4256 0.00498 0.00098 -0.0750 0.7109 0.7661
1.000 0.4532 0.00501 0.00099 -0.0749 0.6984 0.7767
1.250 0.4805 0.00504 0.00103 -0.0748 0.6854 0.7876
1.500 0.5075 0.00509 0.00106 -0.0745 0.6701 0.7992
1.750 0.5343 0.00515 0.00110 -0.0743 0.6522 0.8118
2.000 0.5610 0.00521 0.00114 -0.0740 0.6329 0.8259
2.250 0.5873 0.00528 0.00120 -0.0737 0.6132 0.8425
2.500 0.6127 0.00535 0.00128 -0.0732 0.5880 0.8637
2.750 0.6363 0.00539 0.00135 -0.0722 0.5602 0.9025
3.000 0.6698 0.00549 0.00143 -0.0735 0.5224 1.0000
3.250 0.6951 0.00581 0.00156 -0.0731 0.4787 1.0000
3.500 0.7200 0.00617 0.00174 -0.0727 0.4312 1.0000
3.750 0.7449 0.00654 0.00192 -0.0723 0.3864 1.0000
4.000 0.7702 0.00688 0.00211 -0.0720 0.3479 1.0000
4.250 0.7941 0.00736 0.00234 -0.0715 0.2946 1.0000
4.500 0.8182 0.00781 0.00259 -0.0710 0.2508 1.0000
4.750 0.8430 0.00820 0.00284 -0.0706 0.2166 1.0000
5.000 0.8672 0.00865 0.00310 -0.0702 0.1786 1.0000
5.250 0.8915 0.00907 0.00337 -0.0697 0.1456 1.0000
5.500 0.9151 0.00958 0.00369 -0.0692 0.1106 1.0000
5.750 0.9346 0.01057 0.00427 -0.0680 0.0434 1.0000
6.000 0.9549 0.01150 0.00497 -0.0669 0.0063 1.0000
6.250 0.9799 0.01185 0.00539 -0.0664 0.0056 1.0000
6.500 1.0044 0.01226 0.00585 -0.0659 0.0050 1.0000
6.750 1.0282 0.01274 0.00639 -0.0653 0.0044 1.0000
7.000 1.0494 0.01359 0.00737 -0.0641 0.0036 1.0000
7.500 1.0883 0.01560 0.00965 -0.0613 0.0033 1.0000
7.750 1.1069 0.01664 0.01080 -0.0598 0.0033 1.0000
8.000 1.1225 0.01802 0.01232 -0.0579 0.0033 1.0000
8.250 1.1375 0.01955 0.01396 -0.0559 0.0034 1.0000
8.500 1.1570 0.02044 0.01494 -0.0547 0.0035 1.0000
8.750 1.1763 0.02133 0.01591 -0.0534 0.0036 1.0000
9.000 1.1954 0.02221 0.01690 -0.0521 0.0038 1.0000
17.250 0.9703 0.22187 0.22037 -0.1097 0.0061 1.0000
17.500 0.9783 0.22607 0.22457 -0.1120 0.0059 1.0000
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Polar data table (+)
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