HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 200,000 Max Cl/Cd: 82.8 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1712-il-200000.txt Download as CSV file: xf-hs1712-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4249 0.09634 0.09318 -0.0285 0.9933 0.0564
-7.000 -0.4057 0.09189 0.08872 -0.0346 0.9877 0.0597
-6.750 -0.3803 0.08480 0.08158 -0.0458 0.9832 0.0622
-6.500 -0.3542 0.07855 0.07525 -0.0560 0.9761 0.0668
-6.250 -0.3269 0.07340 0.07004 -0.0621 0.9726 0.0690
-6.000 -0.2686 0.04011 0.03485 -0.0954 0.9719 0.0501
-5.750 -0.2316 0.03545 0.02966 -0.0995 0.9688 0.0498
-5.500 -0.1914 0.03136 0.02478 -0.1034 0.9660 0.0498
-5.250 -0.1521 0.02954 0.02273 -0.1065 0.9629 0.0513
-5.000 -0.1093 0.02818 0.02094 -0.1098 0.9606 0.0548
-4.750 -0.0663 0.02698 0.01962 -0.1132 0.9590 0.0575
-4.500 -0.0332 0.02605 0.01834 -0.1143 0.9529 0.0609
-4.250 0.0046 0.02523 0.01756 -0.1166 0.9493 0.0652
-4.000 0.0459 0.02437 0.01663 -0.1195 0.9470 0.0700
-3.750 0.0887 0.02372 0.01595 -0.1226 0.9452 0.0768
-3.500 0.1196 0.02325 0.01543 -0.1233 0.9379 0.0829
-3.250 0.1588 0.02264 0.01489 -0.1257 0.9339 0.0907
-3.000 0.2010 0.02202 0.01431 -0.1287 0.9314 0.0996
-2.750 0.2447 0.02145 0.01380 -0.1320 0.9296 0.1123
-2.500 0.2723 0.02103 0.01346 -0.1320 0.9206 0.1272
-2.250 0.3132 0.02046 0.01303 -0.1346 0.9173 0.1630
-2.000 0.3554 0.01998 0.01264 -0.1375 0.9148 0.1996
-1.750 0.3851 0.01973 0.01239 -0.1378 0.9067 0.2235
-1.500 0.4232 0.01918 0.01194 -0.1399 0.9020 0.2480
-1.250 0.4657 0.01850 0.01134 -0.1428 0.8993 0.2746
-1.000 0.5101 0.01770 0.01070 -0.1461 0.8975 0.3121
-0.750 0.5369 0.01720 0.01052 -0.1459 0.8869 0.3774
-0.500 0.5649 0.01543 0.01025 -0.1449 0.8844 0.8553
-0.250 0.6019 0.01439 0.00917 -0.1458 0.8812 1.0000
0.000 0.6273 0.01420 0.00889 -0.1449 0.8696 1.0000
0.250 0.6725 0.01357 0.00815 -0.1481 0.8656 1.0000
0.500 0.7026 0.01329 0.00780 -0.1482 0.8538 1.0000
0.750 0.7471 0.01272 0.00713 -0.1513 0.8473 1.0000
1.000 0.7813 0.01247 0.00680 -0.1523 0.8348 1.0000
1.250 0.8178 0.01224 0.00649 -0.1539 0.8218 1.0000
1.500 0.8543 0.01206 0.00622 -0.1555 0.8077 1.0000
1.750 0.8920 0.01193 0.00597 -0.1574 0.7933 1.0000
2.000 0.9263 0.01193 0.00585 -0.1585 0.7769 1.0000
2.250 0.9462 0.01210 0.00600 -0.1567 0.7517 1.0000
2.500 0.9800 0.01211 0.00582 -0.1577 0.7332 1.0000
2.750 1.0104 0.01229 0.00584 -0.1580 0.7135 1.0000
3.000 1.0377 0.01257 0.00599 -0.1578 0.6934 1.0000
3.250 1.0629 0.01285 0.00619 -0.1571 0.6725 1.0000
3.500 1.0872 0.01313 0.00638 -0.1563 0.6513 1.0000
3.750 1.1105 0.01342 0.00657 -0.1552 0.6287 1.0000
4.000 1.1316 0.01371 0.00679 -0.1537 0.6028 1.0000
4.250 1.1513 0.01407 0.00699 -0.1519 0.5731 1.0000
4.500 1.1696 0.01448 0.00728 -0.1498 0.5397 1.0000
4.750 1.1861 0.01497 0.00756 -0.1474 0.5039 1.0000
5.000 1.2020 0.01552 0.00792 -0.1450 0.4705 1.0000
5.250 1.2190 0.01609 0.00833 -0.1428 0.4437 1.0000
5.500 1.2370 0.01665 0.00877 -0.1409 0.4215 1.0000
5.750 1.2557 0.01719 0.00921 -0.1392 0.4036 1.0000
6.000 1.2746 0.01773 0.00967 -0.1376 0.3880 1.0000
6.250 1.2930 0.01830 0.01015 -0.1359 0.3738 1.0000
6.500 1.3109 0.01887 0.01065 -0.1341 0.3614 1.0000
6.750 1.3300 0.01943 0.01117 -0.1325 0.3507 1.0000
7.000 1.3500 0.02009 0.01174 -0.1312 0.3412 1.0000
7.250 1.3692 0.02059 0.01231 -0.1297 0.3310 1.0000
7.500 1.3879 0.02115 0.01288 -0.1281 0.3211 1.0000
7.750 1.4052 0.02167 0.01343 -0.1263 0.3110 1.0000
8.000 1.4228 0.02212 0.01398 -0.1245 0.3008 1.0000
8.250 1.4382 0.02269 0.01454 -0.1224 0.2909 1.0000
8.500 1.4545 0.02319 0.01511 -0.1204 0.2801 1.0000
8.750 1.4697 0.02379 0.01575 -0.1183 0.2698 1.0000
9.000 1.4835 0.02447 0.01644 -0.1161 0.2591 1.0000
9.250 1.4988 0.02511 0.01716 -0.1141 0.2477 1.0000
9.500 1.5117 0.02589 0.01795 -0.1118 0.2367 1.0000
9.750 1.5236 0.02673 0.01880 -0.1094 0.2246 1.0000
10.000 1.5360 0.02758 0.01970 -0.1071 0.2113 1.0000
10.250 1.5465 0.02858 0.02071 -0.1047 0.1975 1.0000
10.500 1.5552 0.02972 0.02183 -0.1020 0.1834 1.0000
10.750 1.5627 0.03100 0.02309 -0.0993 0.1705 1.0000
11.250 1.5768 0.03376 0.02585 -0.0941 0.1490 1.0000
11.500 1.5831 0.03528 0.02737 -0.0916 0.1415 1.0000
11.750 1.5904 0.03674 0.02887 -0.0892 0.1349 1.0000
12.000 1.5953 0.03843 0.03055 -0.0868 0.1299 1.0000
12.250 1.6045 0.03983 0.03207 -0.0849 0.1250 1.0000
12.500 1.6104 0.04150 0.03377 -0.0828 0.1210 1.0000
12.750 1.6155 0.04329 0.03558 -0.0806 0.1174 1.0000
13.000 1.6237 0.04484 0.03729 -0.0790 0.1133 1.0000
13.250 1.6288 0.04668 0.03919 -0.0772 0.1096 1.0000
13.500 1.6325 0.04872 0.04124 -0.0754 0.1063 1.0000
13.750 1.6388 0.05059 0.04328 -0.0739 0.1028 1.0000
14.000 1.6424 0.05271 0.04548 -0.0725 0.0994 1.0000
14.250 1.6441 0.05506 0.04783 -0.0709 0.0962 1.0000
14.500 1.6475 0.05737 0.05034 -0.0698 0.0927 1.0000
14.750 1.6482 0.05999 0.05303 -0.0686 0.0893 1.0000
15.000 1.6482 0.06278 0.05591 -0.0676 0.0858 1.0000
15.250 1.6475 0.06574 0.05901 -0.0668 0.0822 1.0000
15.500 1.6452 0.06884 0.06212 -0.0660 0.0790 1.0000
15.750 1.6425 0.07212 0.06550 -0.0653 0.0757 1.0000
16.000 1.6421 0.07492 0.06821 -0.0643 0.0725 1.0000
16.250 1.6369 0.07869 0.07218 -0.0640 0.0694 1.0000
16.500 1.6386 0.08126 0.07468 -0.0632 0.0664 1.0000
16.750 1.6297 0.08580 0.07952 -0.0636 0.0638 1.0000
17.000 1.6280 0.08913 0.08290 -0.0637 0.0614 1.0000
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Polar data table (+)
Polar graphs
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