HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 50,000 Max Cl/Cd: 36.43 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1712-il-50000.txt Download as CSV file: xf-hs1712-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-712 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3791 0.11978 0.11316 -0.0202 1.0000 0.2001
-7.750 -0.4092 0.12014 0.11368 -0.0182 1.0000 0.2029
-7.500 -0.4428 0.12079 0.11451 -0.0201 1.0000 0.2042
-7.250 -0.3971 0.11249 0.10612 -0.0146 1.0000 0.2132
-7.000 -0.4125 0.11111 0.10485 -0.0129 1.0000 0.2193
-6.750 -0.4425 0.11123 0.10512 -0.0181 1.0000 0.2232
-6.500 -0.4206 0.10540 0.09931 -0.0108 1.0000 0.2297
-6.250 -0.4257 0.10320 0.09718 -0.0107 1.0000 0.2386
-6.000 -0.4335 0.10032 0.09438 -0.0131 1.0000 0.2446
-5.750 -0.4257 0.09706 0.09115 -0.0092 1.0000 0.2517
-5.500 -0.4300 0.09440 0.08854 -0.0143 1.0000 0.2631
-5.250 -0.4232 0.09113 0.08533 -0.0096 1.0000 0.2698
-5.000 -0.4200 0.08808 0.08230 -0.0126 1.0000 0.2835
-4.750 -0.4132 0.08532 0.07955 -0.0143 1.0000 0.3010
-4.500 -0.4061 0.08252 0.07678 -0.0138 1.0000 0.3195
-4.250 -0.3994 0.07969 0.07399 -0.0120 1.0000 0.3385
-4.000 -0.3925 0.07697 0.07132 -0.0097 1.0000 0.3583
-3.750 -0.3848 0.07443 0.06882 -0.0075 1.0000 0.3804
-3.500 -0.2235 0.05692 0.04919 -0.0617 1.0000 0.1854
-3.250 -0.1992 0.05353 0.04577 -0.0630 1.0000 0.1802
-3.000 -0.1629 0.05026 0.04206 -0.0671 1.0000 0.1784
-2.750 -0.1260 0.04754 0.03881 -0.0708 1.0000 0.1790
-2.500 -0.0876 0.04556 0.03606 -0.0742 1.0000 0.1847
-2.250 -0.0630 0.04442 0.03497 -0.0750 1.0000 0.1937
-2.000 -0.0298 0.04350 0.03346 -0.0770 1.0000 0.2045
-1.750 -0.0043 0.04272 0.03269 -0.0777 1.0000 0.2158
-1.500 0.0243 0.04214 0.03186 -0.0787 1.0000 0.2306
-1.250 0.0537 0.04169 0.03123 -0.0798 1.0000 0.2504
-1.000 0.0828 0.04140 0.03082 -0.0808 1.0000 0.2826
-0.750 0.1109 0.04128 0.03074 -0.0815 1.0000 0.3250
-0.500 0.1391 0.04139 0.03103 -0.0824 1.0000 0.3813
-0.250 0.1694 0.04153 0.03156 -0.0837 1.0000 0.4606
0.000 0.1922 0.04039 0.03224 -0.0814 1.0000 0.7976
0.250 0.1953 0.04070 0.03214 -0.0788 1.0000 1.0000
0.500 0.2167 0.04190 0.03291 -0.0792 1.0000 1.0000
0.750 0.2750 0.04343 0.03396 -0.0862 0.9843 1.0000
1.000 0.3230 0.04451 0.03474 -0.0913 0.9664 1.0000
1.250 0.3655 0.04550 0.03551 -0.0952 0.9504 1.0000
1.500 0.4074 0.04640 0.03623 -0.0988 0.9344 1.0000
1.750 0.4495 0.04715 0.03684 -0.1023 0.9177 1.0000
2.000 0.4915 0.04775 0.03733 -0.1055 0.9007 1.0000
2.250 0.5336 0.04823 0.03771 -0.1085 0.8837 1.0000
2.500 0.5758 0.04856 0.03797 -0.1114 0.8667 1.0000
2.750 0.6188 0.04870 0.03807 -0.1141 0.8495 1.0000
3.000 0.6632 0.04861 0.03795 -0.1168 0.8324 1.0000
3.250 0.6939 0.04877 0.03811 -0.1173 0.8120 1.0000
3.500 0.7346 0.04846 0.03783 -0.1189 0.7931 1.0000
3.750 0.7839 0.04764 0.03703 -0.1214 0.7771 1.0000
4.000 0.8123 0.04759 0.03700 -0.1210 0.7555 1.0000
4.250 0.8589 0.04644 0.03592 -0.1225 0.7393 1.0000
4.500 0.9037 0.04520 0.03472 -0.1236 0.7232 1.0000
4.750 0.9490 0.04376 0.03333 -0.1245 0.7074 1.0000
5.000 0.9977 0.04218 0.03183 -0.1259 0.6919 1.0000
5.250 1.0552 0.04022 0.02994 -0.1286 0.6762 1.0000
5.500 1.1146 0.03852 0.02831 -0.1319 0.6589 1.0000
5.750 1.1623 0.03762 0.02744 -0.1339 0.6395 1.0000
6.000 1.2031 0.03724 0.02710 -0.1350 0.6196 1.0000
6.250 1.2391 0.03719 0.02708 -0.1355 0.5999 1.0000
6.500 1.2734 0.03729 0.02718 -0.1358 0.5807 1.0000
6.750 1.3082 0.03739 0.02729 -0.1362 0.5618 1.0000
7.000 1.3386 0.03768 0.02756 -0.1360 0.5427 1.0000
7.250 1.3699 0.03791 0.02775 -0.1358 0.5238 1.0000
7.500 1.3969 0.03834 0.02816 -0.1351 0.5050 1.0000
7.750 1.4195 0.03900 0.02882 -0.1337 0.4863 1.0000
8.000 1.4422 0.03970 0.02951 -0.1324 0.4678 1.0000
8.250 1.4651 0.04051 0.03034 -0.1312 0.4497 1.0000
8.500 1.4810 0.04166 0.03157 -0.1290 0.4326 1.0000
8.750 1.4972 0.04283 0.03281 -0.1269 0.4154 1.0000
9.000 1.5129 0.04405 0.03411 -0.1248 0.3984 1.0000
9.250 1.5292 0.04527 0.03538 -0.1227 0.3813 1.0000
9.500 1.5468 0.04657 0.03671 -0.1209 0.3643 1.0000
9.750 1.5645 0.04809 0.03826 -0.1192 0.3476 1.0000
10.000 1.5760 0.05010 0.04040 -0.1168 0.3325 1.0000
10.250 1.5843 0.05228 0.04274 -0.1139 0.3183 1.0000
10.500 1.5946 0.05440 0.04496 -0.1113 0.3047 1.0000
10.750 1.6135 0.05618 0.04677 -0.1099 0.2909 1.0000
11.000 1.5909 0.05929 0.05031 -0.1030 0.2832 1.0000
11.250 1.6064 0.06123 0.05228 -0.1013 0.2721 1.0000
11.500 1.5748 0.06482 0.05624 -0.0937 0.2674 1.0000
11.750 1.6061 0.06631 0.05768 -0.0942 0.2561 1.0000
12.000 1.5614 0.07067 0.06240 -0.0858 0.2545 1.0000
12.250 1.5096 0.07645 0.06848 -0.0786 0.2537 1.0000
12.500 1.4430 0.08478 0.07707 -0.0732 0.2544 1.0000
12.750 1.3524 0.09841 0.09084 -0.0719 0.2564 1.0000
13.000 1.0529 0.16050 0.15238 -0.1042 0.2864 1.0000
13.250 1.0564 0.16660 0.15855 -0.1063 0.2899 1.0000
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Polar data table (+)
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