HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 50,000 Max Cl/Cd: 38.34 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1712-il-50000-n5.txt Download as CSV file: xf-hs1712-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3771 0.12035 0.11347 -0.0275 1.0000 0.1140
-8.250 -0.3826 0.11750 0.11070 -0.0265 1.0000 0.1117
-7.750 -0.4276 0.10696 0.10029 -0.0285 1.0000 0.0672
-7.500 -0.4293 0.10390 0.09729 -0.0279 1.0000 0.0665
-7.250 -0.4323 0.10042 0.09387 -0.0285 1.0000 0.0661
-7.000 -0.4340 0.09662 0.09011 -0.0299 1.0000 0.0659
-6.750 -0.4335 0.09251 0.08603 -0.0318 1.0000 0.0657
-6.500 -0.4302 0.08808 0.08161 -0.0344 1.0000 0.0655
-6.250 -0.4236 0.08335 0.07684 -0.0376 1.0000 0.0650
-6.000 -0.4130 0.07809 0.07151 -0.0416 1.0000 0.0642
-5.750 -0.3971 0.07208 0.06534 -0.0468 1.0000 0.0635
-5.500 -0.3677 0.06561 0.05858 -0.0543 0.9978 0.0641
-5.250 -0.3229 0.05726 0.04960 -0.0654 0.9942 0.0666
-5.000 -0.2797 0.05100 0.04266 -0.0733 0.9909 0.0682
-4.750 -0.2417 0.04816 0.03947 -0.0777 0.9868 0.0714
-4.500 -0.1974 0.04412 0.03463 -0.0834 0.9841 0.0759
-4.250 -0.1603 0.04228 0.03247 -0.0865 0.9802 0.0798
-4.000 -0.1216 0.04029 0.02998 -0.0898 0.9761 0.0856
-3.750 -0.0816 0.03887 0.02812 -0.0929 0.9726 0.0924
-3.500 -0.0467 0.03804 0.02717 -0.0950 0.9674 0.0993
-3.250 -0.0098 0.03715 0.02602 -0.0973 0.9623 0.1080
-3.000 0.0297 0.03645 0.02502 -0.0999 0.9586 0.1187
-2.750 0.0600 0.03599 0.02457 -0.1009 0.9515 0.1284
-2.500 0.0970 0.03550 0.02399 -0.1030 0.9467 0.1415
-2.250 0.1318 0.03512 0.02351 -0.1046 0.9408 0.1595
-2.000 0.1658 0.03486 0.02312 -0.1060 0.9338 0.1847
-1.750 0.2054 0.03463 0.02291 -0.1087 0.9293 0.2172
-1.500 0.2331 0.03445 0.02275 -0.1091 0.9201 0.2494
-1.250 0.2722 0.03411 0.02253 -0.1118 0.9146 0.2956
-1.000 0.3016 0.03380 0.02239 -0.1125 0.9052 0.3392
-0.750 0.3408 0.03315 0.02218 -0.1151 0.8990 0.4195
-0.500 0.3558 0.03185 0.02225 -0.1116 0.8900 0.7519
-0.250 0.3878 0.03124 0.02147 -0.1118 0.8809 1.0000
0.250 0.4468 0.03158 0.02131 -0.1128 0.8608 1.0000
0.500 0.4789 0.03166 0.02120 -0.1136 0.8512 1.0000
0.750 0.5086 0.03175 0.02112 -0.1140 0.8403 1.0000
1.000 0.5487 0.03147 0.02068 -0.1159 0.8328 1.0000
1.250 0.5761 0.03153 0.02064 -0.1158 0.8203 1.0000
1.500 0.6072 0.03147 0.02048 -0.1162 0.8096 1.0000
1.750 0.6462 0.03105 0.01996 -0.1177 0.8021 1.0000
2.000 0.6765 0.03094 0.01980 -0.1178 0.7912 1.0000
2.250 0.7072 0.03081 0.01962 -0.1180 0.7802 1.0000
2.500 0.7326 0.03091 0.01970 -0.1174 0.7666 1.0000
2.750 0.7598 0.03089 0.01966 -0.1170 0.7533 1.0000
3.000 0.7917 0.03062 0.01938 -0.1172 0.7415 1.0000
3.250 0.8280 0.03014 0.01888 -0.1180 0.7309 1.0000
3.500 0.8694 0.02943 0.01816 -0.1195 0.7205 1.0000
3.750 0.9023 0.02920 0.01793 -0.1199 0.7057 1.0000
4.000 0.9349 0.02904 0.01776 -0.1202 0.6896 1.0000
4.250 0.9668 0.02893 0.01764 -0.1204 0.6718 1.0000
4.500 0.9984 0.02888 0.01760 -0.1206 0.6529 1.0000
4.750 1.0294 0.02886 0.01757 -0.1207 0.6326 1.0000
5.000 1.0598 0.02891 0.01757 -0.1207 0.6115 1.0000
5.250 1.0836 0.02920 0.01787 -0.1196 0.5886 1.0000
5.500 1.1085 0.02948 0.01812 -0.1188 0.5659 1.0000
5.750 1.1325 0.02986 0.01846 -0.1178 0.5435 1.0000
6.000 1.1556 0.03028 0.01882 -0.1168 0.5219 1.0000
6.250 1.1784 0.03077 0.01928 -0.1158 0.5018 1.0000
6.500 1.2007 0.03133 0.01979 -0.1147 0.4828 1.0000
6.750 1.2234 0.03191 0.02033 -0.1138 0.4651 1.0000
7.000 1.2466 0.03254 0.02091 -0.1130 0.4485 1.0000
7.250 1.2669 0.03325 0.02161 -0.1117 0.4320 1.0000
7.500 1.2850 0.03405 0.02242 -0.1101 0.4161 1.0000
7.750 1.3027 0.03487 0.02328 -0.1086 0.4006 1.0000
8.000 1.3204 0.03572 0.02414 -0.1070 0.3860 1.0000
8.250 1.3384 0.03657 0.02497 -0.1055 0.3720 1.0000
8.500 1.3575 0.03741 0.02575 -0.1042 0.3583 1.0000
8.750 1.3744 0.03838 0.02676 -0.1026 0.3450 1.0000
9.000 1.3886 0.03948 0.02797 -0.1007 0.3322 1.0000
9.250 1.4024 0.04059 0.02917 -0.0988 0.3200 1.0000
9.500 1.4159 0.04167 0.03032 -0.0968 0.3081 1.0000
9.750 1.4211 0.04299 0.03187 -0.0937 0.2963 1.0000
10.000 1.4282 0.04428 0.03330 -0.0910 0.2851 1.0000
10.250 1.4379 0.04540 0.03443 -0.0887 0.2747 1.0000
10.500 1.4407 0.04701 0.03629 -0.0857 0.2635 1.0000
10.750 1.4474 0.04844 0.03783 -0.0833 0.2536 1.0000
11.000 1.4526 0.05003 0.03957 -0.0808 0.2437 1.0000
11.250 1.4579 0.05176 0.04145 -0.0785 0.2344 1.0000
11.500 1.4635 0.05342 0.04321 -0.0763 0.2254 1.0000
11.750 1.4664 0.05549 0.04548 -0.0741 0.2165 1.0000
12.000 1.4715 0.05728 0.04733 -0.0720 0.2083 1.0000
12.250 1.4720 0.05969 0.04994 -0.0700 0.2000 1.0000
12.500 1.4755 0.06173 0.05206 -0.0681 0.1925 1.0000
12.750 1.4746 0.06440 0.05490 -0.0663 0.1853 1.0000
13.000 1.4742 0.06698 0.05762 -0.0646 0.1784 1.0000
13.250 1.4767 0.06936 0.06007 -0.0632 0.1724 1.0000
13.500 1.4691 0.07301 0.06400 -0.0618 0.1666 1.0000
13.750 1.4710 0.07540 0.06643 -0.0607 0.1609 1.0000
14.000 1.4636 0.07916 0.07039 -0.0598 0.1560 1.0000
14.250 1.4512 0.08372 0.07520 -0.0593 0.1514 1.0000
14.500 1.4522 0.08638 0.07791 -0.0588 0.1464 1.0000
14.750 1.4413 0.09099 0.08270 -0.0589 0.1423 1.0000
15.000 1.4181 0.09777 0.08979 -0.0602 0.1389 1.0000
15.250 1.4044 0.10323 0.09542 -0.0614 0.1350 1.0000
15.500 1.4137 0.10476 0.09691 -0.0610 0.1304 1.0000
15.750 1.3737 0.11561 0.10812 -0.0656 0.1284 1.0000
16.000 1.3006 0.13523 0.12805 -0.0764 0.1270 1.0000
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Polar data table (+)
Polar graphs
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