HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/9 AIRFOIL (hq359-il) Reynolds number: 500,000 Max Cl/Cd: 101.08 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq359-il-500000-n5.txt Download as CSV file: xf-hq359-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3366 0.10684 0.10452 -0.0357 1.0000 0.0068
-9.500 -0.3348 0.10369 0.10140 -0.0362 1.0000 0.0068
-9.000 -0.3346 0.09768 0.09547 -0.0365 1.0000 0.0068
-8.500 -0.3190 0.08984 0.08765 -0.0413 0.9937 0.0055
-8.250 -0.3085 0.08517 0.08299 -0.0456 0.9885 0.0050
-8.000 -0.2979 0.08006 0.07789 -0.0506 0.9826 0.0046
-7.750 -0.2851 0.07497 0.07281 -0.0565 0.9762 0.0046
-7.500 -0.2692 0.07012 0.06797 -0.0632 0.9691 0.0047
-7.250 -0.2482 0.06464 0.06248 -0.0724 0.9615 0.0054
-7.000 -0.2270 0.05749 0.05529 -0.0847 0.9501 0.0052
-6.750 -0.2071 0.05104 0.04871 -0.0937 0.9384 0.0058
-6.500 -0.1895 0.04535 0.04285 -0.0992 0.9275 0.0061
-6.250 -0.1705 0.04035 0.03763 -0.1025 0.9184 0.0065
-6.000 -0.1518 0.03565 0.03269 -0.1046 0.9093 0.0066
-5.750 -0.1328 0.03071 0.02742 -0.1061 0.9015 0.0063
-5.500 -0.1114 0.02577 0.02206 -0.1070 0.8944 0.0061
-5.250 -0.0886 0.02050 0.01624 -0.1072 0.8878 0.0059
-5.000 -0.0638 0.01680 0.01196 -0.1070 0.8816 0.0060
-4.750 -0.0375 0.01473 0.00949 -0.1068 0.8763 0.0062
-4.500 -0.0109 0.01347 0.00796 -0.1066 0.8703 0.0066
-4.250 0.0163 0.01272 0.00698 -0.1064 0.8652 0.0069
-4.000 0.0423 0.01130 0.00534 -0.1061 0.8593 0.0076
-3.750 0.0692 0.01082 0.00481 -0.1061 0.8538 0.0089
-3.500 0.0964 0.01028 0.00416 -0.1060 0.8484 0.0093
-3.250 0.1238 0.00976 0.00354 -0.1058 0.8423 0.0095
-3.000 0.1514 0.00937 0.00303 -0.1057 0.8370 0.0099
-2.750 0.1791 0.00906 0.00262 -0.1057 0.8306 0.0105
-2.500 0.2069 0.00884 0.00229 -0.1056 0.8245 0.0113
-2.250 0.2347 0.00862 0.00203 -0.1055 0.8171 0.0150
-2.000 0.2622 0.00844 0.00185 -0.1054 0.8083 0.0308
-1.500 0.3165 0.00814 0.00156 -0.1051 0.7835 0.0756
-1.250 0.3437 0.00793 0.00145 -0.1051 0.7721 0.1276
-1.000 0.3697 0.00694 0.00136 -0.1055 0.7624 0.4466
-0.750 0.3963 0.00671 0.00136 -0.1054 0.7524 0.5530
-0.500 0.4228 0.00662 0.00139 -0.1050 0.7412 0.6199
-0.250 0.4495 0.00658 0.00142 -0.1047 0.7300 0.6650
0.000 0.4759 0.00657 0.00146 -0.1043 0.7184 0.7060
0.250 0.5027 0.00661 0.00146 -0.1040 0.7044 0.7244
0.500 0.5295 0.00666 0.00146 -0.1037 0.6891 0.7336
0.750 0.5565 0.00672 0.00148 -0.1035 0.6762 0.7431
1.250 0.6099 0.00687 0.00155 -0.1030 0.6474 0.7634
1.500 0.6363 0.00696 0.00159 -0.1027 0.6305 0.7745
1.750 0.6624 0.00705 0.00165 -0.1023 0.6120 0.7866
2.000 0.6879 0.00718 0.00173 -0.1018 0.5891 0.8001
2.250 0.7128 0.00732 0.00183 -0.1012 0.5627 0.8157
2.500 0.7371 0.00749 0.00193 -0.1005 0.5339 0.8348
2.750 0.7598 0.00766 0.00206 -0.0995 0.4990 0.8625
3.000 0.7874 0.00779 0.00218 -0.0995 0.4616 1.0000
3.250 0.8117 0.00815 0.00237 -0.0990 0.4257 1.0000
3.500 0.8360 0.00853 0.00260 -0.0985 0.3892 1.0000
3.750 0.8602 0.00892 0.00283 -0.0980 0.3544 1.0000
4.000 0.8844 0.00930 0.00306 -0.0975 0.3204 1.0000
4.250 0.9088 0.00967 0.00331 -0.0971 0.2948 1.0000
4.500 0.9336 0.01000 0.00358 -0.0967 0.2763 1.0000
4.750 0.9585 0.01031 0.00384 -0.0963 0.2614 1.0000
5.000 0.9823 0.01071 0.00414 -0.0958 0.2368 1.0000
5.250 1.0057 0.01115 0.00443 -0.0952 0.2088 1.0000
5.500 1.0299 0.01150 0.00472 -0.0947 0.1905 1.0000
5.750 1.0532 0.01194 0.00506 -0.0941 0.1619 1.0000
6.000 1.0728 0.01274 0.00555 -0.0931 0.1112 1.0000
6.250 1.0925 0.01354 0.00611 -0.0920 0.0711 1.0000
6.500 1.1073 0.01487 0.00705 -0.0901 0.0138 1.0000
6.750 1.1284 0.01553 0.00767 -0.0891 0.0052 1.0000
7.000 1.1507 0.01603 0.00823 -0.0883 0.0042 1.0000
7.250 1.1726 0.01657 0.00886 -0.0874 0.0036 1.0000
7.500 1.1940 0.01713 0.00956 -0.0864 0.0034 1.0000
7.750 1.2148 0.01774 0.01027 -0.0853 0.0032 1.0000
8.000 1.2344 0.01844 0.01108 -0.0841 0.0031 1.0000
8.250 1.2530 0.01922 0.01197 -0.0827 0.0030 1.0000
8.500 1.2702 0.02007 0.01294 -0.0812 0.0029 1.0000
8.750 1.2859 0.02099 0.01397 -0.0794 0.0028 1.0000
9.000 1.3004 0.02191 0.01499 -0.0775 0.0026 1.0000
9.250 1.3123 0.02284 0.01601 -0.0752 0.0024 1.0000
9.500 1.3221 0.02389 0.01715 -0.0726 0.0022 1.0000
9.750 1.3292 0.02514 0.01855 -0.0698 0.0021 1.0000
10.000 1.3324 0.02670 0.02024 -0.0666 0.0020 1.0000
10.250 1.3336 0.02851 0.02219 -0.0635 0.0019 1.0000
10.500 1.3324 0.03067 0.02451 -0.0603 0.0018 1.0000
10.750 1.3371 0.03238 0.02636 -0.0580 0.0018 1.0000
11.000 1.3422 0.03409 0.02821 -0.0560 0.0018 1.0000
11.250 1.3476 0.03580 0.03007 -0.0542 0.0017 1.0000
11.500 1.3505 0.03784 0.03226 -0.0524 0.0017 1.0000
11.750 1.3534 0.03995 0.03454 -0.0509 0.0016 1.0000
12.000 1.3525 0.04256 0.03732 -0.0493 0.0016 1.0000
12.250 1.3519 0.04523 0.04016 -0.0481 0.0015 1.0000
12.500 1.3489 0.04829 0.04341 -0.0471 0.0015 1.0000
12.750 1.3448 0.05163 0.04694 -0.0465 0.0014 1.0000
13.000 1.3381 0.05547 0.05097 -0.0463 0.0014 1.0000
13.250 1.3303 0.05964 0.05534 -0.0465 0.0014 1.0000
13.500 1.3203 0.06440 0.06029 -0.0473 0.0014 1.0000
13.750 1.3093 0.06960 0.06568 -0.0486 0.0013 1.0000
14.000 1.2975 0.07531 0.07159 -0.0506 0.0013 1.0000
14.250 1.2844 0.08165 0.07812 -0.0533 0.0013 1.0000
14.500 1.2703 0.08863 0.08528 -0.0567 0.0013 1.0000
14.750 1.2559 0.09613 0.09296 -0.0607 0.0013 1.0000
15.000 1.2413 0.10408 0.10109 -0.0651 0.0013 1.0000
15.250 1.2259 0.11256 0.10973 -0.0700 0.0013 1.0000
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