HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 100,000 Max Cl/Cd: 58.37 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1712-il-100000-n5.txt Download as CSV file: xf-hs1712-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3857 0.12181 0.11685 -0.0293 1.0000 0.0605
-9.000 -0.3949 0.11902 0.11413 -0.0291 1.0000 0.0607
-8.500 -0.4228 0.10752 0.10267 -0.0283 1.0000 0.0368
-8.250 -0.4202 0.10439 0.09957 -0.0290 0.9981 0.0364
-8.000 -0.4154 0.10012 0.09532 -0.0323 0.9942 0.0360
-7.750 -0.4087 0.09458 0.08978 -0.0379 0.9891 0.0361
-7.500 -0.3974 0.08687 0.08204 -0.0475 0.9839 0.0366
-7.000 -0.3645 0.06816 0.06309 -0.0693 0.9733 0.0369
-6.750 -0.3355 0.05048 0.04463 -0.0871 0.9703 0.0368
-6.500 -0.3076 0.04516 0.03888 -0.0921 0.9660 0.0378
-6.250 -0.2706 0.03846 0.03111 -0.0989 0.9635 0.0407
-6.000 -0.2355 0.03617 0.02850 -0.1020 0.9609 0.0424
-5.750 -0.1971 0.03347 0.02523 -0.1055 0.9592 0.0443
-5.500 -0.1652 0.03198 0.02345 -0.1072 0.9555 0.0468
-5.250 -0.1331 0.03067 0.02181 -0.1087 0.9515 0.0498
-5.000 -0.0987 0.02970 0.02072 -0.1105 0.9485 0.0521
-4.750 -0.0619 0.02871 0.01947 -0.1127 0.9461 0.0560
-4.500 -0.0239 0.02789 0.01844 -0.1151 0.9442 0.0606
-4.250 0.0018 0.02732 0.01788 -0.1150 0.9376 0.0640
-4.000 0.0368 0.02670 0.01717 -0.1167 0.9336 0.0693
-3.750 0.0751 0.02608 0.01647 -0.1190 0.9305 0.0756
-3.500 0.1056 0.02565 0.01600 -0.1197 0.9242 0.0826
-3.250 0.1388 0.02517 0.01554 -0.1210 0.9184 0.0908
-3.000 0.1773 0.02460 0.01499 -0.1232 0.9149 0.1008
-2.750 0.2065 0.02420 0.01463 -0.1236 0.9075 0.1131
-2.500 0.2405 0.02375 0.01421 -0.1248 0.9015 0.1320
-2.250 0.2789 0.02329 0.01384 -0.1270 0.8980 0.1561
-2.000 0.3039 0.02317 0.01375 -0.1265 0.8885 0.1788
-1.750 0.3390 0.02286 0.01344 -0.1279 0.8837 0.2049
-1.500 0.3714 0.02256 0.01317 -0.1288 0.8777 0.2275
-1.250 0.4009 0.02229 0.01296 -0.1291 0.8693 0.2533
-1.000 0.4384 0.02175 0.01251 -0.1310 0.8653 0.2836
-0.750 0.4647 0.02155 0.01242 -0.1307 0.8553 0.3192
-0.500 0.5012 0.02081 0.01213 -0.1325 0.8506 0.4326
-0.250 0.5140 0.01949 0.01210 -0.1279 0.8431 0.8697
0.000 0.5441 0.01889 0.01140 -0.1278 0.8342 1.0000
0.250 0.5748 0.01873 0.01109 -0.1281 0.8236 1.0000
0.500 0.6143 0.01829 0.01050 -0.1300 0.8166 1.0000
0.750 0.6440 0.01821 0.01031 -0.1301 0.8044 1.0000
1.000 0.6805 0.01795 0.00994 -0.1316 0.7949 1.0000
1.250 0.7252 0.01754 0.00940 -0.1347 0.7875 1.0000
1.500 0.7573 0.01752 0.00931 -0.1354 0.7747 1.0000
1.750 0.7697 0.01793 0.00972 -0.1323 0.7533 1.0000
2.000 0.8113 0.01764 0.00931 -0.1348 0.7416 1.0000
2.250 0.8541 0.01736 0.00892 -0.1375 0.7296 1.0000
2.500 0.8959 0.01719 0.00861 -0.1401 0.7160 1.0000
2.750 0.9335 0.01718 0.00848 -0.1420 0.7003 1.0000
3.000 0.9638 0.01735 0.00858 -0.1424 0.6826 1.0000
3.250 0.9921 0.01756 0.00872 -0.1423 0.6635 1.0000
3.500 1.0188 0.01780 0.00889 -0.1420 0.6433 1.0000
3.750 1.0440 0.01807 0.00910 -0.1414 0.6211 1.0000
4.000 1.0677 0.01836 0.00931 -0.1404 0.5964 1.0000
4.250 1.0910 0.01869 0.00951 -0.1394 0.5700 1.0000
4.500 1.1119 0.01907 0.00979 -0.1379 0.5405 1.0000
4.750 1.1316 0.01951 0.01008 -0.1362 0.5084 1.0000
5.000 1.1503 0.02001 0.01041 -0.1343 0.4773 1.0000
5.500 1.1868 0.02116 0.01124 -0.1307 0.4255 1.0000
5.750 1.2049 0.02175 0.01174 -0.1289 0.4049 1.0000
6.000 1.2233 0.02235 0.01225 -0.1272 0.3881 1.0000
6.250 1.2416 0.02296 0.01278 -0.1256 0.3739 1.0000
6.500 1.2594 0.02358 0.01334 -0.1238 0.3616 1.0000
6.750 1.2777 0.02420 0.01394 -0.1222 0.3509 1.0000
7.000 1.2959 0.02489 0.01456 -0.1206 0.3412 1.0000
7.250 1.3144 0.02551 0.01523 -0.1191 0.3303 1.0000
7.500 1.3325 0.02615 0.01592 -0.1175 0.3196 1.0000
7.750 1.3496 0.02682 0.01661 -0.1157 0.3092 1.0000
8.000 1.3671 0.02740 0.01732 -0.1141 0.2986 1.0000
8.250 1.3832 0.02807 0.01804 -0.1122 0.2889 1.0000
8.500 1.3987 0.02876 0.01880 -0.1103 0.2787 1.0000
8.750 1.4141 0.02947 0.01959 -0.1084 0.2690 1.0000
9.000 1.4279 0.03026 0.02041 -0.1063 0.2593 1.0000
9.250 1.4426 0.03103 0.02130 -0.1044 0.2494 1.0000
9.500 1.4544 0.03195 0.02223 -0.1021 0.2400 1.0000
9.750 1.4678 0.03282 0.02322 -0.1001 0.2290 1.0000
10.000 1.4789 0.03382 0.02428 -0.0978 0.2187 1.0000
10.250 1.4883 0.03492 0.02543 -0.0954 0.2080 1.0000
10.500 1.4987 0.03604 0.02663 -0.0932 0.1968 1.0000
10.750 1.5066 0.03732 0.02795 -0.0908 0.1866 1.0000
11.000 1.5138 0.03869 0.02937 -0.0884 0.1764 1.0000
11.250 1.5217 0.04008 0.03087 -0.0862 0.1668 1.0000
11.500 1.5261 0.04173 0.03253 -0.0838 0.1586 1.0000
11.750 1.5330 0.04330 0.03422 -0.0817 0.1500 1.0000
12.000 1.5364 0.04514 0.03610 -0.0794 0.1432 1.0000
12.250 1.5414 0.04694 0.03803 -0.0774 0.1363 1.0000
12.750 1.5471 0.05104 0.04232 -0.0735 0.1256 1.0000
13.000 1.5486 0.05329 0.04467 -0.0717 0.1212 1.0000
13.250 1.5489 0.05571 0.04716 -0.0700 0.1175 1.0000
13.500 1.5520 0.05800 0.04963 -0.0686 0.1133 1.0000
13.750 1.5524 0.06059 0.05234 -0.0673 0.1098 1.0000
14.000 1.5506 0.06347 0.05526 -0.0661 0.1066 1.0000
14.250 1.5515 0.06622 0.05821 -0.0652 0.1026 1.0000
14.500 1.5497 0.06930 0.06142 -0.0644 0.0993 1.0000
14.750 1.5462 0.07262 0.06478 -0.0638 0.0967 1.0000
15.000 1.5451 0.07585 0.06824 -0.0634 0.0934 1.0000
15.250 1.5417 0.07939 0.07194 -0.0632 0.0904 1.0000
15.500 1.5368 0.08315 0.07577 -0.0632 0.0879 1.0000
15.750 1.5323 0.08707 0.07990 -0.0634 0.0848 1.0000
16.000 1.5264 0.09124 0.08422 -0.0639 0.0820 1.0000
16.250 1.5200 0.09548 0.08852 -0.0646 0.0797 1.0000
16.500 1.5137 0.09990 0.09312 -0.0655 0.0772 1.0000
16.750 1.5077 0.10425 0.09755 -0.0666 0.0749 1.0000
17.000 1.5041 0.10811 0.10140 -0.0675 0.0726 1.0000
17.250 1.4954 0.11323 0.10676 -0.0693 0.0700 1.0000
17.500 1.4913 0.11738 0.11098 -0.0706 0.0676 1.0000
17.750 1.4833 0.12257 0.11635 -0.0728 0.0653 1.0000
18.000 1.4732 0.12837 0.12238 -0.0756 0.0629 1.0000
18.250 1.4692 0.13285 0.12693 -0.0778 0.0608 1.0000
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