HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 200,000 Max Cl/Cd: 86.97 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3510-il-200000.txt Download as CSV file: xf-hq3510-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3768 0.09288 0.08980 -0.0335 1.0000 0.0374
-7.750 -0.3953 0.09178 0.08880 -0.0309 1.0000 0.0375
-7.500 -0.4162 0.09083 0.08793 -0.0279 1.0000 0.0376
-7.250 -0.3912 0.08342 0.08048 -0.0451 0.9926 0.0381
-7.000 -0.3674 0.07685 0.07376 -0.0566 0.9859 0.0383
-6.750 -0.3552 0.06843 0.06535 -0.0624 0.9824 0.0394
-6.500 -0.3410 0.06514 0.06208 -0.0630 0.9768 0.0405
-6.250 -0.3177 0.06117 0.05806 -0.0673 0.9724 0.0423
-6.000 -0.2906 0.05631 0.05306 -0.0740 0.9678 0.0450
-5.750 -0.2527 0.05287 0.04881 -0.0831 0.9591 0.0509
-5.500 -0.2335 0.04560 0.04175 -0.0865 0.9568 0.0541
-5.250 -0.2115 0.04271 0.03873 -0.0880 0.9504 0.0571
-4.500 -0.1088 0.02824 0.02252 -0.0961 0.9379 0.0408
-4.250 -0.0760 0.02466 0.01849 -0.0969 0.9337 0.0331
-4.000 -0.0380 0.02153 0.01478 -0.0984 0.9313 0.0312
-3.750 0.0015 0.01965 0.01260 -0.1004 0.9295 0.0325
-3.500 0.0413 0.01889 0.01160 -0.1024 0.9274 0.0379
-3.250 0.0643 0.01732 0.00998 -0.1014 0.9203 0.0410
-3.000 0.1008 0.01608 0.00875 -0.1030 0.9174 0.0535
-2.750 0.1390 0.01524 0.00797 -0.1051 0.9151 0.0836
-2.500 0.1647 0.01489 0.00762 -0.1049 0.9082 0.1073
-2.250 0.1980 0.01394 0.00696 -0.1062 0.9041 0.1682
-2.000 0.2263 0.01237 0.00699 -0.1066 0.9011 0.6319
-1.750 0.2488 0.01242 0.00709 -0.1051 0.8933 0.6862
-1.500 0.2796 0.01232 0.00698 -0.1050 0.8889 0.7281
-1.250 0.3068 0.01226 0.00692 -0.1042 0.8834 0.7613
-1.000 0.3298 0.01220 0.00691 -0.1024 0.8764 0.7969
-0.750 0.3566 0.01195 0.00669 -0.1009 0.8725 0.8334
-0.500 0.3749 0.01181 0.00658 -0.0984 0.8630 0.8601
-0.250 0.4049 0.01147 0.00619 -0.0981 0.8574 0.8764
0.000 0.4290 0.01125 0.00597 -0.0969 0.8480 0.8942
0.250 0.4571 0.01101 0.00570 -0.0965 0.8403 0.9150
0.500 0.4933 0.01073 0.00541 -0.0977 0.8329 0.9434
0.750 0.5371 0.01053 0.00516 -0.1010 0.8240 1.0000
1.000 0.5697 0.01039 0.00491 -0.1019 0.8165 1.0000
1.250 0.5973 0.01042 0.00489 -0.1021 0.8062 1.0000
1.500 0.6264 0.01043 0.00483 -0.1024 0.7975 1.0000
1.750 0.6566 0.01037 0.00470 -0.1028 0.7893 1.0000
2.000 0.6836 0.01041 0.00472 -0.1026 0.7784 1.0000
2.250 0.7113 0.01042 0.00470 -0.1025 0.7681 1.0000
2.500 0.7395 0.01042 0.00465 -0.1024 0.7577 1.0000
2.750 0.7674 0.01042 0.00460 -0.1022 0.7463 1.0000
3.000 0.7944 0.01044 0.00463 -0.1018 0.7336 1.0000
3.250 0.8210 0.01048 0.00465 -0.1014 0.7197 1.0000
3.500 0.8472 0.01053 0.00468 -0.1009 0.7042 1.0000
3.750 0.8727 0.01060 0.00475 -0.1003 0.6863 1.0000
4.000 0.8984 0.01068 0.00482 -0.0996 0.6668 1.0000
4.250 0.9233 0.01080 0.00490 -0.0989 0.6441 1.0000
4.500 0.9475 0.01095 0.00500 -0.0980 0.6173 1.0000
4.750 0.9706 0.01116 0.00512 -0.0969 0.5837 1.0000
5.000 0.9922 0.01148 0.00532 -0.0955 0.5422 1.0000
5.250 1.0118 0.01196 0.00557 -0.0939 0.4938 1.0000
5.500 1.0300 0.01259 0.00594 -0.0922 0.4447 1.0000
5.750 1.0484 0.01328 0.00641 -0.0906 0.4038 1.0000
6.000 1.0677 0.01394 0.00690 -0.0893 0.3721 1.0000
6.250 1.0880 0.01456 0.00744 -0.0881 0.3467 1.0000
6.500 1.1084 0.01518 0.00796 -0.0870 0.3265 1.0000
6.750 1.1295 0.01574 0.00851 -0.0860 0.3087 1.0000
7.000 1.1505 0.01632 0.00908 -0.0850 0.2932 1.0000
7.250 1.1713 0.01691 0.00968 -0.0840 0.2785 1.0000
7.500 1.1910 0.01750 0.01026 -0.0828 0.2618 1.0000
7.750 1.2088 0.01805 0.01082 -0.0814 0.2409 1.0000
8.000 1.2261 0.01853 0.01129 -0.0799 0.2172 1.0000
8.250 1.2448 0.01901 0.01182 -0.0786 0.1960 1.0000
8.500 1.2618 0.01958 0.01237 -0.0771 0.1710 1.0000
8.750 1.2763 0.02033 0.01302 -0.0753 0.1395 1.0000
9.000 1.2853 0.02146 0.01393 -0.0727 0.1010 1.0000
9.250 1.2786 0.02400 0.01584 -0.0682 0.0375 1.0000
9.500 1.2794 0.02597 0.01776 -0.0645 0.0234 1.0000
9.750 1.2810 0.02778 0.01967 -0.0613 0.0200 1.0000
10.000 1.2830 0.02957 0.02166 -0.0582 0.0184 1.0000
10.250 1.2869 0.03127 0.02352 -0.0556 0.0174 1.0000
10.500 1.2898 0.03314 0.02553 -0.0532 0.0167 1.0000
10.750 1.2924 0.03515 0.02767 -0.0509 0.0159 1.0000
11.000 1.2950 0.03729 0.02994 -0.0489 0.0154 1.0000
11.250 1.2977 0.03957 0.03234 -0.0470 0.0149 1.0000
11.500 1.3013 0.04194 0.03484 -0.0454 0.0146 1.0000
11.750 1.3059 0.04443 0.03746 -0.0438 0.0143 1.0000
12.000 1.3114 0.04703 0.04021 -0.0424 0.0142 1.0000
12.250 1.3169 0.04986 0.04321 -0.0412 0.0140 1.0000
12.500 1.3213 0.05287 0.04643 -0.0400 0.0140 1.0000
12.750 1.3231 0.05616 0.04997 -0.0389 0.0140 1.0000
13.000 1.3213 0.05985 0.05393 -0.0380 0.0141 1.0000
13.250 1.3159 0.06394 0.05831 -0.0374 0.0143 1.0000
13.500 1.3069 0.06845 0.06310 -0.0373 0.0144 1.0000
13.750 1.2954 0.07331 0.06823 -0.0377 0.0145 1.0000
14.000 1.2816 0.07860 0.07378 -0.0387 0.0145 1.0000
14.250 1.2667 0.08425 0.07967 -0.0404 0.0145 1.0000
14.500 1.2501 0.09058 0.08624 -0.0429 0.0146 1.0000
14.750 1.2258 0.09890 0.09488 -0.0469 0.0151 1.0000
15.000 1.2049 0.10711 0.10332 -0.0516 0.0153 1.0000
15.250 1.1801 0.11696 0.11342 -0.0578 0.0157 1.0000
15.500 1.1563 0.12743 0.12409 -0.0647 0.0160 1.0000
15.750 1.1330 0.13863 0.13546 -0.0723 0.0164 1.0000
16.000 1.1091 0.15097 0.14793 -0.0807 0.0167 1.0000
16.250 1.0812 0.16591 0.16296 -0.0904 0.0172 1.0000
16.500 1.0578 0.18079 0.17783 -0.0988 0.0181 1.0000
16.750 1.0495 0.18998 0.18698 -0.1036 0.0189 1.0000
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