HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 1,000,000 Max Cl/Cd: 168.96 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1708-il-1000000.txt Download as CSV file: xf-hs1708-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-708 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2598 0.09307 0.09141 -0.0596 0.9770 0.0150
-9.000 -0.2499 0.08905 0.08738 -0.0628 0.9633 0.0150
-8.750 -0.3450 0.02351 0.02053 -0.1297 0.9036 0.0081
-8.500 -0.3188 0.01938 0.01592 -0.1330 0.8970 0.0080
-8.250 -0.2920 0.01720 0.01339 -0.1344 0.8910 0.0080
-8.000 -0.2646 0.01566 0.01157 -0.1353 0.8859 0.0080
-7.750 -0.2364 0.01443 0.01010 -0.1360 0.8811 0.0080
-7.500 -0.2082 0.01347 0.00894 -0.1365 0.8765 0.0081
-7.250 -0.1798 0.01269 0.00797 -0.1369 0.8723 0.0082
-7.000 -0.1510 0.01200 0.00715 -0.1374 0.8684 0.0082
-6.750 -0.1221 0.01144 0.00646 -0.1378 0.8645 0.0083
-6.500 -0.0931 0.01077 0.00563 -0.1382 0.8609 0.0086
-6.250 -0.0641 0.01019 0.00489 -0.1385 0.8576 0.0092
-6.000 -0.0349 0.00975 0.00438 -0.1389 0.8546 0.0100
-5.750 -0.0057 0.00942 0.00398 -0.1392 0.8516 0.0109
-5.500 0.0235 0.00903 0.00355 -0.1395 0.8486 0.0136
-5.250 0.0526 0.00867 0.00319 -0.1398 0.8457 0.0225
-5.000 0.0815 0.00849 0.00300 -0.1400 0.8427 0.0296
-4.750 0.1107 0.00835 0.00285 -0.1403 0.8402 0.0337
-4.500 0.1398 0.00818 0.00269 -0.1406 0.8377 0.0390
-4.250 0.1689 0.00807 0.00257 -0.1408 0.8352 0.0427
-4.000 0.1979 0.00796 0.00243 -0.1410 0.8323 0.0468
-3.750 0.2267 0.00788 0.00234 -0.1412 0.8289 0.0525
-3.500 0.2557 0.00779 0.00225 -0.1414 0.8250 0.0573
-3.250 0.2846 0.00765 0.00213 -0.1416 0.8205 0.0640
-3.000 0.3133 0.00761 0.00204 -0.1416 0.8162 0.0675
-2.750 0.3423 0.00749 0.00194 -0.1419 0.8123 0.0759
-2.500 0.3713 0.00740 0.00185 -0.1420 0.8085 0.0827
-2.250 0.4002 0.00731 0.00179 -0.1422 0.8046 0.0943
-2.000 0.4290 0.00724 0.00174 -0.1424 0.8007 0.1075
-1.750 0.4580 0.00716 0.00170 -0.1426 0.7970 0.1202
-1.500 0.4870 0.00708 0.00166 -0.1428 0.7928 0.1319
-1.250 0.5158 0.00704 0.00163 -0.1429 0.7885 0.1431
-1.000 0.5445 0.00704 0.00161 -0.1431 0.7849 0.1524
-0.750 0.5736 0.00699 0.00161 -0.1433 0.7814 0.1625
-0.500 0.6024 0.00695 0.00160 -0.1434 0.7774 0.1709
-0.250 0.6312 0.00694 0.00159 -0.1436 0.7733 0.1799
0.000 0.6599 0.00692 0.00159 -0.1437 0.7687 0.1896
0.250 0.6887 0.00689 0.00159 -0.1438 0.7638 0.1978
0.500 0.7174 0.00687 0.00160 -0.1440 0.7591 0.2086
0.750 0.7460 0.00686 0.00162 -0.1441 0.7545 0.2192
1.000 0.7748 0.00682 0.00163 -0.1443 0.7484 0.2320
1.250 0.8031 0.00681 0.00164 -0.1443 0.7417 0.2482
1.500 0.8318 0.00675 0.00167 -0.1445 0.7336 0.2717
1.750 0.8602 0.00664 0.00172 -0.1447 0.7243 0.3445
2.000 0.8820 0.00539 0.00185 -0.1436 0.7137 1.0000
2.250 0.9101 0.00545 0.00188 -0.1436 0.7002 1.0000
2.500 0.9377 0.00555 0.00192 -0.1435 0.6820 1.0000
2.750 0.9642 0.00574 0.00198 -0.1431 0.6486 1.0000
3.000 0.9865 0.00630 0.00217 -0.1420 0.5738 1.0000
3.250 1.0086 0.00696 0.00248 -0.1410 0.5047 1.0000
3.500 1.0326 0.00743 0.00272 -0.1404 0.4553 1.0000
3.750 1.0556 0.00799 0.00300 -0.1396 0.3999 1.0000
4.250 1.1044 0.00880 0.00350 -0.1385 0.3364 1.0000
4.500 1.1295 0.00912 0.00372 -0.1381 0.3162 1.0000
4.750 1.1551 0.00939 0.00393 -0.1377 0.2998 1.0000
5.000 1.1804 0.00967 0.00415 -0.1373 0.2828 1.0000
5.250 1.2052 0.00998 0.00438 -0.1368 0.2634 1.0000
5.500 1.2293 0.01035 0.00464 -0.1362 0.2402 1.0000
5.750 1.2519 0.01084 0.00497 -0.1354 0.2080 1.0000
6.000 1.2730 0.01145 0.00538 -0.1343 0.1705 1.0000
6.250 1.2925 0.01219 0.00588 -0.1329 0.1286 1.0000
6.500 1.3098 0.01312 0.00651 -0.1312 0.0823 1.0000
6.750 1.3302 0.01374 0.00702 -0.1300 0.0623 1.0000
7.000 1.3522 0.01421 0.00745 -0.1290 0.0530 1.0000
7.250 1.3731 0.01475 0.00795 -0.1279 0.0453 1.0000
7.500 1.3960 0.01509 0.00833 -0.1270 0.0429 1.0000
7.750 1.4172 0.01555 0.00878 -0.1260 0.0395 1.0000
8.000 1.4361 0.01621 0.00946 -0.1244 0.0350 1.0000
8.250 1.4580 0.01653 0.00982 -0.1234 0.0341 1.0000
8.500 1.4787 0.01693 0.01025 -0.1223 0.0327 1.0000
8.750 1.4982 0.01739 0.01075 -0.1209 0.0311 1.0000
9.000 1.5161 0.01794 0.01131 -0.1192 0.0293 1.0000
9.250 1.5294 0.01873 0.01216 -0.1167 0.0270 1.0000
9.500 1.5423 0.01943 0.01294 -0.1141 0.0260 1.0000
9.750 1.5604 0.01982 0.01336 -0.1126 0.0253 1.0000
10.000 1.5778 0.02026 0.01385 -0.1110 0.0243 1.0000
10.250 1.5947 0.02075 0.01435 -0.1094 0.0230 1.0000
10.500 1.6097 0.02139 0.01500 -0.1075 0.0217 1.0000
10.750 1.6209 0.02230 0.01596 -0.1050 0.0202 1.0000
11.000 1.6278 0.02355 0.01733 -0.1020 0.0191 1.0000
11.250 1.6440 0.02413 0.01796 -0.1005 0.0187 1.0000
11.500 1.6594 0.02479 0.01866 -0.0989 0.0182 1.0000
11.750 1.6741 0.02551 0.01943 -0.0973 0.0175 1.0000
12.000 1.6887 0.02624 0.02021 -0.0958 0.0167 1.0000
12.250 1.7017 0.02710 0.02110 -0.0941 0.0158 1.0000
12.500 1.7122 0.02818 0.02221 -0.0922 0.0149 1.0000
12.750 1.7154 0.02989 0.02401 -0.0895 0.0138 1.0000
13.000 1.7270 0.03092 0.02512 -0.0879 0.0134 1.0000
13.250 1.7398 0.03187 0.02614 -0.0865 0.0130 1.0000
13.500 1.7512 0.03295 0.02728 -0.0850 0.0124 1.0000
13.750 1.7617 0.03414 0.02851 -0.0836 0.0117 1.0000
14.000 1.7703 0.03549 0.02990 -0.0820 0.0109 1.0000
14.250 1.7736 0.03736 0.03182 -0.0800 0.0099 1.0000
14.500 1.7780 0.03916 0.03372 -0.0783 0.0093 1.0000
14.750 1.7862 0.04064 0.03527 -0.0769 0.0088 1.0000
15.000 1.7922 0.04235 0.03704 -0.0755 0.0081 1.0000
15.250 1.7943 0.04446 0.03920 -0.0740 0.0074 1.0000
15.500 1.7894 0.04739 0.04223 -0.0722 0.0065 1.0000
15.750 1.7919 0.04964 0.04459 -0.0710 0.0062 1.0000
16.000 1.7923 0.05221 0.04725 -0.0699 0.0057 1.0000
16.250 1.7902 0.05511 0.05024 -0.0689 0.0053 1.0000
16.500 1.7857 0.05844 0.05366 -0.0681 0.0050 1.0000
16.750 1.7768 0.06249 0.05782 -0.0675 0.0046 1.0000
17.000 1.7629 0.06745 0.06293 -0.0674 0.0043 1.0000
17.250 1.7568 0.07152 0.06712 -0.0675 0.0042 1.0000
17.500 1.7483 0.07608 0.07181 -0.0680 0.0041 1.0000
17.750 1.7381 0.08108 0.07695 -0.0689 0.0040 1.0000
18.000 1.7263 0.08650 0.08251 -0.0702 0.0039 1.0000
18.250 1.7123 0.09243 0.08858 -0.0718 0.0038 1.0000
18.500 1.6962 0.09880 0.09510 -0.0739 0.0038 1.0000
18.750 1.6790 0.10554 0.10198 -0.0763 0.0037 1.0000
19.000 1.6610 0.11259 0.10917 -0.0791 0.0037 1.0000
19.250 1.6420 0.11998 0.11670 -0.0823 0.0036 1.0000
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