HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il) Reynolds number: 100,000 Max Cl/Cd: 38.18 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1620-il-100000-n5.txt Download as CSV file: xf-hs1620-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-620 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8650 0.06537 0.05853 -0.0751 1.0000 0.0748
-12.500 -0.9302 0.06038 0.05328 -0.0689 0.9999 0.0746
-12.250 -0.9428 0.05671 0.04933 -0.0679 0.9958 0.0756
-12.000 -0.9469 0.05300 0.04522 -0.0675 0.9919 0.0772
-11.750 -0.9432 0.04995 0.04180 -0.0669 0.9874 0.0788
-11.500 -0.9196 0.04909 0.04097 -0.0675 0.9841 0.0801
-11.250 -0.8971 0.04775 0.03953 -0.0684 0.9812 0.0818
-11.000 -0.8827 0.04586 0.03739 -0.0679 0.9765 0.0838
-10.750 -0.8644 0.04397 0.03520 -0.0680 0.9724 0.0860
-10.500 -0.8357 0.04328 0.03455 -0.0692 0.9695 0.0877
-10.250 -0.8139 0.04222 0.03338 -0.0692 0.9651 0.0899
-10.000 -0.7930 0.04069 0.03153 -0.0692 0.9605 0.0927
-9.750 -0.7638 0.03994 0.03079 -0.0703 0.9572 0.0948
-9.500 -0.7354 0.03921 0.03000 -0.0712 0.9539 0.0974
-9.250 -0.7148 0.03814 0.02872 -0.0706 0.9480 0.1004
-9.000 -0.6858 0.03742 0.02796 -0.0716 0.9444 0.1030
-8.750 -0.6531 0.03681 0.02730 -0.0732 0.9418 0.1062
-8.500 -0.6329 0.03595 0.02622 -0.0722 0.9351 0.1098
-8.250 -0.6034 0.03542 0.02574 -0.0731 0.9308 0.1127
-8.000 -0.5704 0.03484 0.02508 -0.0746 0.9278 0.1167
-7.750 -0.5471 0.03421 0.02431 -0.0741 0.9220 0.1206
-7.500 -0.5200 0.03382 0.02397 -0.0743 0.9165 0.1239
-7.250 -0.4866 0.03322 0.02322 -0.0758 0.9133 0.1290
-7.000 -0.4590 0.03280 0.02281 -0.0761 0.9082 0.1329
-6.750 -0.4344 0.03245 0.02244 -0.0757 0.9014 0.1372
-6.500 -0.4016 0.03194 0.02181 -0.0769 0.8980 0.1427
-6.250 -0.3660 0.03155 0.02145 -0.0787 0.8955 0.1477
-6.000 -0.3490 0.03131 0.02110 -0.0768 0.8858 0.1527
-5.750 -0.3156 0.03092 0.02074 -0.0780 0.8820 0.1578
-5.500 -0.2794 0.03048 0.02024 -0.0798 0.8796 0.1644
-5.250 -0.2626 0.03039 0.02011 -0.0779 0.8698 0.1691
-5.000 -0.2294 0.03005 0.01980 -0.0791 0.8659 0.1750
-4.750 -0.1929 0.02958 0.01921 -0.0808 0.8633 0.1825
-4.500 -0.1749 0.02957 0.01927 -0.0791 0.8537 0.1870
-4.250 -0.1420 0.02923 0.01889 -0.0801 0.8497 0.1941
-4.000 -0.1061 0.02875 0.01838 -0.0817 0.8470 0.2009
-3.750 -0.0849 0.02873 0.01839 -0.0806 0.8385 0.2065
-3.500 -0.0538 0.02845 0.01803 -0.0812 0.8337 0.2141
-3.250 -0.0189 0.02795 0.01759 -0.0826 0.8307 0.2209
-3.000 0.0181 0.02743 0.01706 -0.0843 0.8285 0.2290
-2.750 0.0363 0.02758 0.01716 -0.0825 0.8183 0.2352
-2.500 0.0696 0.02708 0.01675 -0.0836 0.8145 0.2425
-2.250 0.1067 0.02654 0.01620 -0.0852 0.8118 0.2515
-2.000 0.1333 0.02637 0.01607 -0.0850 0.8052 0.2588
-1.750 0.1619 0.02607 0.01583 -0.0851 0.7984 0.2672
-1.500 0.2011 0.02538 0.01513 -0.0869 0.7943 0.2775
-1.250 0.2358 0.02473 0.01458 -0.0880 0.7877 0.2878
-1.000 0.2659 0.02433 0.01416 -0.0881 0.7778 0.2989
-0.750 0.3129 0.02326 0.01319 -0.0913 0.7725 0.3150
-0.500 0.3354 0.02315 0.01315 -0.0901 0.7602 0.3299
-0.250 0.3785 0.02238 0.01251 -0.0929 0.7540 0.3593
0.000 0.4063 0.02210 0.01245 -0.0929 0.7451 0.4050
0.500 0.4797 0.02044 0.01207 -0.0953 0.7313 0.7457
0.750 0.5036 0.02066 0.01259 -0.0934 0.7197 0.8539
1.000 0.5739 0.02046 0.01232 -0.1014 0.7116 0.9378
1.250 0.6143 0.02082 0.01264 -0.1040 0.6988 0.9764
1.500 0.6861 0.02086 0.01253 -0.1131 0.6874 0.9992
1.750 0.7038 0.02091 0.01249 -0.1111 0.6745 1.0000
2.000 0.7227 0.02093 0.01241 -0.1093 0.6620 1.0000
2.250 0.7488 0.02088 0.01221 -0.1089 0.6492 1.0000
2.500 0.7570 0.02106 0.01233 -0.1049 0.6350 1.0000
2.750 0.7738 0.02116 0.01233 -0.1026 0.6207 1.0000
3.000 0.7929 0.02125 0.01230 -0.1007 0.6054 1.0000
3.250 0.8049 0.02146 0.01243 -0.0975 0.5886 1.0000
3.500 0.8177 0.02171 0.01259 -0.0944 0.5705 1.0000
3.750 0.8323 0.02197 0.01275 -0.0918 0.5513 1.0000
4.000 0.8474 0.02226 0.01291 -0.0892 0.5307 1.0000
4.250 0.8628 0.02260 0.01309 -0.0868 0.5093 1.0000
4.500 0.8777 0.02300 0.01332 -0.0844 0.4879 1.0000
4.750 0.8924 0.02346 0.01362 -0.0819 0.4673 1.0000
5.000 0.9070 0.02398 0.01398 -0.0796 0.4481 1.0000
5.250 0.9218 0.02453 0.01439 -0.0774 0.4306 1.0000
5.500 0.9372 0.02510 0.01484 -0.0753 0.4151 1.0000
5.750 0.9532 0.02569 0.01529 -0.0734 0.4017 1.0000
6.000 0.9696 0.02629 0.01578 -0.0716 0.3895 1.0000
6.250 0.9870 0.02688 0.01629 -0.0700 0.3791 1.0000
6.500 1.0043 0.02750 0.01681 -0.0685 0.3693 1.0000
6.750 1.0228 0.02810 0.01734 -0.0672 0.3609 1.0000
7.000 1.0410 0.02871 0.01790 -0.0658 0.3529 1.0000
7.250 1.0602 0.02934 0.01840 -0.0647 0.3461 1.0000
7.500 1.0787 0.02996 0.01905 -0.0635 0.3390 1.0000
7.750 1.0972 0.03061 0.01966 -0.0623 0.3325 1.0000
8.000 1.1180 0.03124 0.02016 -0.0615 0.3269 1.0000
8.250 1.1362 0.03191 0.02088 -0.0604 0.3210 1.0000
8.500 1.1544 0.03260 0.02157 -0.0592 0.3152 1.0000
8.750 1.1739 0.03327 0.02218 -0.0583 0.3101 1.0000
9.000 1.1939 0.03396 0.02284 -0.0575 0.3053 1.0000
9.250 1.2106 0.03472 0.02367 -0.0562 0.3001 1.0000
9.500 1.2280 0.03548 0.02444 -0.0551 0.2952 1.0000
9.750 1.2474 0.03619 0.02510 -0.0543 0.2908 1.0000
10.000 1.2662 0.03696 0.02586 -0.0534 0.2866 1.0000
10.250 1.2805 0.03786 0.02687 -0.0520 0.2820 1.0000
10.500 1.2960 0.03873 0.02778 -0.0507 0.2775 1.0000
10.750 1.3127 0.03956 0.02860 -0.0496 0.2735 1.0000
11.000 1.3329 0.04031 0.02929 -0.0490 0.2698 1.0000
11.250 1.3433 0.04144 0.03058 -0.0473 0.2657 1.0000
11.500 1.3552 0.04251 0.03174 -0.0457 0.2615 1.0000
11.750 1.3687 0.04351 0.03277 -0.0444 0.2576 1.0000
12.000 1.3857 0.04437 0.03359 -0.0436 0.2542 1.0000
12.250 1.3972 0.04555 0.03487 -0.0421 0.2507 1.0000
12.500 1.4041 0.04697 0.03644 -0.0403 0.2466 1.0000
12.750 1.4133 0.04827 0.03782 -0.0388 0.2428 1.0000
13.000 1.4250 0.04942 0.03899 -0.0375 0.2395 1.0000
13.250 1.4421 0.05030 0.03981 -0.0369 0.2364 1.0000
13.500 1.4422 0.05228 0.04202 -0.0348 0.2327 1.0000
13.750 1.4460 0.05410 0.04398 -0.0331 0.2290 1.0000
14.000 1.4527 0.05571 0.04567 -0.0318 0.2256 1.0000
14.250 1.4629 0.05705 0.04703 -0.0308 0.2225 1.0000
14.500 1.4733 0.05845 0.04845 -0.0299 0.2196 1.0000
14.750 1.4681 0.06120 0.05144 -0.0281 0.2161 1.0000
15.000 1.4675 0.06364 0.05402 -0.0268 0.2127 1.0000
15.250 1.4713 0.06567 0.05614 -0.0259 0.2095 1.0000
15.500 1.4809 0.06716 0.05763 -0.0252 0.2067 1.0000
15.750 1.4815 0.06962 0.06019 -0.0243 0.2038 1.0000
16.000 1.4686 0.07358 0.06441 -0.0232 0.2004 1.0000
16.250 1.4625 0.07691 0.06789 -0.0225 0.1971 1.0000
16.500 1.4648 0.07933 0.07036 -0.0221 0.1941 1.0000
16.750 1.4772 0.08059 0.07159 -0.0219 0.1916 1.0000
17.000 1.4549 0.08609 0.07737 -0.0217 0.1884 1.0000
17.250 1.4292 0.09232 0.08385 -0.0220 0.1849 1.0000
17.500 1.4195 0.09661 0.08826 -0.0225 0.1817 1.0000
17.750 1.4293 0.09825 0.08990 -0.0226 0.1791 1.0000
18.000 1.4198 0.10264 0.09440 -0.0234 0.1763 1.0000
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