HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 200,000 Max Cl/Cd: 74.65 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1712-il-200000-n5.txt Download as CSV file: xf-hs1712-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3432 0.09232 0.08858 -0.0592 0.9806 0.0222
-8.750 -0.3488 0.08706 0.08334 -0.0621 0.9754 0.0222
-8.250 -0.3870 0.03582 0.03062 -0.1117 0.9604 0.0227
-8.000 -0.3553 0.03383 0.02839 -0.1147 0.9591 0.0233
-7.750 -0.3281 0.03133 0.02548 -0.1167 0.9566 0.0245
-7.500 -0.3033 0.02849 0.02204 -0.1180 0.9530 0.0258
-7.250 -0.2733 0.02770 0.02117 -0.1192 0.9503 0.0266
-7.000 -0.2410 0.02638 0.01959 -0.1209 0.9483 0.0276
-6.750 -0.2069 0.02476 0.01754 -0.1229 0.9469 0.0290
-6.500 -0.1717 0.02400 0.01669 -0.1249 0.9454 0.0302
-6.250 -0.1346 0.02311 0.01553 -0.1272 0.9442 0.0325
-6.000 -0.1140 0.02252 0.01486 -0.1260 0.9375 0.0339
-5.750 -0.0816 0.02176 0.01394 -0.1271 0.9347 0.0359
-5.500 -0.0474 0.02098 0.01305 -0.1287 0.9327 0.0380
-5.250 -0.0119 0.02029 0.01220 -0.1305 0.9311 0.0411
-5.000 0.0242 0.01952 0.01150 -0.1326 0.9298 0.0438
-4.750 0.0486 0.01907 0.01104 -0.1320 0.9239 0.0462
-4.500 0.0790 0.01866 0.01063 -0.1327 0.9198 0.0495
-4.250 0.1133 0.01824 0.01021 -0.1342 0.9171 0.0533
-4.000 0.1492 0.01781 0.00975 -0.1359 0.9152 0.0576
-3.750 0.1860 0.01737 0.00928 -0.1379 0.9136 0.0627
-3.500 0.2061 0.01725 0.00915 -0.1363 0.9049 0.0670
-3.250 0.2399 0.01684 0.00877 -0.1375 0.9011 0.0743
-3.000 0.2764 0.01636 0.00832 -0.1393 0.8984 0.0842
-2.750 0.3013 0.01613 0.00815 -0.1387 0.8902 0.0953
-2.500 0.3333 0.01577 0.00786 -0.1395 0.8853 0.1145
-2.250 0.3690 0.01539 0.00754 -0.1411 0.8821 0.1365
-2.000 0.3946 0.01527 0.00748 -0.1406 0.8735 0.1553
-1.750 0.4282 0.01498 0.00722 -0.1417 0.8676 0.1754
-1.500 0.4623 0.01470 0.00696 -0.1429 0.8609 0.1926
-1.250 0.4959 0.01441 0.00668 -0.1440 0.8517 0.2095
-1.000 0.5341 0.01406 0.00635 -0.1461 0.8432 0.2302
-0.750 0.5763 0.01365 0.00599 -0.1492 0.8347 0.2550
-0.500 0.6160 0.01328 0.00568 -0.1517 0.8230 0.2869
-0.250 0.6568 0.01279 0.00542 -0.1546 0.8079 0.3660
0.000 0.6952 0.01176 0.00533 -0.1570 0.7935 0.7097
0.250 0.7114 0.01122 0.00511 -0.1532 0.7770 0.9196
0.500 0.7346 0.01112 0.00493 -0.1519 0.7433 1.0000
0.750 0.7697 0.01119 0.00472 -0.1533 0.7230 1.0000
1.000 0.7996 0.01139 0.00470 -0.1536 0.7050 1.0000
1.250 0.8273 0.01160 0.00478 -0.1535 0.6878 1.0000
1.500 0.8545 0.01182 0.00488 -0.1534 0.6708 1.0000
1.750 0.8812 0.01205 0.00500 -0.1531 0.6532 1.0000
2.000 0.9072 0.01229 0.00513 -0.1527 0.6347 1.0000
2.250 0.9323 0.01254 0.00527 -0.1521 0.6151 1.0000
2.500 0.9563 0.01281 0.00542 -0.1513 0.5927 1.0000
2.750 0.9793 0.01312 0.00559 -0.1502 0.5682 1.0000
3.000 1.0020 0.01343 0.00579 -0.1492 0.5422 1.0000
3.250 1.0221 0.01384 0.00600 -0.1476 0.5079 1.0000
3.500 1.0414 0.01429 0.00626 -0.1458 0.4734 1.0000
3.750 1.0601 0.01478 0.00658 -0.1440 0.4418 1.0000
4.000 1.0789 0.01529 0.00691 -0.1423 0.4136 1.0000
4.250 1.0985 0.01577 0.00726 -0.1407 0.3897 1.0000
4.500 1.1178 0.01627 0.00762 -0.1391 0.3698 1.0000
4.750 1.1370 0.01677 0.00802 -0.1375 0.3560 1.0000
5.000 1.1565 0.01727 0.00843 -0.1360 0.3456 1.0000
5.250 1.1774 0.01768 0.00882 -0.1347 0.3364 1.0000
5.500 1.1970 0.01813 0.00924 -0.1332 0.3277 1.0000
5.750 1.2185 0.01848 0.00963 -0.1321 0.3194 1.0000
6.000 1.2389 0.01889 0.01005 -0.1308 0.3106 1.0000
6.250 1.2601 0.01926 0.01045 -0.1296 0.3012 1.0000
6.500 1.2792 0.01972 0.01090 -0.1281 0.2907 1.0000
6.750 1.2991 0.02016 0.01134 -0.1267 0.2801 1.0000
7.000 1.3181 0.02063 0.01182 -0.1252 0.2713 1.0000
7.250 1.3374 0.02111 0.01231 -0.1238 0.2621 1.0000
7.500 1.3558 0.02163 0.01285 -0.1223 0.2524 1.0000
7.750 1.3731 0.02221 0.01341 -0.1205 0.2411 1.0000
8.000 1.3913 0.02275 0.01398 -0.1190 0.2308 1.0000
8.250 1.4078 0.02339 0.01462 -0.1172 0.2200 1.0000
8.500 1.4238 0.02406 0.01529 -0.1154 0.2081 1.0000
8.750 1.4400 0.02474 0.01598 -0.1137 0.1970 1.0000
9.000 1.4550 0.02549 0.01674 -0.1118 0.1863 1.0000
9.250 1.4691 0.02631 0.01755 -0.1098 0.1755 1.0000
9.500 1.4839 0.02710 0.01837 -0.1079 0.1653 1.0000
9.750 1.4973 0.02799 0.01927 -0.1059 0.1556 1.0000
10.000 1.5095 0.02897 0.02026 -0.1038 0.1455 1.0000
10.250 1.5220 0.02995 0.02127 -0.1018 0.1356 1.0000
10.500 1.5329 0.03105 0.02238 -0.0996 0.1262 1.0000
10.750 1.5428 0.03224 0.02357 -0.0974 0.1180 1.0000
11.000 1.5537 0.03338 0.02477 -0.0954 0.1107 1.0000
11.250 1.5631 0.03465 0.02608 -0.0933 0.1054 1.0000
11.500 1.5726 0.03592 0.02742 -0.0912 0.1007 1.0000
11.750 1.5801 0.03737 0.02892 -0.0891 0.0968 1.0000
12.000 1.5895 0.03871 0.03037 -0.0872 0.0932 1.0000
12.250 1.5969 0.04024 0.03197 -0.0852 0.0898 1.0000
12.500 1.6033 0.04189 0.03370 -0.0833 0.0869 1.0000
12.750 1.6107 0.04349 0.03541 -0.0816 0.0840 1.0000
13.000 1.6161 0.04532 0.03733 -0.0798 0.0813 1.0000
13.250 1.6198 0.04737 0.03945 -0.0781 0.0789 1.0000
13.500 1.6228 0.04955 0.04173 -0.0765 0.0769 1.0000
13.750 1.6233 0.05206 0.04430 -0.0749 0.0748 1.0000
14.000 1.6212 0.05492 0.04720 -0.0734 0.0729 1.0000
14.250 1.6247 0.05728 0.04973 -0.0723 0.0707 1.0000
14.500 1.6252 0.06006 0.05264 -0.0713 0.0687 1.0000
14.750 1.6218 0.06335 0.05602 -0.0704 0.0669 1.0000
15.000 1.6266 0.06578 0.05865 -0.0699 0.0644 1.0000
15.250 1.6280 0.06866 0.06170 -0.0694 0.0619 1.0000
15.500 1.6279 0.07176 0.06494 -0.0690 0.0597 1.0000
15.750 1.6271 0.07505 0.06836 -0.0688 0.0575 1.0000
16.000 1.6231 0.07884 0.07225 -0.0689 0.0558 1.0000
16.250 1.6192 0.08269 0.07623 -0.0690 0.0540 1.0000
16.500 1.6138 0.08683 0.08051 -0.0695 0.0522 1.0000
16.750 1.6056 0.09146 0.08523 -0.0702 0.0507 1.0000
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