HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.61 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq358-il-1000000-n5.txt Download as CSV file: xf-hq358-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3380 0.10767 0.10600 -0.0312 1.0000 0.0033
-9.250 -0.3351 0.10472 0.10307 -0.0316 1.0000 0.0033
-9.000 -0.3327 0.10196 0.10033 -0.0319 1.0000 0.0034
-8.750 -0.3214 0.09796 0.09633 -0.0351 0.9987 0.0034
-8.500 -0.3106 0.09430 0.09267 -0.0379 0.9934 0.0034
-8.250 -0.2989 0.09051 0.08890 -0.0412 0.9888 0.0034
-8.000 -0.2857 0.08668 0.08507 -0.0450 0.9845 0.0034
-7.750 -0.2717 0.08268 0.08107 -0.0492 0.9790 0.0034
-7.500 -0.2532 0.07834 0.07673 -0.0548 0.9749 0.0034
-7.250 -0.2337 0.07375 0.07214 -0.0612 0.9678 0.0034
-7.000 -0.2112 0.06903 0.06740 -0.0687 0.9594 0.0034
-6.750 -0.1889 0.06413 0.06247 -0.0767 0.9470 0.0034
-6.500 -0.1712 0.05976 0.05804 -0.0833 0.9318 0.0034
-6.250 -0.1560 0.05503 0.05323 -0.0893 0.9170 0.0034
-6.000 -0.1400 0.05101 0.04911 -0.0934 0.9051 0.0034
-5.500 -0.1041 0.04308 0.04093 -0.0995 0.8857 0.0034
-5.250 -0.0836 0.03912 0.03680 -0.1018 0.8778 0.0034
-5.000 -0.0613 0.03546 0.03297 -0.1036 0.8702 0.0034
-4.750 -0.0376 0.03188 0.02919 -0.1049 0.8635 0.0034
-4.500 -0.0129 0.02852 0.02562 -0.1059 0.8568 0.0034
-4.250 0.0129 0.02534 0.02221 -0.1065 0.8507 0.0034
-4.000 0.0393 0.02221 0.01881 -0.1069 0.8443 0.0033
-3.750 0.0660 0.01842 0.01464 -0.1073 0.8385 0.0030
-3.500 0.0939 0.01531 0.01116 -0.1072 0.8324 0.0027
-3.250 0.1221 0.01296 0.00846 -0.1069 0.8267 0.0024
-3.000 0.1503 0.01121 0.00643 -0.1066 0.8196 0.0023
-2.750 0.1778 0.00994 0.00492 -0.1062 0.8095 0.0023
-2.500 0.2050 0.00904 0.00383 -0.1058 0.7957 0.0023
-2.250 0.2320 0.00840 0.00302 -0.1054 0.7801 0.0026
-2.000 0.2594 0.00810 0.00261 -0.1052 0.7678 0.0032
-1.750 0.2867 0.00767 0.00206 -0.1051 0.7560 0.0041
-1.500 0.3142 0.00737 0.00168 -0.1051 0.7444 0.0049
-1.250 0.3417 0.00722 0.00148 -0.1050 0.7332 0.0066
-1.000 0.3694 0.00706 0.00121 -0.1049 0.7210 0.0066
-0.750 0.3969 0.00699 0.00102 -0.1048 0.7052 0.0064
-0.500 0.4242 0.00698 0.00088 -0.1046 0.6877 0.0062
-0.250 0.4517 0.00698 0.00080 -0.1044 0.6728 0.0061
0.000 0.4790 0.00700 0.00076 -0.1043 0.6579 0.0061
0.250 0.5061 0.00706 0.00073 -0.1042 0.6412 0.0062
0.500 0.5333 0.00711 0.00069 -0.1041 0.6248 0.0058
0.750 0.5602 0.00719 0.00067 -0.1039 0.6057 0.0065
1.000 0.5865 0.00628 0.00079 -0.1044 0.5810 0.4746
1.250 0.6116 0.00603 0.00097 -0.1042 0.5533 0.6686
1.500 0.6366 0.00608 0.00111 -0.1036 0.5234 0.7456
1.750 0.6622 0.00631 0.00122 -0.1033 0.4875 0.7569
2.000 0.6876 0.00655 0.00135 -0.1029 0.4520 0.7689
2.250 0.7132 0.00678 0.00148 -0.1026 0.4194 0.7818
2.500 0.7384 0.00704 0.00162 -0.1022 0.3845 0.7964
2.750 0.7632 0.00730 0.00177 -0.1018 0.3474 0.8138
3.000 0.7876 0.00756 0.00194 -0.1012 0.3106 0.8372
3.250 0.8105 0.00766 0.00212 -0.1003 0.2860 0.8872
3.500 0.8391 0.00774 0.00226 -0.1005 0.2687 1.0000
3.750 0.8653 0.00796 0.00241 -0.1004 0.2543 1.0000
4.000 0.8913 0.00820 0.00258 -0.1002 0.2388 1.0000
4.250 0.9174 0.00842 0.00275 -0.1000 0.2253 1.0000
4.500 0.9437 0.00861 0.00295 -0.0998 0.2146 1.0000
4.750 0.9666 0.00917 0.00323 -0.0992 0.1639 1.0000
5.000 0.9877 0.00995 0.00366 -0.0983 0.1024 1.0000
5.250 1.0086 0.01075 0.00415 -0.0974 0.0488 1.0000
5.500 1.0302 0.01151 0.00469 -0.0965 0.0121 1.0000
5.750 1.0540 0.01198 0.00512 -0.0959 0.0024 1.0000
6.000 1.0786 0.01234 0.00552 -0.0955 0.0015 1.0000
6.250 1.1033 0.01269 0.00591 -0.0950 0.0011 1.0000
6.500 1.1278 0.01305 0.00633 -0.0945 0.0009 1.0000
6.750 1.1519 0.01344 0.00678 -0.0940 0.0008 1.0000
7.000 1.1757 0.01384 0.00723 -0.0935 0.0007 1.0000
7.250 1.1989 0.01431 0.00776 -0.0928 0.0005 1.0000
7.500 1.2211 0.01490 0.00844 -0.0919 0.0004 1.0000
7.750 1.2427 0.01556 0.00920 -0.0910 0.0004 1.0000
8.000 1.2632 0.01632 0.01007 -0.0898 0.0003 1.0000
8.250 1.2826 0.01718 0.01109 -0.0885 0.0003 1.0000
8.500 1.3011 0.01811 0.01215 -0.0871 0.0003 1.0000
8.750 1.3175 0.01923 0.01341 -0.0853 0.0003 1.0000
9.000 1.3322 0.02047 0.01480 -0.0833 0.0003 1.0000
9.250 1.3457 0.02178 0.01627 -0.0812 0.0003 1.0000
9.500 1.3561 0.02336 0.01804 -0.0786 0.0003 1.0000
9.750 1.3651 0.02500 0.01986 -0.0759 0.0003 1.0000
10.000 1.3700 0.02672 0.02177 -0.0725 0.0003 1.0000
10.250 1.3713 0.02876 0.02402 -0.0687 0.0003 1.0000
10.500 1.3714 0.03092 0.02640 -0.0651 0.0003 1.0000
10.750 1.3691 0.03334 0.02906 -0.0616 0.0003 1.0000
11.000 1.3639 0.03611 0.03207 -0.0582 0.0003 1.0000
11.250 1.3553 0.03927 0.03548 -0.0550 0.0003 1.0000
11.500 1.3468 0.04246 0.03890 -0.0524 0.0004 1.0000
11.750 1.3343 0.04624 0.04291 -0.0503 0.0004 1.0000
12.000 1.3192 0.05059 0.04749 -0.0488 0.0004 1.0000
12.250 1.3039 0.05525 0.05236 -0.0483 0.0004 1.0000
12.500 1.2868 0.06056 0.05787 -0.0487 0.0004 1.0000
12.750 1.2699 0.06637 0.06387 -0.0502 0.0004 1.0000
13.000 1.2525 0.07285 0.07053 -0.0528 0.0004 1.0000
13.250 1.2363 0.07986 0.07769 -0.0563 0.0004 1.0000
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Polar data table (+)
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