HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 50,000 Max Cl/Cd: 43 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1708-il-50000-n5.txt Download as CSV file: xf-hs1708-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-708 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3608 0.11057 0.10407 -0.0269 1.0000 0.0915
-7.750 -0.3746 0.10955 0.10315 -0.0245 1.0000 0.0922
-7.500 -0.3859 0.10815 0.10184 -0.0227 1.0000 0.0925
-6.500 -0.4012 0.09268 0.08650 -0.0299 1.0000 0.0549
-6.250 -0.3969 0.08940 0.08324 -0.0301 1.0000 0.0545
-5.750 -0.3646 0.08247 0.07629 -0.0346 0.9943 0.0589
-5.500 -0.3408 0.07771 0.07146 -0.0408 0.9904 0.0598
-5.250 -0.3108 0.07202 0.06564 -0.0488 0.9867 0.0596
-5.000 -0.2780 0.06657 0.06002 -0.0566 0.9834 0.0610
-4.750 -0.2369 0.06004 0.05319 -0.0668 0.9801 0.0654
-4.500 -0.1949 0.05393 0.04670 -0.0755 0.9774 0.0694
-4.250 -0.1594 0.05079 0.04330 -0.0801 0.9747 0.0760
-4.000 -0.1086 0.04466 0.03649 -0.0892 0.9732 0.0828
-3.750 -0.0727 0.04214 0.03361 -0.0927 0.9706 0.0889
-3.500 -0.0313 0.03874 0.02956 -0.0975 0.9684 0.0969
-3.250 0.0045 0.03699 0.02737 -0.1002 0.9656 0.1044
-3.000 0.0421 0.03536 0.02530 -0.1030 0.9630 0.1127
-2.750 0.0818 0.03384 0.02321 -0.1061 0.9606 0.1231
-2.500 0.1159 0.03319 0.02241 -0.1078 0.9575 0.1313
-2.250 0.1460 0.03266 0.02163 -0.1088 0.9529 0.1427
-2.000 0.1817 0.03190 0.02051 -0.1107 0.9491 0.1533
-1.750 0.2180 0.03158 0.02002 -0.1127 0.9456 0.1682
-1.500 0.2484 0.03129 0.01955 -0.1135 0.9407 0.1821
-1.250 0.2800 0.03109 0.01918 -0.1145 0.9357 0.1973
-1.000 0.3160 0.03093 0.01893 -0.1163 0.9317 0.2162
-0.750 0.3457 0.03082 0.01873 -0.1170 0.9262 0.2343
-0.500 0.3772 0.03073 0.01856 -0.1179 0.9207 0.2554
-0.250 0.4141 0.03058 0.01842 -0.1199 0.9166 0.2799
0.000 0.4403 0.03056 0.01847 -0.1200 0.9097 0.3025
0.250 0.4748 0.03043 0.01844 -0.1216 0.9044 0.3334
0.500 0.5083 0.03024 0.01852 -0.1230 0.8987 0.3793
0.750 0.5278 0.02887 0.01859 -0.1212 0.8906 1.0000
1.000 0.5602 0.02916 0.01861 -0.1220 0.8818 1.0000
1.250 0.6006 0.02918 0.01842 -0.1239 0.8729 1.0000
1.500 0.6307 0.02928 0.01839 -0.1240 0.8605 1.0000
1.750 0.6617 0.02936 0.01839 -0.1242 0.8488 1.0000
2.000 0.6960 0.02937 0.01834 -0.1250 0.8392 1.0000
2.250 0.7308 0.02936 0.01831 -0.1258 0.8301 1.0000
2.500 0.7572 0.02955 0.01852 -0.1253 0.8185 1.0000
2.750 0.7860 0.02965 0.01864 -0.1251 0.8074 1.0000
3.000 0.8208 0.02949 0.01851 -0.1257 0.7980 1.0000
3.250 0.8505 0.02942 0.01854 -0.1254 0.7864 1.0000
3.500 0.8764 0.02944 0.01864 -0.1245 0.7728 1.0000
3.750 0.9027 0.02940 0.01869 -0.1236 0.7587 1.0000
4.000 0.9295 0.02927 0.01867 -0.1227 0.7440 1.0000
4.500 0.9829 0.02883 0.01850 -0.1205 0.7119 1.0000
4.750 1.0005 0.02899 0.01880 -0.1183 0.6898 1.0000
5.000 1.0273 0.02868 0.01865 -0.1170 0.6704 1.0000
5.250 1.0488 0.02865 0.01876 -0.1152 0.6461 1.0000
5.500 1.0773 0.02828 0.01850 -0.1141 0.6221 1.0000
5.750 1.1097 0.02776 0.01808 -0.1134 0.5963 1.0000
6.000 1.1420 0.02741 0.01774 -0.1128 0.5679 1.0000
6.250 1.1713 0.02743 0.01771 -0.1120 0.5378 1.0000
6.500 1.1959 0.02781 0.01807 -0.1107 0.5062 1.0000
6.750 1.2142 0.02843 0.01857 -0.1085 0.4688 1.0000
7.000 1.2268 0.02927 0.01924 -0.1056 0.4287 1.0000
7.250 1.2371 0.03025 0.02001 -0.1026 0.3907 1.0000
7.500 1.2474 0.03131 0.02100 -0.0998 0.3582 1.0000
7.750 1.2565 0.03242 0.02210 -0.0970 0.3286 1.0000
8.000 1.2636 0.03362 0.02330 -0.0939 0.2985 1.0000
8.250 1.2697 0.03495 0.02465 -0.0910 0.2659 1.0000
8.500 1.2736 0.03651 0.02613 -0.0880 0.2296 1.0000
8.750 1.2761 0.03837 0.02782 -0.0852 0.1904 1.0000
9.000 1.2784 0.04049 0.02972 -0.0826 0.1590 1.0000
9.250 1.2830 0.04266 0.03179 -0.0802 0.1374 1.0000
9.500 1.2883 0.04486 0.03395 -0.0780 0.1227 1.0000
9.750 1.2947 0.04699 0.03609 -0.0760 0.1110 1.0000
10.000 1.3016 0.04912 0.03826 -0.0741 0.1020 1.0000
10.250 1.3097 0.05121 0.04040 -0.0723 0.0955 1.0000
10.500 1.3226 0.05318 0.04252 -0.0705 0.0903 1.0000
10.750 1.3351 0.05517 0.04467 -0.0689 0.0852 1.0000
11.000 1.3468 0.05728 0.04676 -0.0674 0.0806 1.0000
11.250 1.3571 0.05956 0.04940 -0.0659 0.0758 1.0000
11.500 1.3692 0.06184 0.05190 -0.0645 0.0722 1.0000
11.750 1.3892 0.06411 0.05417 -0.0635 0.0693 1.0000
12.000 1.3965 0.06717 0.05763 -0.0620 0.0671 1.0000
12.250 1.3957 0.07054 0.06140 -0.0603 0.0648 1.0000
12.500 1.3917 0.07405 0.06523 -0.0589 0.0626 1.0000
12.750 1.3873 0.07759 0.06902 -0.0577 0.0606 1.0000
13.000 1.3837 0.08120 0.07283 -0.0568 0.0590 1.0000
13.250 1.3803 0.08515 0.07697 -0.0560 0.0579 1.0000
13.750 1.3600 0.09480 0.08707 -0.0556 0.0566 1.0000
14.000 1.3389 0.10078 0.09337 -0.0566 0.0565 1.0000
14.250 1.3162 0.10742 0.10029 -0.0587 0.0564 1.0000
14.500 1.2924 0.11482 0.10793 -0.0620 0.0565 1.0000
14.750 1.2678 0.12316 0.11648 -0.0665 0.0566 1.0000
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Polar data table (+)
Polar graphs
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