HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il) Reynolds number: 200,000 Max Cl/Cd: 59.4 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1620-il-200000.txt Download as CSV file: xf-hs1620-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9131 0.07006 0.06491 -0.0855 1.0000 0.0714
-14.250 -0.9724 0.06324 0.05784 -0.0846 1.0000 0.0712
-14.000 -1.0223 0.05899 0.05337 -0.0801 1.0000 0.0712
-13.750 -1.0684 0.05630 0.05049 -0.0726 1.0000 0.0712
-13.500 -1.1045 0.05324 0.04713 -0.0661 1.0000 0.0715
-13.250 -1.1271 0.05027 0.04381 -0.0610 1.0000 0.0720
-13.000 -1.1150 0.04916 0.04281 -0.0593 1.0000 0.0728
-12.750 -1.1059 0.04827 0.04195 -0.0571 1.0000 0.0736
-12.500 -1.0993 0.04719 0.04082 -0.0547 1.0000 0.0746
-12.250 -1.0941 0.04589 0.03941 -0.0522 1.0000 0.0757
-12.000 -1.0919 0.04416 0.03743 -0.0494 1.0000 0.0769
-11.750 -1.0836 0.04198 0.03474 -0.0480 0.9985 0.0785
-11.500 -1.0464 0.04118 0.03411 -0.0507 0.9950 0.0800
-11.250 -1.0115 0.04045 0.03334 -0.0531 0.9916 0.0818
-11.000 -0.9844 0.03920 0.03188 -0.0541 0.9866 0.0838
-10.750 -0.9553 0.03783 0.03020 -0.0556 0.9830 0.0861
-10.500 -0.9171 0.03748 0.02999 -0.0583 0.9808 0.0881
-10.250 -0.8914 0.03656 0.02897 -0.0586 0.9739 0.0902
-10.000 -0.8588 0.03554 0.02760 -0.0603 0.9704 0.0930
-9.750 -0.8208 0.03494 0.02713 -0.0630 0.9684 0.0953
-9.500 -0.7973 0.03431 0.02650 -0.0626 0.9610 0.0977
-9.250 -0.7636 0.03358 0.02549 -0.0643 0.9577 0.1009
-9.000 -0.7256 0.03296 0.02497 -0.0668 0.9558 0.1037
-8.750 -0.7014 0.03247 0.02448 -0.0664 0.9481 0.1065
-8.500 -0.6663 0.03184 0.02358 -0.0682 0.9445 0.1104
-8.250 -0.6275 0.03134 0.02324 -0.0708 0.9424 0.1137
-8.000 -0.6027 0.03094 0.02280 -0.0705 0.9354 0.1172
-7.750 -0.5697 0.03035 0.02211 -0.0718 0.9313 0.1213
-7.500 -0.5314 0.03000 0.02184 -0.0741 0.9288 0.1255
-7.250 -0.4912 0.02949 0.02116 -0.0767 0.9270 0.1308
-7.000 -0.4708 0.02917 0.02096 -0.0755 0.9178 0.1342
-6.750 -0.4336 0.02880 0.02053 -0.0775 0.9147 0.1398
-6.500 -0.3947 0.02831 0.02007 -0.0799 0.9127 0.1450
-6.250 -0.3705 0.02815 0.01992 -0.0793 0.9052 0.1498
-6.000 -0.3369 0.02769 0.01939 -0.0805 0.9007 0.1556
-5.750 -0.2980 0.02733 0.01911 -0.0828 0.8982 0.1615
-5.500 -0.2575 0.02684 0.01853 -0.0853 0.8966 0.1686
-5.250 -0.2388 0.02677 0.01855 -0.0837 0.8870 0.1731
-5.000 -0.2016 0.02643 0.01814 -0.0855 0.8837 0.1804
-4.750 -0.1622 0.02586 0.01764 -0.0878 0.8817 0.1870
-4.500 -0.1215 0.02546 0.01722 -0.0903 0.8801 0.1948
-4.250 -0.1042 0.02540 0.01713 -0.0883 0.8700 0.2002
-4.000 -0.0666 0.02492 0.01674 -0.0903 0.8671 0.2073
-3.750 -0.0261 0.02447 0.01619 -0.0926 0.8652 0.2153
-3.500 0.0151 0.02368 0.01551 -0.0952 0.8639 0.2231
-3.250 0.0333 0.02373 0.01556 -0.0933 0.8540 0.2292
-3.000 0.0726 0.02302 0.01481 -0.0954 0.8511 0.2372
-2.750 0.1156 0.02207 0.01395 -0.0981 0.8493 0.2459
-2.500 0.1622 0.02119 0.01300 -0.1014 0.8477 0.2550
-2.250 0.2103 0.02006 0.01199 -0.1052 0.8464 0.2651
-2.000 0.2286 0.01991 0.01185 -0.1031 0.8354 0.2723
-1.750 0.2753 0.01896 0.01094 -0.1066 0.8323 0.2828
-1.500 0.3296 0.01804 0.01005 -0.1118 0.8297 0.2957
-1.250 0.3568 0.01766 0.00975 -0.1115 0.8203 0.3062
-1.000 0.4020 0.01709 0.00921 -0.1150 0.8149 0.3210
-0.750 0.4528 0.01635 0.00859 -0.1198 0.8106 0.3417
-0.500 0.4768 0.01614 0.00851 -0.1190 0.7999 0.3642
-0.250 0.5190 0.01540 0.00811 -0.1221 0.7933 0.4343
0.000 0.5381 0.01450 0.00827 -0.1200 0.7836 0.6992
0.250 0.5687 0.01419 0.00841 -0.1191 0.7749 0.8573
0.500 0.6079 0.01440 0.00865 -0.1205 0.7646 0.9296
0.750 0.6590 0.01459 0.00872 -0.1249 0.7546 0.9629
1.000 0.7126 0.01493 0.00898 -0.1301 0.7427 0.9795
1.250 0.7751 0.01511 0.00899 -0.1373 0.7312 0.9894
1.500 0.8262 0.01542 0.00925 -0.1423 0.7170 0.9981
1.750 0.8530 0.01546 0.00919 -0.1423 0.7045 1.0000
2.000 0.8729 0.01543 0.00903 -0.1407 0.6917 1.0000
2.250 0.8842 0.01548 0.00903 -0.1373 0.6777 1.0000
2.500 0.9010 0.01552 0.00897 -0.1350 0.6640 1.0000
2.750 0.9178 0.01558 0.00890 -0.1326 0.6493 1.0000
3.000 0.9275 0.01568 0.00896 -0.1287 0.6329 1.0000
3.250 0.9382 0.01580 0.00899 -0.1250 0.6156 1.0000
3.500 0.9474 0.01595 0.00904 -0.1210 0.5966 1.0000
3.750 0.9540 0.01614 0.00912 -0.1164 0.5755 1.0000
4.000 0.9559 0.01639 0.00924 -0.1108 0.5522 1.0000
4.250 0.9581 0.01674 0.00942 -0.1054 0.5264 1.0000
4.500 0.9621 0.01721 0.00971 -0.1004 0.4982 1.0000
4.750 0.9678 0.01777 0.01007 -0.0960 0.4713 1.0000
5.000 0.9767 0.01839 0.01048 -0.0924 0.4483 1.0000
5.250 0.9885 0.01900 0.01093 -0.0894 0.4291 1.0000
5.500 1.0028 0.01958 0.01139 -0.0870 0.4129 1.0000
5.750 1.0186 0.02016 0.01184 -0.0849 0.3995 1.0000
6.000 1.0350 0.02076 0.01231 -0.0830 0.3879 1.0000
6.250 1.0536 0.02128 0.01278 -0.0815 0.3778 1.0000
6.500 1.0723 0.02186 0.01324 -0.0801 0.3688 1.0000
6.750 1.0924 0.02239 0.01372 -0.0789 0.3607 1.0000
7.000 1.1115 0.02292 0.01421 -0.0776 0.3530 1.0000
7.250 1.1354 0.02351 0.01464 -0.0773 0.3459 1.0000
7.500 1.1534 0.02402 0.01521 -0.0758 0.3396 1.0000
7.750 1.1729 0.02456 0.01573 -0.0746 0.3334 1.0000
8.000 1.1995 0.02514 0.01615 -0.0748 0.3272 1.0000
8.250 1.2173 0.02569 0.01677 -0.0734 0.3221 1.0000
8.500 1.2359 0.02626 0.01736 -0.0721 0.3166 1.0000
8.750 1.2571 0.02683 0.01788 -0.0714 0.3114 1.0000
9.000 1.2842 0.02742 0.01838 -0.0717 0.3063 1.0000
9.250 1.2992 0.02804 0.01910 -0.0698 0.3017 1.0000
9.500 1.3169 0.02866 0.01974 -0.0685 0.2970 1.0000
9.750 1.3374 0.02926 0.02030 -0.0677 0.2925 1.0000
10.000 1.3657 0.02988 0.02084 -0.0683 0.2877 1.0000
10.250 1.3776 0.03061 0.02169 -0.0661 0.2838 1.0000
10.500 1.3928 0.03131 0.02244 -0.0645 0.2794 1.0000
10.750 1.4104 0.03197 0.02309 -0.0633 0.2753 1.0000
11.000 1.4433 0.03254 0.02351 -0.0647 0.2705 1.0000
11.250 1.4494 0.03343 0.02457 -0.0617 0.2672 1.0000
11.500 1.4607 0.03427 0.02551 -0.0597 0.2632 1.0000
11.750 1.4752 0.03504 0.02631 -0.0582 0.2593 1.0000
12.000 1.4939 0.03574 0.02697 -0.0574 0.2557 1.0000
12.250 1.5164 0.03651 0.02771 -0.0572 0.2518 1.0000
12.500 1.5223 0.03759 0.02895 -0.0545 0.2484 1.0000
12.750 1.5319 0.03858 0.03003 -0.0526 0.2446 1.0000
13.000 1.5454 0.03944 0.03090 -0.0511 0.2411 1.0000
13.250 1.5667 0.04012 0.03151 -0.0508 0.2376 1.0000
13.500 1.5772 0.04128 0.03277 -0.0492 0.2342 1.0000
13.750 1.5807 0.04263 0.03427 -0.0467 0.2308 1.0000
14.000 1.5884 0.04382 0.03554 -0.0449 0.2273 1.0000
14.250 1.6007 0.04481 0.03653 -0.0436 0.2240 1.0000
14.500 1.6274 0.04534 0.03692 -0.0440 0.2203 1.0000
14.750 1.6220 0.04728 0.03910 -0.0410 0.2175 1.0000
15.000 1.6234 0.04901 0.04097 -0.0389 0.2142 1.0000
15.250 1.6305 0.05043 0.04245 -0.0374 0.2109 1.0000
15.500 1.6425 0.05153 0.04353 -0.0365 0.2079 1.0000
15.750 1.6595 0.05250 0.04447 -0.0360 0.2046 1.0000
16.000 1.6524 0.05503 0.04722 -0.0337 0.2017 1.0000
16.250 1.6528 0.05712 0.04945 -0.0321 0.1985 1.0000
16.500 1.6593 0.05875 0.05112 -0.0311 0.1954 1.0000
16.750 1.6734 0.05980 0.05210 -0.0306 0.1925 1.0000
17.000 1.6775 0.06180 0.05420 -0.0295 0.1895 1.0000
17.250 1.6687 0.06493 0.05754 -0.0280 0.1866 1.0000
17.500 1.6679 0.06741 0.06013 -0.0271 0.1836 1.0000
17.750 1.6751 0.06912 0.06185 -0.0265 0.1807 1.0000
18.000 1.6980 0.06937 0.06195 -0.0264 0.1777 1.0000
18.250 1.6802 0.07368 0.06654 -0.0253 0.1752 1.0000
18.500 1.6691 0.07750 0.07055 -0.0246 0.1723 1.0000
18.750 1.6684 0.08021 0.07335 -0.0243 0.1695 1.0000
19.000 1.6788 0.08165 0.07475 -0.0242 0.1668 1.0000
19.250 1.6897 0.08307 0.07615 -0.0240 0.1641 1.0000
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Polar data table (+)
Polar graphs
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