HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 200,000 Max Cl/Cd: 97.27 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1708-il-200000.txt Download as CSV file: xf-hs1708-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3325 0.11462 0.11118 -0.0322 1.0000 0.0398
-9.250 -0.3470 0.11411 0.11074 -0.0284 1.0000 0.0403
-9.000 -0.3598 0.11331 0.11000 -0.0254 1.0000 0.0409
-8.750 -0.3567 0.11070 0.10742 -0.0282 0.9979 0.0424
-8.500 -0.3503 0.10799 0.10472 -0.0365 0.9930 0.0433
-8.250 -0.3413 0.10465 0.10140 -0.0426 0.9875 0.0436
-8.000 -0.3236 0.10019 0.09693 -0.0497 0.9829 0.0437
-7.750 -0.3165 0.09432 0.09108 -0.0499 0.9797 0.0444
-7.500 -0.3006 0.09077 0.08752 -0.0493 0.9775 0.0453
-7.250 -0.2811 0.08720 0.08395 -0.0521 0.9748 0.0465
-7.000 -0.2590 0.08337 0.08010 -0.0572 0.9724 0.0481
-6.750 -0.2498 0.08039 0.07712 -0.0598 0.9658 0.0497
-6.500 -0.2240 0.07571 0.07240 -0.0691 0.9615 0.0529
-6.250 -0.1773 0.06860 0.06513 -0.0891 0.9562 0.0549
-6.000 -0.1657 0.06280 0.05932 -0.0922 0.9511 0.0558
-5.750 -0.1105 0.03406 0.02953 -0.1193 0.9486 0.0340
-5.500 -0.0692 0.02624 0.02082 -0.1272 0.9477 0.0364
-5.250 -0.0304 0.02375 0.01773 -0.1304 0.9466 0.0425
-5.000 0.0065 0.02273 0.01653 -0.1328 0.9454 0.0509
-4.750 0.0382 0.02172 0.01522 -0.1342 0.9431 0.0587
-4.500 0.0573 0.02233 0.01578 -0.1327 0.9379 0.0665
-4.250 0.0889 0.02186 0.01530 -0.1340 0.9356 0.0742
-4.000 0.1256 0.02105 0.01405 -0.1358 0.9339 0.0807
-3.750 0.1617 0.01997 0.01292 -0.1379 0.9328 0.0871
-3.500 0.1993 0.01938 0.01205 -0.1399 0.9316 0.0941
-3.250 0.2371 0.01879 0.01147 -0.1422 0.9306 0.1028
-3.000 0.2536 0.01880 0.01130 -0.1400 0.9242 0.1085
-2.750 0.2895 0.01834 0.01088 -0.1417 0.9214 0.1184
-2.500 0.3292 0.01783 0.01035 -0.1441 0.9194 0.1293
-2.250 0.3677 0.01740 0.00989 -0.1461 0.9176 0.1419
-2.000 0.4054 0.01709 0.00957 -0.1480 0.9160 0.1564
-1.750 0.4228 0.01732 0.00977 -0.1461 0.9092 0.1676
-1.500 0.4562 0.01711 0.00958 -0.1472 0.9061 0.1831
-1.250 0.4941 0.01670 0.00921 -0.1489 0.9034 0.2004
-1.000 0.5259 0.01641 0.00895 -0.1495 0.8985 0.2156
-0.750 0.5552 0.01615 0.00873 -0.1495 0.8922 0.2313
-0.500 0.5910 0.01566 0.00828 -0.1506 0.8885 0.2487
-0.250 0.6182 0.01547 0.00815 -0.1502 0.8818 0.2649
0.000 0.6486 0.01514 0.00789 -0.1503 0.8762 0.2838
0.250 0.6814 0.01469 0.00758 -0.1509 0.8728 0.3070
0.500 0.7057 0.01464 0.00770 -0.1503 0.8657 0.3366
0.750 0.7271 0.01304 0.00762 -0.1484 0.8609 1.0000
1.000 0.7585 0.01293 0.00736 -0.1485 0.8567 1.0000
1.250 0.7830 0.01308 0.00746 -0.1477 0.8486 1.0000
1.500 0.8139 0.01290 0.00721 -0.1477 0.8437 1.0000
1.750 0.8389 0.01299 0.00730 -0.1469 0.8352 1.0000
2.000 0.8693 0.01279 0.00705 -0.1467 0.8293 1.0000
2.250 0.8944 0.01284 0.00711 -0.1459 0.8200 1.0000
2.500 0.9241 0.01268 0.00693 -0.1456 0.8134 1.0000
2.750 0.9496 0.01267 0.00695 -0.1448 0.8031 1.0000
3.000 0.9760 0.01260 0.00689 -0.1440 0.7928 1.0000
3.250 1.0036 0.01243 0.00672 -0.1434 0.7823 1.0000
3.500 1.0313 0.01225 0.00655 -0.1427 0.7706 1.0000
3.750 1.0569 0.01214 0.00648 -0.1418 0.7563 1.0000
4.000 1.0820 0.01206 0.00643 -0.1408 0.7397 1.0000
4.250 1.1064 0.01198 0.00641 -0.1396 0.7179 1.0000
4.500 1.1304 0.01185 0.00625 -0.1382 0.6856 1.0000
4.750 1.1526 0.01185 0.00607 -0.1364 0.6316 1.0000
5.000 1.1716 0.01232 0.00610 -0.1341 0.5629 1.0000
5.250 1.1887 0.01310 0.00650 -0.1319 0.5044 1.0000
5.500 1.2066 0.01383 0.00698 -0.1300 0.4580 1.0000
6.000 1.2435 0.01520 0.00803 -0.1267 0.3907 1.0000
6.250 1.2622 0.01587 0.00858 -0.1251 0.3634 1.0000
6.500 1.2808 0.01651 0.00915 -0.1235 0.3366 1.0000
6.750 1.2990 0.01714 0.00972 -0.1218 0.3095 1.0000
7.000 1.3164 0.01780 0.01033 -0.1201 0.2791 1.0000
7.250 1.3306 0.01862 0.01098 -0.1178 0.2334 1.0000
7.500 1.3354 0.02018 0.01201 -0.1142 0.1532 1.0000
7.750 1.3384 0.02197 0.01336 -0.1104 0.1053 1.0000
8.000 1.3456 0.02324 0.01455 -0.1070 0.0897 1.0000
8.250 1.3515 0.02466 0.01590 -0.1035 0.0811 1.0000
8.500 1.3631 0.02573 0.01707 -0.1010 0.0753 1.0000
8.750 1.3703 0.02718 0.01852 -0.0980 0.0705 1.0000
9.000 1.3801 0.02856 0.01998 -0.0954 0.0667 1.0000
9.250 1.3922 0.02974 0.02125 -0.0932 0.0629 1.0000
9.500 1.4030 0.03113 0.02267 -0.0910 0.0598 1.0000
9.750 1.4154 0.03330 0.02478 -0.0890 0.0567 1.0000
10.000 1.4309 0.03446 0.02611 -0.0872 0.0550 1.0000
10.250 1.4459 0.03578 0.02759 -0.0856 0.0526 1.0000
10.500 1.4598 0.03715 0.02907 -0.0838 0.0501 1.0000
10.750 1.4743 0.03869 0.03064 -0.0823 0.0479 1.0000
11.000 1.5072 0.04198 0.03402 -0.0832 0.0451 1.0000
11.250 1.5159 0.04341 0.03569 -0.0807 0.0441 1.0000
11.500 1.5240 0.04506 0.03758 -0.0784 0.0426 1.0000
11.750 1.5313 0.04688 0.03961 -0.0761 0.0409 1.0000
12.000 1.5386 0.04887 0.04179 -0.0740 0.0394 1.0000
12.250 1.5429 0.05084 0.04393 -0.0718 0.0380 1.0000
12.500 1.5499 0.05318 0.04633 -0.0701 0.0364 1.0000
12.750 1.5487 0.05835 0.05181 -0.0680 0.0348 1.0000
13.000 1.5392 0.06059 0.05433 -0.0649 0.0343 1.0000
13.250 1.5291 0.06347 0.05750 -0.0623 0.0337 1.0000
13.500 1.5175 0.06679 0.06110 -0.0601 0.0329 1.0000
13.750 1.5045 0.07045 0.06503 -0.0583 0.0321 1.0000
14.000 1.4906 0.07436 0.06919 -0.0570 0.0314 1.0000
14.250 1.4765 0.07854 0.07359 -0.0562 0.0307 1.0000
14.500 1.4633 0.08274 0.07798 -0.0559 0.0300 1.0000
14.750 1.4495 0.08727 0.08268 -0.0560 0.0294 1.0000
15.000 1.4364 0.09192 0.08749 -0.0567 0.0288 1.0000
15.250 1.4167 0.09805 0.09384 -0.0584 0.0286 1.0000
15.500 1.3951 0.10501 0.10102 -0.0611 0.0285 1.0000
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