HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.93 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq358-il-1000000.txt Download as CSV file: xf-hq358-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3411 0.09776 0.09619 -0.0322 1.0000 0.0053
-8.500 -0.3434 0.09522 0.09366 -0.0316 1.0000 0.0053
-8.250 -0.3448 0.09266 0.09113 -0.0313 0.9997 0.0053
-8.000 -0.3296 0.08828 0.08675 -0.0360 0.9981 0.0053
-7.750 -0.3132 0.08403 0.08250 -0.0410 0.9955 0.0053
-7.500 -0.2980 0.07949 0.07798 -0.0462 0.9913 0.0053
-7.250 -0.2809 0.07491 0.07339 -0.0522 0.9864 0.0053
-7.000 -0.2564 0.06935 0.06784 -0.0611 0.9832 0.0053
-6.750 -0.2306 0.06359 0.06206 -0.0711 0.9785 0.0053
-6.500 -0.1992 0.05691 0.05533 -0.0832 0.9734 0.0053
-6.250 -0.1661 0.05043 0.04875 -0.0935 0.9691 0.0054
-6.000 -0.1434 0.04527 0.04346 -0.0988 0.9589 0.0054
-2.750 0.1759 0.00947 0.00460 -0.1064 0.8657 0.0096
-2.500 0.2026 0.00824 0.00320 -0.1059 0.8566 0.0089
-2.250 0.2297 0.00756 0.00236 -0.1055 0.8473 0.0088
-2.000 0.2575 0.00713 0.00180 -0.1054 0.8385 0.0094
-1.750 0.2855 0.00685 0.00139 -0.1052 0.8309 0.0113
-1.500 0.3133 0.00669 0.00114 -0.1051 0.8226 0.0146
-1.250 0.3412 0.00645 0.00101 -0.1051 0.8144 0.0546
-1.000 0.3684 0.00595 0.00092 -0.1053 0.8056 0.2166
-0.750 0.3949 0.00524 0.00086 -0.1056 0.7955 0.4775
-0.500 0.4218 0.00498 0.00088 -0.1055 0.7855 0.5952
-0.250 0.4484 0.00485 0.00093 -0.1052 0.7756 0.6807
0.000 0.4754 0.00483 0.00095 -0.1049 0.7656 0.7152
0.250 0.5025 0.00483 0.00096 -0.1047 0.7554 0.7408
0.500 0.5293 0.00481 0.00099 -0.1044 0.7446 0.7728
0.750 0.5561 0.00482 0.00101 -0.1041 0.7324 0.7956
1.000 0.5830 0.00484 0.00103 -0.1039 0.7199 0.8107
1.250 0.6096 0.00486 0.00106 -0.1036 0.7067 0.8287
1.500 0.6356 0.00487 0.00108 -0.1032 0.6910 0.8526
1.750 0.6586 0.00476 0.00111 -0.1020 0.6751 0.9151
2.000 0.6907 0.00480 0.00113 -0.1029 0.6565 1.0000
2.250 0.7174 0.00495 0.00119 -0.1027 0.6342 1.0000
2.500 0.7436 0.00514 0.00129 -0.1025 0.6064 1.0000
2.750 0.7691 0.00539 0.00138 -0.1021 0.5691 1.0000
3.000 0.7939 0.00571 0.00152 -0.1016 0.5254 1.0000
3.250 0.8184 0.00608 0.00168 -0.1011 0.4779 1.0000
3.500 0.8426 0.00648 0.00187 -0.1005 0.4304 1.0000
3.750 0.8671 0.00687 0.00208 -0.1001 0.3869 1.0000
4.000 0.8908 0.00734 0.00234 -0.0995 0.3359 1.0000
4.250 0.9152 0.00775 0.00257 -0.0990 0.2965 1.0000
4.500 0.9390 0.00820 0.00283 -0.0985 0.2577 1.0000
4.750 0.9637 0.00856 0.00306 -0.0981 0.2299 1.0000
5.000 0.9879 0.00897 0.00330 -0.0977 0.1967 1.0000
5.250 1.0119 0.00940 0.00360 -0.0972 0.1621 1.0000
5.500 1.0322 0.01025 0.00408 -0.0961 0.0985 1.0000
5.750 1.0491 0.01153 0.00489 -0.0946 0.0205 1.0000
6.000 1.0713 0.01226 0.00558 -0.0935 0.0044 1.0000
6.250 1.0955 0.01269 0.00609 -0.0929 0.0041 1.0000
6.500 1.1189 0.01322 0.00671 -0.0921 0.0040 1.0000
6.750 1.1415 0.01385 0.00746 -0.0912 0.0039 1.0000
7.000 1.1630 0.01459 0.00835 -0.0901 0.0039 1.0000
7.250 1.1829 0.01552 0.00941 -0.0887 0.0040 1.0000
7.500 1.2007 0.01665 0.01068 -0.0869 0.0041 1.0000
7.750 1.2183 0.01777 0.01191 -0.0852 0.0040 1.0000
8.000 1.2367 0.01876 0.01300 -0.0838 0.0039 1.0000
8.250 1.2551 0.01973 0.01407 -0.0823 0.0036 1.0000
8.500 1.2697 0.02128 0.01576 -0.0802 0.0037 1.0000
8.750 1.2853 0.02276 0.01737 -0.0784 0.0036 1.0000
9.000 1.3000 0.02455 0.01932 -0.0764 0.0036 1.0000
9.250 1.3147 0.02632 0.02124 -0.0746 0.0035 1.0000
9.500 1.3283 0.02812 0.02324 -0.0726 0.0033 1.0000
9.750 1.3411 0.02945 0.02470 -0.0707 0.0030 1.0000
10.000 1.3504 0.03096 0.02634 -0.0683 0.0028 1.0000
10.250 1.3547 0.03225 0.02773 -0.0653 0.0026 1.0000
10.500 1.3543 0.03461 0.03030 -0.0617 0.0025 1.0000
10.750 1.3202 0.04374 0.04022 -0.0542 0.0034 1.0000
11.000 1.3085 0.04682 0.04351 -0.0507 0.0033 1.0000
11.250 1.2944 0.05030 0.04720 -0.0479 0.0033 1.0000
11.500 1.2799 0.05398 0.05107 -0.0459 0.0033 1.0000
11.750 1.2644 0.05806 0.05533 -0.0448 0.0033 1.0000
12.000 1.2472 0.06277 0.06022 -0.0446 0.0033 1.0000
12.250 1.2286 0.06815 0.06578 -0.0455 0.0033 1.0000
12.500 1.2094 0.07423 0.07202 -0.0475 0.0033 1.0000
12.750 1.1896 0.08116 0.07911 -0.0508 0.0033 1.0000
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Polar data table (+)
Polar graphs
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