HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 100,000 Max Cl/Cd: 68.47 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1606-il-100000.txt Download as CSV file: xf-hs1606-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-606 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3567 0.10276 0.09798 -0.0301 1.0000 0.0669
-7.750 -0.3710 0.10245 0.09781 -0.0288 1.0000 0.0675
-7.500 -0.3826 0.10198 0.09746 -0.0293 1.0000 0.0678
-7.250 -0.3904 0.10113 0.09670 -0.0310 1.0000 0.0681
-7.000 -0.3928 0.09969 0.09530 -0.0339 1.0000 0.0683
-6.750 -0.3863 0.09264 0.08830 -0.0214 1.0000 0.0719
-6.500 -0.3891 0.09066 0.08637 -0.0199 1.0000 0.0740
-6.250 -0.3910 0.08861 0.08436 -0.0197 1.0000 0.0764
-6.000 -0.3892 0.08652 0.08232 -0.0224 1.0000 0.0796
-5.750 -0.3664 0.08438 0.08008 -0.0379 1.0000 0.0817
-5.500 -0.3725 0.07990 0.07571 -0.0301 1.0000 0.0830
-5.250 -0.3683 0.07686 0.07270 -0.0275 1.0000 0.0848
-5.000 -0.3578 0.07387 0.06971 -0.0281 1.0000 0.0878
-4.750 -0.3118 0.06942 0.06501 -0.0447 1.0000 0.0955
-4.500 -0.3075 0.06563 0.06130 -0.0414 1.0000 0.0967
-4.250 -0.2948 0.06253 0.05821 -0.0407 1.0000 0.0993
-3.750 -0.2299 0.05428 0.04963 -0.0525 1.0000 0.1108
-3.500 -0.1600 0.04243 0.03718 -0.0665 1.0000 0.0606
-3.250 -0.0727 0.02911 0.02228 -0.0818 1.0000 0.0470
-3.000 -0.0259 0.02500 0.01722 -0.0858 1.0000 0.0479
-2.750 0.0117 0.02297 0.01459 -0.0875 1.0000 0.0535
-2.500 0.0438 0.02199 0.01353 -0.0886 1.0000 0.0748
-2.250 0.0589 0.02373 0.01558 -0.0868 1.0000 0.1387
-2.000 0.0820 0.02411 0.01575 -0.0863 1.0000 0.1635
-1.750 0.1084 0.02382 0.01527 -0.0865 1.0000 0.1781
-1.500 0.1356 0.02345 0.01474 -0.0869 1.0000 0.1905
-1.250 0.1630 0.02316 0.01429 -0.0873 1.0000 0.2045
-1.000 0.1893 0.02298 0.01409 -0.0876 1.0000 0.2224
-0.750 0.2161 0.02280 0.01386 -0.0880 1.0000 0.2403
-0.500 0.2485 0.02268 0.01368 -0.0895 0.9983 0.2638
-0.250 0.2926 0.02255 0.01358 -0.0932 0.9945 0.2926
0.000 0.3315 0.02241 0.01355 -0.0960 0.9890 0.3220
0.250 0.3776 0.02235 0.01358 -0.1000 0.9842 0.3603
0.500 0.4232 0.02202 0.01363 -0.1040 0.9755 0.4316
0.750 0.4631 0.02093 0.01355 -0.1060 0.9647 1.0000
1.000 0.5120 0.02114 0.01356 -0.1101 0.9544 1.0000
1.250 0.5516 0.02136 0.01368 -0.1125 0.9448 1.0000
1.500 0.5866 0.02161 0.01388 -0.1141 0.9347 1.0000
1.750 0.6259 0.02177 0.01403 -0.1164 0.9255 1.0000
2.000 0.6704 0.02178 0.01409 -0.1195 0.9172 1.0000
2.250 0.7052 0.02185 0.01420 -0.1207 0.9059 1.0000
2.500 0.7413 0.02182 0.01424 -0.1220 0.8943 1.0000
2.750 0.7803 0.02164 0.01416 -0.1235 0.8829 1.0000
3.000 0.8244 0.02120 0.01391 -0.1257 0.8729 1.0000
3.250 0.8679 0.02055 0.01341 -0.1274 0.8626 1.0000
3.500 0.9031 0.02001 0.01303 -0.1274 0.8490 1.0000
3.750 0.9377 0.01938 0.01262 -0.1271 0.8347 1.0000
4.000 0.9646 0.01887 0.01228 -0.1253 0.8143 1.0000
4.250 0.9955 0.01760 0.01115 -0.1229 0.7873 1.0000
4.500 1.0210 0.01643 0.01004 -0.1195 0.7477 1.0000
4.750 1.0424 0.01581 0.00949 -0.1163 0.6930 1.0000
5.000 1.0647 0.01555 0.00906 -0.1134 0.6149 1.0000
5.250 1.0827 0.01616 0.00901 -0.1102 0.5059 1.0000
5.500 1.0939 0.01754 0.00969 -0.1067 0.3846 1.0000
5.750 1.0926 0.02060 0.01112 -0.1020 0.1604 1.0000
6.000 1.1032 0.02287 0.01284 -0.0991 0.1149 1.0000
6.250 1.1189 0.02444 0.01437 -0.0970 0.0986 1.0000
6.500 1.1344 0.02622 0.01608 -0.0949 0.0888 1.0000
6.750 1.1561 0.02775 0.01773 -0.0935 0.0830 1.0000
7.000 1.1807 0.02978 0.01968 -0.0927 0.0781 1.0000
7.250 1.2101 0.03232 0.02230 -0.0925 0.0744 1.0000
7.500 1.2348 0.03414 0.02436 -0.0917 0.0690 1.0000
7.750 1.2620 0.03682 0.02723 -0.0912 0.0663 1.0000
8.000 1.2883 0.04046 0.03112 -0.0907 0.0647 1.0000
8.250 1.3084 0.04530 0.03645 -0.0894 0.0633 1.0000
8.500 1.3188 0.04726 0.03913 -0.0861 0.0607 1.0000
8.750 1.3292 0.05157 0.04402 -0.0832 0.0606 1.0000
9.000 1.3340 0.05615 0.04917 -0.0799 0.0606 1.0000
9.250 1.3323 0.06020 0.05376 -0.0762 0.0590 1.0000
9.500 1.3265 0.06475 0.05879 -0.0725 0.0586 1.0000
9.750 1.3185 0.07037 0.06475 -0.0693 0.0608 1.0000
10.000 1.2166 0.06560 0.06044 -0.0533 0.0608 1.0000
10.250 1.1967 0.07006 0.06508 -0.0494 0.0616 1.0000
10.500 1.1413 0.07539 0.07093 -0.0441 0.0710 1.0000
10.750 1.1145 0.08083 0.07651 -0.0425 0.0731 1.0000
11.000 1.0925 0.08648 0.08226 -0.0417 0.0744 1.0000
11.250 1.0831 0.09292 0.08874 -0.0414 0.0755 1.0000
11.500 0.9961 0.10149 0.09758 -0.0473 0.0800 1.0000
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Polar data table (+)
Polar graphs
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