HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il) Reynolds number: 200,000 Max Cl/Cd: 51.25 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1620-il-200000-n5.txt Download as CSV file: xf-hs1620-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8294 0.09653 0.09126 -0.0720 1.0000 0.0520
-16.000 -0.9118 0.08071 0.07511 -0.0796 1.0000 0.0523
-15.750 -0.9567 0.07059 0.06473 -0.0850 0.9996 0.0526
-15.500 -0.9837 0.06253 0.05642 -0.0904 0.9982 0.0531
-15.250 -1.0023 0.05652 0.05017 -0.0940 0.9964 0.0536
-15.000 -1.0141 0.05184 0.04525 -0.0965 0.9943 0.0541
-14.750 -1.0215 0.04836 0.04157 -0.0976 0.9926 0.0547
-14.500 -1.0261 0.04601 0.03916 -0.0966 0.9900 0.0552
-14.250 -1.0287 0.04404 0.03710 -0.0951 0.9870 0.0558
-14.000 -1.0296 0.04237 0.03534 -0.0933 0.9842 0.0564
-13.750 -1.0265 0.04093 0.03379 -0.0915 0.9818 0.0572
-13.500 -1.0190 0.03959 0.03233 -0.0897 0.9789 0.0581
-13.250 -1.0099 0.03829 0.03088 -0.0880 0.9750 0.0591
-13.000 -0.9936 0.03704 0.02948 -0.0874 0.9723 0.0602
-12.750 -0.9720 0.03602 0.02844 -0.0876 0.9702 0.0612
-12.500 -0.9469 0.03507 0.02743 -0.0884 0.9686 0.0624
-12.250 -0.9347 0.03419 0.02647 -0.0863 0.9638 0.0636
-12.000 -0.9137 0.03328 0.02542 -0.0859 0.9607 0.0652
-11.750 -0.8892 0.03241 0.02450 -0.0862 0.9584 0.0665
-11.500 -0.8615 0.03163 0.02370 -0.0870 0.9566 0.0679
-11.250 -0.8319 0.03088 0.02286 -0.0881 0.9553 0.0697
-11.000 -0.8191 0.03026 0.02214 -0.0856 0.9495 0.0713
-10.750 -0.7939 0.02957 0.02143 -0.0857 0.9465 0.0729
-10.500 -0.7651 0.02895 0.02078 -0.0865 0.9443 0.0748
-10.250 -0.7341 0.02831 0.02006 -0.0876 0.9427 0.0771
-10.000 -0.7020 0.02767 0.01936 -0.0890 0.9414 0.0793
-9.750 -0.6889 0.02725 0.01895 -0.0863 0.9345 0.0810
-9.500 -0.6607 0.02674 0.01838 -0.0867 0.9316 0.0835
-9.250 -0.6294 0.02618 0.01776 -0.0878 0.9294 0.0862
-9.000 -0.5963 0.02564 0.01722 -0.0892 0.9278 0.0888
-8.500 -0.5496 0.02481 0.01632 -0.0878 0.9178 0.0943
-8.250 -0.5187 0.02436 0.01587 -0.0886 0.9152 0.0975
-7.750 -0.4502 0.02341 0.01489 -0.0916 0.9118 0.1050
-7.500 -0.4352 0.02319 0.01464 -0.0890 0.9027 0.1082
-7.250 -0.4036 0.02276 0.01420 -0.0899 0.8996 0.1122
-7.000 -0.3696 0.02234 0.01378 -0.0913 0.8975 0.1168
-6.750 -0.3344 0.02191 0.01333 -0.0929 0.8959 0.1215
-6.500 -0.3193 0.02177 0.01322 -0.0903 0.8861 0.1252
-6.250 -0.2864 0.02138 0.01278 -0.0913 0.8829 0.1305
-6.000 -0.2518 0.02095 0.01239 -0.0927 0.8807 0.1355
-5.750 -0.2313 0.02080 0.01221 -0.0912 0.8722 0.1404
-5.500 -0.2015 0.02047 0.01192 -0.0916 0.8677 0.1454
-5.250 -0.1678 0.02009 0.01151 -0.0927 0.8649 0.1515
-5.000 -0.1403 0.01982 0.01126 -0.0926 0.8589 0.1566
-4.750 -0.1140 0.01962 0.01107 -0.0922 0.8517 0.1620
-4.500 -0.0794 0.01925 0.01067 -0.0935 0.8483 0.1683
-4.250 -0.0419 0.01883 0.01028 -0.0954 0.8459 0.1744
-4.000 -0.0195 0.01877 0.01019 -0.0942 0.8360 0.1799
-3.750 0.0165 0.01839 0.00983 -0.0958 0.8320 0.1857
-3.500 0.0566 0.01798 0.00942 -0.0983 0.8290 0.1925
-3.250 0.0859 0.01782 0.00921 -0.0985 0.8207 0.1982
-3.000 0.1257 0.01737 0.00881 -0.1009 0.8146 0.2046
-2.750 0.1715 0.01693 0.00832 -0.1046 0.8080 0.2122
-2.500 0.2098 0.01662 0.00798 -0.1067 0.7974 0.2186
-2.250 0.2594 0.01624 0.00758 -0.1114 0.7889 0.2265
-2.000 0.2963 0.01607 0.00734 -0.1132 0.7775 0.2335
-1.750 0.3341 0.01583 0.00709 -0.1154 0.7662 0.2407
-1.500 0.3708 0.01567 0.00688 -0.1172 0.7537 0.2488
-1.250 0.4003 0.01564 0.00678 -0.1175 0.7408 0.2558
-1.000 0.4333 0.01551 0.00665 -0.1186 0.7307 0.2643
-0.750 0.4593 0.01549 0.00663 -0.1182 0.7198 0.2730
-0.500 0.4901 0.01543 0.00655 -0.1189 0.7101 0.2833
-0.250 0.5148 0.01540 0.00657 -0.1182 0.6998 0.2959
0.000 0.5440 0.01534 0.00653 -0.1185 0.6899 0.3139
0.250 0.5670 0.01527 0.00658 -0.1176 0.6789 0.3421
0.500 0.5931 0.01508 0.00659 -0.1173 0.6685 0.4087
0.750 0.6127 0.01470 0.00673 -0.1157 0.6575 0.5427
1.000 0.6341 0.01444 0.00689 -0.1141 0.6471 0.6841
1.250 0.6532 0.01439 0.00708 -0.1119 0.6349 0.7590
1.500 0.6742 0.01445 0.00733 -0.1098 0.6225 0.8377
1.750 0.7022 0.01468 0.00759 -0.1093 0.6080 0.9077
2.000 0.7347 0.01498 0.00786 -0.1101 0.5919 0.9499
2.250 0.7702 0.01536 0.00815 -0.1117 0.5733 0.9788
2.500 0.8104 0.01582 0.00847 -0.1145 0.5498 0.9961
2.750 0.8251 0.01610 0.00861 -0.1119 0.5279 1.0000
3.000 0.8286 0.01632 0.00869 -0.1068 0.5068 1.0000
3.250 0.8345 0.01662 0.00884 -0.1023 0.4847 1.0000
3.500 0.8422 0.01700 0.00906 -0.0982 0.4620 1.0000
3.750 0.8515 0.01743 0.00934 -0.0946 0.4397 1.0000
4.000 0.8624 0.01790 0.00966 -0.0913 0.4190 1.0000
4.250 0.8745 0.01839 0.01002 -0.0884 0.4007 1.0000
4.500 0.8875 0.01892 0.01042 -0.0857 0.3849 1.0000
4.750 0.9026 0.01941 0.01081 -0.0834 0.3706 1.0000
5.000 0.9182 0.01991 0.01122 -0.0813 0.3590 1.0000
5.250 0.9338 0.02045 0.01167 -0.0793 0.3486 1.0000
5.500 0.9513 0.02094 0.01210 -0.0776 0.3402 1.0000
5.750 0.9685 0.02145 0.01256 -0.0759 0.3322 1.0000
6.000 0.9853 0.02201 0.01304 -0.0742 0.3253 1.0000
6.250 1.0045 0.02248 0.01350 -0.0729 0.3186 1.0000
6.500 1.0219 0.02304 0.01401 -0.0714 0.3124 1.0000
6.750 1.0388 0.02365 0.01454 -0.0698 0.3071 1.0000
7.000 1.0588 0.02411 0.01503 -0.0687 0.3019 1.0000
7.250 1.0773 0.02465 0.01555 -0.0674 0.2966 1.0000
7.500 1.0944 0.02528 0.01613 -0.0660 0.2918 1.0000
7.750 1.1121 0.02589 0.01671 -0.0646 0.2875 1.0000
8.000 1.1318 0.02640 0.01726 -0.0637 0.2830 1.0000
8.250 1.1500 0.02700 0.01786 -0.0625 0.2785 1.0000
8.500 1.1669 0.02767 0.01850 -0.0611 0.2743 1.0000
8.750 1.1832 0.02840 0.01918 -0.0597 0.2706 1.0000
9.000 1.2024 0.02896 0.01980 -0.0588 0.2668 1.0000
9.250 1.2202 0.02960 0.02048 -0.0576 0.2627 1.0000
9.500 1.2368 0.03031 0.02120 -0.0564 0.2588 1.0000
9.750 1.2526 0.03109 0.02196 -0.0551 0.2553 1.0000
10.000 1.2688 0.03187 0.02273 -0.0539 0.2519 1.0000
10.250 1.2863 0.03258 0.02351 -0.0528 0.2482 1.0000
10.500 1.3027 0.03336 0.02433 -0.0517 0.2445 1.0000
10.750 1.3178 0.03422 0.02520 -0.0505 0.2410 1.0000
11.000 1.3317 0.03516 0.02613 -0.0492 0.2377 1.0000
11.250 1.3471 0.03605 0.02705 -0.0481 0.2344 1.0000
11.500 1.3627 0.03693 0.02802 -0.0470 0.2309 1.0000
11.750 1.3769 0.03791 0.02904 -0.0459 0.2273 1.0000
12.000 1.3900 0.03898 0.03013 -0.0447 0.2239 1.0000
12.250 1.4021 0.04014 0.03127 -0.0434 0.2209 1.0000
12.500 1.4165 0.04117 0.03238 -0.0425 0.2177 1.0000
12.750 1.4299 0.04229 0.03359 -0.0415 0.2143 1.0000
13.000 1.4420 0.04351 0.03486 -0.0404 0.2110 1.0000
13.250 1.4529 0.04483 0.03619 -0.0393 0.2080 1.0000
13.500 1.4634 0.04620 0.03755 -0.0382 0.2052 1.0000
13.750 1.4758 0.04748 0.03896 -0.0373 0.2019 1.0000
14.000 1.4867 0.04890 0.04047 -0.0364 0.1986 1.0000
14.250 1.4963 0.05043 0.04204 -0.0355 0.1955 1.0000
14.500 1.5046 0.05209 0.04371 -0.0345 0.1926 1.0000
14.750 1.5137 0.05371 0.04538 -0.0337 0.1898 1.0000
15.000 1.5229 0.05537 0.04716 -0.0329 0.1865 1.0000
15.250 1.5308 0.05716 0.04902 -0.0322 0.1833 1.0000
15.500 1.5370 0.05912 0.05103 -0.0314 0.1804 1.0000
15.750 1.5427 0.06113 0.05303 -0.0306 0.1777 1.0000
16.000 1.5498 0.06311 0.05514 -0.0301 0.1748 1.0000
16.250 1.5558 0.06521 0.05734 -0.0295 0.1716 1.0000
16.500 1.5600 0.06751 0.05971 -0.0290 0.1687 1.0000
16.750 1.5633 0.06989 0.06212 -0.0285 0.1661 1.0000
17.000 1.5670 0.07228 0.06457 -0.0281 0.1635 1.0000
17.250 1.5702 0.07479 0.06722 -0.0278 0.1605 1.0000
17.500 1.5722 0.07747 0.06999 -0.0276 0.1576 1.0000
17.750 1.5731 0.08028 0.07285 -0.0275 0.1550 1.0000
18.000 1.5745 0.08299 0.07557 -0.0274 0.1527 1.0000
18.250 1.5744 0.08607 0.07881 -0.0275 0.1500 1.0000
18.500 1.5734 0.08924 0.08211 -0.0277 0.1471 1.0000
18.750 1.5718 0.09250 0.08544 -0.0280 0.1445 1.0000
19.000 1.5703 0.09573 0.08870 -0.0284 0.1422 1.0000
19.250 1.5684 0.09910 0.09216 -0.0289 0.1398 1.0000
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Polar data table (+)
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