HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 500,000 Max Cl/Cd: 133.24 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1606-il-500000.txt Download as CSV file: xf-hs1606-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3465 0.09792 0.09568 -0.0312 1.0000 0.0133
-8.250 -0.3490 0.09569 0.09350 -0.0309 1.0000 0.0136
-8.000 -0.3620 0.09468 0.09256 -0.0277 1.0000 0.0137
-7.750 -0.3487 0.09121 0.08910 -0.0321 0.9966 0.0140
-7.500 -0.3263 0.08653 0.08441 -0.0391 0.9924 0.0141
-7.250 -0.3022 0.08161 0.07949 -0.0466 0.9880 0.0142
-7.000 -0.2820 0.07382 0.07170 -0.0565 0.9845 0.0149
-6.750 -0.2575 0.07029 0.06815 -0.0614 0.9820 0.0156
-6.500 -0.2319 0.06662 0.06447 -0.0670 0.9766 0.0165
-6.250 -0.2004 0.06203 0.05984 -0.0751 0.9725 0.0178
-6.000 -0.1654 0.05658 0.05434 -0.0847 0.9673 0.0197
-5.750 -0.1206 0.05097 0.04862 -0.0954 0.9608 0.0218
-5.500 -0.0852 0.04148 0.03896 -0.1073 0.9556 0.0232
-5.250 -0.0594 0.03911 0.03652 -0.1097 0.9487 0.0246
-5.000 -0.0008 0.01777 0.01362 -0.1255 0.9444 0.0119
-4.750 0.0324 0.01375 0.00870 -0.1267 0.9396 0.0099
-4.500 0.0617 0.01239 0.00706 -0.1270 0.9345 0.0103
-4.250 0.0908 0.01150 0.00599 -0.1272 0.9304 0.0111
-4.000 0.1193 0.01091 0.00527 -0.1273 0.9254 0.0123
-3.750 0.1478 0.01044 0.00470 -0.1274 0.9206 0.0136
-3.500 0.1767 0.00985 0.00395 -0.1274 0.9168 0.0138
-3.250 0.2057 0.00943 0.00341 -0.1275 0.9122 0.0140
-3.000 0.2345 0.00909 0.00292 -0.1275 0.9080 0.0154
-2.750 0.2633 0.00858 0.00255 -0.1275 0.9044 0.0598
-2.500 0.2914 0.00840 0.00248 -0.1276 0.8993 0.0976
-2.250 0.3191 0.00832 0.00243 -0.1275 0.8938 0.1200
-2.000 0.3464 0.00829 0.00242 -0.1273 0.8876 0.1422
-1.750 0.3736 0.00827 0.00238 -0.1270 0.8803 0.1596
-1.500 0.4011 0.00824 0.00232 -0.1268 0.8742 0.1715
-1.250 0.4290 0.00820 0.00229 -0.1267 0.8681 0.1829
-1.000 0.4567 0.00819 0.00224 -0.1265 0.8629 0.1936
-0.750 0.4845 0.00816 0.00221 -0.1264 0.8565 0.2032
-0.500 0.5123 0.00810 0.00216 -0.1263 0.8506 0.2124
-0.250 0.5403 0.00808 0.00215 -0.1263 0.8454 0.2228
0.000 0.5684 0.00806 0.00214 -0.1263 0.8402 0.2336
0.250 0.5964 0.00802 0.00213 -0.1263 0.8354 0.2459
0.500 0.6245 0.00797 0.00214 -0.1263 0.8296 0.2605
0.750 0.6525 0.00789 0.00215 -0.1263 0.8237 0.2794
1.000 0.6806 0.00776 0.00218 -0.1264 0.8180 0.3250
1.250 0.7015 0.00634 0.00227 -0.1249 0.8112 1.0000
1.500 0.7293 0.00640 0.00227 -0.1248 0.8042 1.0000
1.750 0.7569 0.00644 0.00229 -0.1246 0.7957 1.0000
2.000 0.7846 0.00648 0.00232 -0.1244 0.7870 1.0000
2.250 0.8121 0.00654 0.00235 -0.1242 0.7782 1.0000
2.500 0.8390 0.00657 0.00239 -0.1239 0.7630 1.0000
2.750 0.8652 0.00661 0.00237 -0.1233 0.7377 1.0000
3.000 0.8914 0.00669 0.00240 -0.1228 0.7096 1.0000
3.250 0.9157 0.00693 0.00242 -0.1218 0.6476 1.0000
3.500 0.9357 0.00769 0.00268 -0.1202 0.5456 1.0000
3.750 0.9572 0.00844 0.00304 -0.1192 0.4642 1.0000
4.000 0.9791 0.00918 0.00342 -0.1182 0.3893 1.0000
4.250 1.0020 0.00980 0.00379 -0.1175 0.3359 1.0000
4.500 1.0247 0.01045 0.00417 -0.1167 0.2790 1.0000
4.750 1.0444 0.01149 0.00471 -0.1156 0.1799 1.0000
5.000 1.0599 0.01312 0.00565 -0.1138 0.0617 1.0000
5.250 1.0829 0.01378 0.00628 -0.1130 0.0484 1.0000
5.500 1.1059 0.01442 0.00692 -0.1121 0.0418 1.0000
5.750 1.1284 0.01511 0.00768 -0.1111 0.0378 1.0000
6.000 1.1519 0.01561 0.00827 -0.1104 0.0352 1.0000
6.250 1.1744 0.01624 0.00896 -0.1095 0.0326 1.0000
6.500 1.1949 0.01709 0.00986 -0.1082 0.0302 1.0000
6.750 1.2091 0.01881 0.01171 -0.1058 0.0280 1.0000
7.000 1.2294 0.01973 0.01272 -0.1045 0.0274 1.0000
7.250 1.2513 0.02039 0.01346 -0.1035 0.0264 1.0000
7.500 1.2725 0.02115 0.01432 -0.1024 0.0250 1.0000
7.750 1.2933 0.02193 0.01522 -0.1012 0.0234 1.0000
8.000 1.3153 0.02226 0.01557 -0.1005 0.0213 1.0000
8.250 1.3279 0.02479 0.01822 -0.0983 0.0186 1.0000
8.500 1.3516 0.02433 0.01782 -0.0978 0.0175 1.0000
8.750 1.3744 0.02427 0.01784 -0.0971 0.0157 1.0000
9.000 1.3973 0.02421 0.01779 -0.0966 0.0137 1.0000
9.250 1.4119 0.02536 0.01901 -0.0947 0.0111 1.0000
9.500 1.4380 0.02495 0.01859 -0.0946 0.0084 1.0000
9.750 1.4463 0.02671 0.02047 -0.0916 0.0067 1.0000
10.000 1.4580 0.02795 0.02190 -0.0891 0.0059 1.0000
10.250 1.4661 0.02932 0.02343 -0.0861 0.0054 1.0000
10.500 1.4736 0.03074 0.02499 -0.0832 0.0051 1.0000
10.750 1.4799 0.03225 0.02666 -0.0803 0.0048 1.0000
11.000 1.4832 0.03409 0.02866 -0.0772 0.0045 1.0000
11.250 1.4795 0.03682 0.03164 -0.0736 0.0043 1.0000
11.500 1.4657 0.04091 0.03610 -0.0693 0.0041 1.0000
11.750 1.4628 0.04357 0.03900 -0.0666 0.0040 1.0000
12.000 1.4631 0.04583 0.04146 -0.0645 0.0039 1.0000
12.250 1.4596 0.04861 0.04446 -0.0625 0.0037 1.0000
12.500 1.4517 0.05204 0.04812 -0.0607 0.0036 1.0000
12.750 1.4406 0.05601 0.05232 -0.0592 0.0036 1.0000
13.000 1.4262 0.06064 0.05719 -0.0584 0.0035 1.0000
13.250 1.4098 0.06583 0.06261 -0.0583 0.0035 1.0000
13.500 1.3895 0.07206 0.06908 -0.0593 0.0035 1.0000
13.750 1.3665 0.07943 0.07668 -0.0617 0.0035 1.0000
14.000 1.3434 0.08771 0.08517 -0.0655 0.0036 1.0000
14.250 1.3194 0.09726 0.09493 -0.0708 0.0036 1.0000
14.500 1.2942 0.10806 0.10591 -0.0773 0.0037 1.0000
14.750 1.2471 0.12534 0.12338 -0.0877 0.0040 1.0000
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Polar data table (+)
Polar graphs
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