HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 500,000 Max Cl/Cd: 139.47 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1708-il-500000.txt Download as CSV file: xf-hs1708-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2187 0.08416 0.08190 -0.0677 0.9738 0.0248
-8.000 -0.2071 0.07950 0.07724 -0.0750 0.9610 0.0259
-7.750 -0.2239 0.02042 0.01638 -0.1379 0.9338 0.0126
-7.500 -0.1961 0.01811 0.01366 -0.1394 0.9294 0.0127
-7.250 -0.1685 0.01658 0.01183 -0.1402 0.9239 0.0130
-7.000 -0.1404 0.01537 0.01038 -0.1407 0.9194 0.0135
-6.750 -0.1120 0.01440 0.00917 -0.1411 0.9156 0.0140
-6.500 -0.0836 0.01360 0.00818 -0.1414 0.9108 0.0147
-6.250 -0.0549 0.01265 0.00705 -0.1419 0.9065 0.0159
-6.000 -0.0262 0.01210 0.00639 -0.1421 0.9030 0.0178
-5.750 0.0029 0.01148 0.00566 -0.1425 0.8996 0.0217
-5.500 0.0317 0.01108 0.00525 -0.1428 0.8959 0.0303
-5.250 0.0604 0.01091 0.00503 -0.1429 0.8924 0.0371
-5.000 0.0889 0.01091 0.00499 -0.1430 0.8892 0.0422
-4.750 0.1176 0.01067 0.00469 -0.1432 0.8862 0.0469
-4.500 0.1464 0.01055 0.00454 -0.1435 0.8829 0.0514
-4.250 0.1752 0.01052 0.00444 -0.1436 0.8798 0.0550
-4.000 0.2041 0.01021 0.00414 -0.1439 0.8769 0.0617
-3.750 0.2329 0.01011 0.00397 -0.1441 0.8742 0.0664
-3.500 0.2618 0.00990 0.00374 -0.1443 0.8716 0.0726
-3.250 0.2906 0.00983 0.00366 -0.1445 0.8686 0.0793
-3.000 0.3192 0.00965 0.00350 -0.1447 0.8648 0.0875
-2.750 0.3476 0.00958 0.00336 -0.1447 0.8604 0.0944
-2.500 0.3759 0.00942 0.00322 -0.1447 0.8558 0.1050
-2.250 0.4042 0.00928 0.00311 -0.1447 0.8502 0.1162
-2.000 0.4326 0.00917 0.00300 -0.1446 0.8453 0.1283
-1.750 0.4611 0.00914 0.00296 -0.1447 0.8413 0.1414
-1.500 0.4895 0.00909 0.00293 -0.1448 0.8369 0.1539
-1.250 0.5180 0.00906 0.00290 -0.1448 0.8325 0.1652
-1.000 0.5465 0.00903 0.00286 -0.1448 0.8284 0.1760
-0.750 0.5747 0.00897 0.00285 -0.1448 0.8231 0.1870
-0.500 0.6031 0.00895 0.00281 -0.1448 0.8183 0.1975
-0.250 0.6317 0.00892 0.00280 -0.1449 0.8146 0.2080
0.000 0.6601 0.00888 0.00282 -0.1450 0.8103 0.2194
0.250 0.6886 0.00883 0.00281 -0.1451 0.8054 0.2310
0.500 0.7171 0.00878 0.00279 -0.1451 0.8009 0.2447
0.750 0.7453 0.00872 0.00280 -0.1451 0.7954 0.2614
1.000 0.7736 0.00862 0.00279 -0.1452 0.7896 0.2848
1.250 0.8024 0.00843 0.00281 -0.1454 0.7847 0.3591
1.500 0.8228 0.00712 0.00289 -0.1438 0.7785 1.0000
1.750 0.8510 0.00716 0.00288 -0.1437 0.7722 1.0000
2.000 0.8789 0.00719 0.00290 -0.1436 0.7643 1.0000
2.250 0.9067 0.00722 0.00288 -0.1434 0.7560 1.0000
2.500 0.9342 0.00723 0.00291 -0.1433 0.7453 1.0000
2.750 0.9617 0.00727 0.00294 -0.1431 0.7343 1.0000
3.000 0.9891 0.00732 0.00297 -0.1428 0.7215 1.0000
3.250 1.0160 0.00737 0.00302 -0.1425 0.7049 1.0000
3.500 1.0418 0.00747 0.00304 -0.1419 0.6742 1.0000
3.750 1.0632 0.00787 0.00309 -0.1404 0.6044 1.0000
4.000 1.0827 0.00856 0.00341 -0.1388 0.5383 1.0000
4.250 1.1032 0.00922 0.00377 -0.1374 0.4812 1.0000
4.500 1.1239 0.00986 0.00414 -0.1362 0.4256 1.0000
4.750 1.1456 0.01041 0.00449 -0.1351 0.3869 1.0000
5.000 1.1682 0.01090 0.00484 -0.1343 0.3583 1.0000
5.250 1.1910 0.01135 0.00518 -0.1334 0.3344 1.0000
5.500 1.2144 0.01174 0.00550 -0.1327 0.3147 1.0000
5.750 1.2377 0.01213 0.00584 -0.1319 0.2945 1.0000
6.000 1.2603 0.01256 0.00619 -0.1310 0.2726 1.0000
6.250 1.2820 0.01305 0.00656 -0.1301 0.2441 1.0000
6.500 1.3016 0.01371 0.00702 -0.1287 0.2041 1.0000
6.750 1.3175 0.01467 0.00766 -0.1268 0.1503 1.0000
7.000 1.3297 0.01594 0.00854 -0.1244 0.0912 1.0000
7.250 1.3455 0.01689 0.00933 -0.1224 0.0683 1.0000
7.500 1.3631 0.01763 0.01003 -0.1207 0.0591 1.0000
7.750 1.3816 0.01824 0.01068 -0.1191 0.0539 1.0000
8.000 1.3989 0.01890 0.01137 -0.1173 0.0496 1.0000
8.250 1.4103 0.01993 0.01244 -0.1145 0.0453 1.0000
8.500 1.4268 0.02045 0.01304 -0.1125 0.0438 1.0000
8.750 1.4419 0.02110 0.01376 -0.1104 0.0418 1.0000
9.000 1.4565 0.02180 0.01451 -0.1083 0.0397 1.0000
9.250 1.4681 0.02273 0.01548 -0.1058 0.0375 1.0000
9.500 1.4707 0.02436 0.01720 -0.1020 0.0352 1.0000
9.750 1.4844 0.02519 0.01813 -0.1000 0.0344 1.0000
10.000 1.4981 0.02604 0.01907 -0.0981 0.0334 1.0000
10.250 1.5103 0.02702 0.02015 -0.0960 0.0322 1.0000
10.500 1.5223 0.02803 0.02123 -0.0940 0.0309 1.0000
10.750 1.5339 0.02907 0.02233 -0.0921 0.0296 1.0000
11.000 1.5431 0.03033 0.02365 -0.0900 0.0284 1.0000
11.250 1.5442 0.03238 0.02578 -0.0870 0.0270 1.0000
11.500 1.5472 0.03436 0.02789 -0.0843 0.0260 1.0000
11.750 1.5616 0.03518 0.02881 -0.0831 0.0252 1.0000
12.000 1.5734 0.03628 0.03001 -0.0817 0.0241 1.0000
12.250 1.5844 0.03745 0.03127 -0.0803 0.0229 1.0000
12.500 1.5944 0.03873 0.03261 -0.0789 0.0219 1.0000
12.750 1.6022 0.04024 0.03418 -0.0774 0.0210 1.0000
13.000 1.6030 0.04250 0.03651 -0.0754 0.0201 1.0000
13.250 1.5927 0.04600 0.04017 -0.0725 0.0191 1.0000
13.500 1.6016 0.04750 0.04178 -0.0715 0.0187 1.0000
13.750 1.6083 0.04929 0.04370 -0.0704 0.0181 1.0000
14.000 1.6133 0.05128 0.04582 -0.0693 0.0173 1.0000
14.250 1.6180 0.05337 0.04802 -0.0684 0.0165 1.0000
14.500 1.6227 0.05550 0.05024 -0.0677 0.0157 1.0000
14.750 1.6262 0.05786 0.05266 -0.0672 0.0150 1.0000
15.000 1.6213 0.06132 0.05620 -0.0665 0.0143 1.0000
15.250 1.6050 0.06633 0.06136 -0.0656 0.0136 1.0000
15.500 1.6092 0.06900 0.06418 -0.0657 0.0131 1.0000
15.750 1.6098 0.07223 0.06755 -0.0659 0.0125 1.0000
16.000 1.6085 0.07583 0.07127 -0.0664 0.0119 1.0000
16.250 1.6061 0.07974 0.07529 -0.0671 0.0113 1.0000
16.500 1.6017 0.08408 0.07973 -0.0682 0.0109 1.0000
16.750 1.5947 0.08895 0.08471 -0.0696 0.0105 1.0000
17.000 1.5811 0.09493 0.09081 -0.0714 0.0101 1.0000
17.250 1.5633 0.10172 0.09775 -0.0736 0.0098 1.0000
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