HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 100,000 Max Cl/Cd: 66.51 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1708-il-100000-n5.txt Download as CSV file: xf-hs1708-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3273 0.11335 0.10834 -0.0369 1.0000 0.0325
-9.250 -0.3326 0.11147 0.10653 -0.0350 1.0000 0.0320
-9.000 -0.3409 0.10989 0.10503 -0.0327 1.0000 0.0317
-8.500 -0.3339 0.10379 0.09899 -0.0355 0.9949 0.0312
-8.250 -0.3239 0.09992 0.09513 -0.0389 0.9897 0.0309
-8.000 -0.3132 0.09591 0.09113 -0.0427 0.9851 0.0302
-7.750 -0.3068 0.09214 0.08738 -0.0457 0.9780 0.0295
-7.500 -0.2920 0.08724 0.08247 -0.0517 0.9727 0.0288
-7.250 -0.2814 0.08265 0.07788 -0.0567 0.9651 0.0282
-7.000 -0.2629 0.07716 0.07238 -0.0642 0.9602 0.0279
-6.750 -0.2466 0.07219 0.06737 -0.0702 0.9543 0.0279
-6.500 -0.2252 0.06687 0.06200 -0.0774 0.9490 0.0281
-6.250 -0.1947 0.06073 0.05576 -0.0866 0.9456 0.0288
-6.000 -0.1681 0.05468 0.04957 -0.0945 0.9401 0.0304
-5.750 -0.1171 0.03788 0.03202 -0.1148 0.9362 0.0350
-5.500 -0.0890 0.03900 0.03316 -0.1151 0.9336 0.0396
-5.250 -0.0412 0.02950 0.02251 -0.1254 0.9325 0.0468
-5.000 -0.0027 0.02671 0.01891 -0.1290 0.9311 0.0555
-4.750 0.0244 0.02615 0.01833 -0.1295 0.9275 0.0599
-4.500 0.0546 0.02464 0.01624 -0.1305 0.9239 0.0671
-4.250 0.0854 0.02376 0.01525 -0.1316 0.9214 0.0715
-4.000 0.1185 0.02297 0.01413 -0.1330 0.9193 0.0787
-3.750 0.1522 0.02226 0.01329 -0.1344 0.9175 0.0848
-3.500 0.1869 0.02163 0.01243 -0.1359 0.9159 0.0925
-3.250 0.2091 0.02147 0.01224 -0.1351 0.9109 0.0990
-3.000 0.2388 0.02106 0.01165 -0.1356 0.9076 0.1068
-2.750 0.2703 0.02080 0.01139 -0.1365 0.9051 0.1157
-2.500 0.3034 0.02050 0.01101 -0.1376 0.9030 0.1265
-2.250 0.3375 0.02017 0.01059 -0.1389 0.9013 0.1377
-2.000 0.3586 0.02027 0.01070 -0.1378 0.8949 0.1488
-1.750 0.3900 0.02009 0.01051 -0.1385 0.8911 0.1622
-1.500 0.4241 0.01982 0.01022 -0.1396 0.8883 0.1763
-1.250 0.4516 0.01977 0.01016 -0.1396 0.8833 0.1908
-1.000 0.4788 0.01971 0.01012 -0.1395 0.8782 0.2045
-0.750 0.5106 0.01954 0.00996 -0.1402 0.8749 0.2206
-0.500 0.5442 0.01932 0.00976 -0.1412 0.8724 0.2377
-0.250 0.5661 0.01942 0.00990 -0.1401 0.8649 0.2524
0.000 0.5998 0.01906 0.00960 -0.1409 0.8598 0.2718
0.250 0.6283 0.01882 0.00942 -0.1406 0.8517 0.2932
0.500 0.6622 0.01829 0.00900 -0.1412 0.8445 0.3271
0.750 0.6891 0.01761 0.00899 -0.1410 0.8359 0.5053
1.250 0.7380 0.01677 0.00880 -0.1383 0.8220 1.0000
1.500 0.7684 0.01672 0.00868 -0.1384 0.8160 1.0000
1.750 0.7935 0.01686 0.00879 -0.1377 0.8075 1.0000
2.000 0.8238 0.01678 0.00869 -0.1377 0.8009 1.0000
2.250 0.8480 0.01691 0.00883 -0.1368 0.7909 1.0000
2.500 0.8766 0.01686 0.00877 -0.1365 0.7826 1.0000
2.750 0.9034 0.01684 0.00879 -0.1359 0.7724 1.0000
3.000 0.9280 0.01689 0.00888 -0.1349 0.7603 1.0000
3.250 0.9532 0.01691 0.00894 -0.1340 0.7475 1.0000
3.500 0.9783 0.01692 0.00900 -0.1331 0.7333 1.0000
3.750 1.0031 0.01693 0.00909 -0.1321 0.7171 1.0000
4.000 1.0285 0.01689 0.00910 -0.1312 0.6986 1.0000
4.250 1.0510 0.01696 0.00923 -0.1298 0.6738 1.0000
4.500 1.0762 0.01692 0.00921 -0.1287 0.6439 1.0000
4.750 1.1031 0.01687 0.00906 -0.1278 0.6076 1.0000
5.000 1.1293 0.01698 0.00898 -0.1268 0.5682 1.0000
5.250 1.1522 0.01739 0.00919 -0.1255 0.5278 1.0000
5.500 1.1722 0.01800 0.00957 -0.1238 0.4840 1.0000
5.750 1.1893 0.01877 0.01007 -0.1217 0.4367 1.0000
6.000 1.2049 0.01962 0.01063 -0.1195 0.3923 1.0000
6.250 1.2217 0.02042 0.01128 -0.1176 0.3582 1.0000
6.500 1.2393 0.02118 0.01194 -0.1159 0.3313 1.0000
6.750 1.2569 0.02190 0.01263 -0.1142 0.3052 1.0000
7.000 1.2735 0.02266 0.01335 -0.1124 0.2763 1.0000
7.250 1.2890 0.02348 0.01413 -0.1105 0.2438 1.0000
7.500 1.3026 0.02443 0.01495 -0.1083 0.2055 1.0000
7.750 1.3124 0.02569 0.01594 -0.1057 0.1600 1.0000
8.000 1.3198 0.02714 0.01711 -0.1028 0.1206 1.0000
8.250 1.3278 0.02854 0.01837 -0.0999 0.0981 1.0000
8.500 1.3367 0.02989 0.01971 -0.0972 0.0863 1.0000
8.750 1.3448 0.03131 0.02114 -0.0945 0.0790 1.0000
9.000 1.3535 0.03268 0.02264 -0.0920 0.0730 1.0000
9.250 1.3587 0.03433 0.02429 -0.0892 0.0684 1.0000
9.500 1.3679 0.03571 0.02584 -0.0869 0.0639 1.0000
9.750 1.3751 0.03727 0.02750 -0.0845 0.0603 1.0000
10.000 1.3796 0.03910 0.02939 -0.0820 0.0578 1.0000
10.250 1.3859 0.04092 0.03131 -0.0797 0.0558 1.0000
10.500 1.3953 0.04255 0.03312 -0.0777 0.0534 1.0000
10.750 1.4040 0.04426 0.03501 -0.0758 0.0508 1.0000
11.000 1.4114 0.04606 0.03690 -0.0740 0.0484 1.0000
11.250 1.4180 0.04807 0.03896 -0.0722 0.0464 1.0000
11.500 1.4284 0.05015 0.04112 -0.0705 0.0448 1.0000
11.750 1.4388 0.05213 0.04335 -0.0689 0.0434 1.0000
12.000 1.4473 0.05426 0.04574 -0.0672 0.0418 1.0000
12.250 1.4530 0.05652 0.04822 -0.0656 0.0401 1.0000
12.500 1.4565 0.05886 0.05073 -0.0640 0.0384 1.0000
12.750 1.4591 0.06129 0.05328 -0.0626 0.0370 1.0000
13.000 1.4628 0.06395 0.05608 -0.0612 0.0359 1.0000
13.250 1.4664 0.06723 0.05951 -0.0599 0.0349 1.0000
13.500 1.4612 0.07066 0.06329 -0.0585 0.0343 1.0000
13.750 1.4529 0.07447 0.06744 -0.0574 0.0335 1.0000
14.000 1.4421 0.07865 0.07193 -0.0566 0.0328 1.0000
14.250 1.4295 0.08317 0.07675 -0.0564 0.0320 1.0000
14.500 1.4153 0.08803 0.08189 -0.0567 0.0314 1.0000
14.750 1.3998 0.09338 0.08750 -0.0577 0.0308 1.0000
15.000 1.3830 0.09932 0.09371 -0.0595 0.0304 1.0000
15.250 1.3646 0.10597 0.10061 -0.0621 0.0301 1.0000
15.500 1.3441 0.11359 0.10847 -0.0659 0.0300 1.0000
15.750 1.3206 0.12255 0.11768 -0.0711 0.0300 1.0000
16.000 1.2904 0.13408 0.12947 -0.0787 0.0305 1.0000
16.250 1.2471 0.15083 0.14642 -0.0904 0.0318 1.0000
16.500 1.2003 0.17173 0.16741 -0.1047 0.0333 1.0000
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Polar data table (+)
Polar graphs
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