HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 100,000 Max Cl/Cd: 66.26 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1606-il-100000-n5.txt Download as CSV file: xf-hs1606-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3660 0.09450 0.08981 -0.0272 1.0000 0.0292
-7.250 -0.3736 0.09266 0.08806 -0.0251 1.0000 0.0284
-7.000 -0.3810 0.09076 0.08625 -0.0236 1.0000 0.0278
-6.000 -0.3039 0.07018 0.06558 -0.0516 0.9840 0.0219
-5.750 -0.2811 0.06544 0.06080 -0.0566 0.9791 0.0212
-5.500 -0.2507 0.06007 0.05533 -0.0639 0.9745 0.0207
-5.250 -0.2127 0.05390 0.04902 -0.0729 0.9713 0.0202
-5.000 -0.1719 0.04713 0.04203 -0.0821 0.9677 0.0198
-4.750 -0.1252 0.03837 0.03283 -0.0923 0.9644 0.0192
-4.500 -0.0717 0.02811 0.02140 -0.1026 0.9633 0.0188
-4.250 -0.0322 0.02422 0.01666 -0.1062 0.9616 0.0192
-4.000 0.0042 0.02205 0.01393 -0.1084 0.9598 0.0201
-3.750 0.0405 0.02059 0.01202 -0.1102 0.9581 0.0215
-3.500 0.0772 0.01937 0.01052 -0.1123 0.9566 0.0254
-3.250 0.1077 0.01851 0.00959 -0.1130 0.9527 0.0410
-3.000 0.1384 0.01849 0.00973 -0.1139 0.9489 0.0995
-2.750 0.1714 0.01859 0.00961 -0.1151 0.9459 0.1228
-2.500 0.2062 0.01827 0.00912 -0.1166 0.9438 0.1347
-2.250 0.2359 0.01810 0.00887 -0.1171 0.9399 0.1474
-2.000 0.2657 0.01798 0.00866 -0.1176 0.9358 0.1624
-1.750 0.2987 0.01779 0.00839 -0.1188 0.9329 0.1772
-1.500 0.3331 0.01763 0.00820 -0.1202 0.9304 0.1942
-1.250 0.3612 0.01754 0.00809 -0.1204 0.9250 0.2092
-1.000 0.3934 0.01737 0.00791 -0.1213 0.9203 0.2260
-0.750 0.4288 0.01713 0.00767 -0.1228 0.9170 0.2445
-0.500 0.4557 0.01707 0.00761 -0.1226 0.9105 0.2607
-0.250 0.4885 0.01688 0.00747 -0.1237 0.9064 0.2799
0.000 0.5223 0.01667 0.00734 -0.1248 0.9027 0.3039
0.250 0.5502 0.01649 0.00733 -0.1248 0.8949 0.3408
0.750 0.6079 0.01475 0.00688 -0.1239 0.8781 1.0000
1.000 0.6363 0.01472 0.00677 -0.1235 0.8678 1.0000
1.250 0.6675 0.01467 0.00667 -0.1238 0.8607 1.0000
1.500 0.6944 0.01476 0.00677 -0.1234 0.8520 1.0000
1.750 0.7225 0.01481 0.00683 -0.1231 0.8440 1.0000
2.000 0.7516 0.01481 0.00684 -0.1230 0.8359 1.0000
2.250 0.7777 0.01489 0.00697 -0.1224 0.8255 1.0000
2.500 0.8050 0.01492 0.00704 -0.1219 0.8152 1.0000
2.750 0.8327 0.01491 0.00715 -0.1214 0.8041 1.0000
3.000 0.8596 0.01491 0.00722 -0.1207 0.7915 1.0000
3.250 0.8852 0.01494 0.00735 -0.1198 0.7763 1.0000
3.500 0.9101 0.01498 0.00750 -0.1188 0.7584 1.0000
3.750 0.9360 0.01498 0.00764 -0.1178 0.7387 1.0000
4.000 0.9604 0.01496 0.00773 -0.1165 0.7101 1.0000
4.250 0.9831 0.01488 0.00760 -0.1145 0.6508 1.0000
4.500 1.0045 0.01516 0.00721 -0.1118 0.5382 1.0000
4.750 1.0206 0.01619 0.00766 -0.1093 0.4363 1.0000
5.000 1.0376 0.01723 0.00827 -0.1074 0.3603 1.0000
5.250 1.0552 0.01827 0.00898 -0.1057 0.2905 1.0000
5.500 1.0701 0.01972 0.00980 -0.1039 0.1790 1.0000
5.750 1.0838 0.02156 0.01099 -0.1019 0.0910 1.0000
6.000 1.1018 0.02286 0.01220 -0.1004 0.0719 1.0000
6.250 1.1193 0.02414 0.01354 -0.0987 0.0628 1.0000
6.500 1.1381 0.02518 0.01473 -0.0972 0.0554 1.0000
6.750 1.1531 0.02661 0.01621 -0.0953 0.0506 1.0000
7.000 1.1704 0.02781 0.01761 -0.0936 0.0479 1.0000
7.250 1.1872 0.02918 0.01913 -0.0917 0.0453 1.0000
7.500 1.2046 0.03068 0.02074 -0.0901 0.0430 1.0000
7.750 1.2221 0.03241 0.02249 -0.0887 0.0402 1.0000
8.000 1.2420 0.03423 0.02446 -0.0875 0.0373 1.0000
8.250 1.2640 0.03611 0.02667 -0.0865 0.0353 1.0000
8.500 1.2859 0.03835 0.02919 -0.0854 0.0335 1.0000
8.750 1.3052 0.04068 0.03181 -0.0841 0.0316 1.0000
9.000 1.3197 0.04273 0.03398 -0.0828 0.0290 1.0000
9.250 1.3326 0.04612 0.03772 -0.0810 0.0271 1.0000
9.500 1.3409 0.04906 0.04123 -0.0782 0.0255 1.0000
9.750 1.3449 0.05165 0.04428 -0.0752 0.0232 1.0000
10.000 1.3471 0.05392 0.04684 -0.0724 0.0212 1.0000
10.250 1.3451 0.05661 0.04980 -0.0692 0.0202 1.0000
10.500 1.3389 0.05905 0.05239 -0.0659 0.0193 1.0000
11.000 1.3092 0.06636 0.06028 -0.0591 0.0181 1.0000
11.250 1.2913 0.07031 0.06459 -0.0567 0.0178 1.0000
11.500 1.2719 0.07487 0.06947 -0.0552 0.0175 1.0000
11.750 1.2514 0.08000 0.07488 -0.0549 0.0173 1.0000
12.000 1.2307 0.08567 0.08078 -0.0557 0.0174 1.0000
12.250 1.2099 0.09192 0.08724 -0.0576 0.0175 1.0000
12.500 1.1895 0.09886 0.09435 -0.0608 0.0177 1.0000
12.750 1.1701 0.10646 0.10209 -0.0651 0.0180 1.0000
13.000 1.1519 0.11465 0.11038 -0.0700 0.0183 1.0000
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Polar data table (+)
Polar graphs
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