HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il) Reynolds number: 200,000 Max Cl/Cd: 31.02 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1430-il-200000.txt Download as CSV file: xf-hs1430-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-430 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.3787 0.21132 0.20660 -0.0249 1.0000 0.1332
-17.500 -0.3733 0.20981 0.20511 -0.0248 1.0000 0.1353
-16.750 -1.1777 0.07474 0.06806 -0.0682 1.0000 0.1504
-16.500 -1.1509 0.07511 0.06858 -0.0676 1.0000 0.1516
-16.250 -1.1254 0.07586 0.06946 -0.0666 1.0000 0.1526
-16.000 -1.1264 0.07432 0.06793 -0.0652 0.9998 0.1537
-15.750 -1.1204 0.07151 0.06505 -0.0669 0.9970 0.1553
-15.500 -1.1374 0.06727 0.06062 -0.0671 0.9939 0.1569
-15.250 -1.1641 0.06279 0.05584 -0.0661 0.9910 0.1587
-15.000 -1.1994 0.05853 0.05123 -0.0623 0.9859 0.1603
-14.750 -1.2346 0.05509 0.04740 -0.0570 0.9804 0.1617
-14.500 -1.1909 0.05452 0.04696 -0.0606 0.9780 0.1635
-14.250 -1.1526 0.05440 0.04694 -0.0635 0.9762 0.1650
-14.000 -1.1421 0.05349 0.04603 -0.0619 0.9697 0.1663
-13.750 -1.1304 0.05245 0.04493 -0.0610 0.9654 0.1679
-13.500 -1.1229 0.05113 0.04346 -0.0596 0.9626 0.1699
-13.250 -1.1378 0.04961 0.04176 -0.0538 0.9545 0.1714
-13.000 -1.1503 0.04793 0.03976 -0.0484 0.9500 0.1732
-12.750 -1.1066 0.04734 0.03928 -0.0521 0.9485 0.1750
-12.500 -1.0914 0.04691 0.03890 -0.0502 0.9402 0.1762
-12.250 -1.0597 0.04646 0.03849 -0.0516 0.9376 0.1779
-12.000 -1.0454 0.04587 0.03786 -0.0499 0.9315 0.1797
-11.750 -1.0280 0.04495 0.03684 -0.0488 0.9271 0.1819
-11.500 -1.0110 0.04364 0.03528 -0.0479 0.9247 0.1845
-11.250 -0.9996 0.04276 0.03432 -0.0454 0.9169 0.1861
-11.000 -0.9602 0.04227 0.03396 -0.0481 0.9150 0.1878
-10.750 -0.9401 0.04189 0.03361 -0.0470 0.9086 0.1895
-10.500 -0.9121 0.04129 0.03299 -0.0475 0.9051 0.1917
-10.250 -0.8811 0.04048 0.03210 -0.0487 0.9033 0.1944
-10.000 -0.8742 0.03978 0.03126 -0.0451 0.8943 0.1965
-9.750 -0.8467 0.03872 0.03002 -0.0455 0.8923 0.1988
-9.500 -0.8270 0.03809 0.02948 -0.0443 0.8840 0.2005
-9.250 -0.7914 0.03751 0.02898 -0.0462 0.8816 0.2027
-9.000 -0.7565 0.03686 0.02834 -0.0479 0.8799 0.2052
-8.750 -0.7452 0.03650 0.02794 -0.0449 0.8707 0.2072
-8.500 -0.7145 0.03572 0.02707 -0.0457 0.8678 0.2099
-8.250 -0.6832 0.03495 0.02614 -0.0466 0.8660 0.2123
-8.000 -0.6680 0.03425 0.02545 -0.0445 0.8574 0.2145
-7.750 -0.6336 0.03353 0.02482 -0.0461 0.8542 0.2169
-7.500 -0.5974 0.03282 0.02416 -0.0479 0.8521 0.2194
-7.250 -0.5610 0.03205 0.02337 -0.0497 0.8506 0.2222
-7.000 -0.5462 0.03177 0.02305 -0.0472 0.8423 0.2245
-6.750 -0.5174 0.03116 0.02235 -0.0475 0.8383 0.2272
-6.500 -0.4827 0.03040 0.02148 -0.0488 0.8359 0.2297
-6.250 -0.4397 0.02913 0.02031 -0.0522 0.8344 0.2331
-6.000 -0.3964 0.02831 0.01956 -0.0554 0.8330 0.2362
-5.750 -0.3846 0.02822 0.01947 -0.0523 0.8231 0.2385
-5.500 -0.3471 0.02753 0.01876 -0.0542 0.8195 0.2419
-5.250 -0.3031 0.02674 0.01790 -0.0575 0.8167 0.2454
-5.000 -0.2531 0.02600 0.01705 -0.0620 0.8143 0.2484
-4.750 -0.2332 0.02529 0.01640 -0.0606 0.8041 0.2520
-4.500 -0.1872 0.02448 0.01564 -0.0644 0.7983 0.2559
-4.250 -0.1248 0.02364 0.01479 -0.0717 0.7943 0.2605
-4.000 -0.1061 0.02345 0.01458 -0.0698 0.7848 0.2637
-3.750 -0.0666 0.02306 0.01411 -0.0724 0.7773 0.2678
-3.500 -0.0074 0.02232 0.01329 -0.0792 0.7716 0.2728
-3.250 0.0077 0.02205 0.01311 -0.0766 0.7612 0.2766
-3.000 0.0436 0.02167 0.01272 -0.0784 0.7525 0.2811
-2.750 0.0836 0.02134 0.01235 -0.0811 0.7444 0.2863
-2.500 0.0947 0.02132 0.01232 -0.0776 0.7336 0.2900
-2.250 0.1322 0.02110 0.01196 -0.0796 0.7238 0.2943
-2.000 0.1500 0.02085 0.01177 -0.0776 0.7137 0.2989
-1.750 0.1696 0.02063 0.01162 -0.0759 0.7038 0.3038
-1.500 0.2063 0.02037 0.01131 -0.0779 0.6950 0.3098
-1.250 0.2094 0.02038 0.01138 -0.0727 0.6853 0.3138
-1.000 0.2272 0.02031 0.01126 -0.0705 0.6746 0.3184
-0.750 0.2486 0.02020 0.01111 -0.0692 0.6643 0.3231
-0.500 0.2542 0.02011 0.01112 -0.0646 0.6527 0.3287
-0.250 0.2758 0.01994 0.01094 -0.0633 0.6405 0.3359
0.000 0.2813 0.02003 0.01109 -0.0587 0.6268 0.3424
0.250 0.2960 0.02005 0.01106 -0.0560 0.6114 0.3508
0.500 0.3037 0.02004 0.01114 -0.0519 0.5925 0.3634
0.750 0.3112 0.02011 0.01125 -0.0479 0.5691 0.3805
1.000 0.3136 0.02016 0.01136 -0.0429 0.5373 0.4131
1.250 0.3078 0.02016 0.01161 -0.0364 0.4974 0.4925
1.500 0.2969 0.02034 0.01221 -0.0288 0.4584 0.6303
1.750 0.2922 0.02106 0.01295 -0.0225 0.4192 0.6968
2.000 0.2941 0.02180 0.01367 -0.0177 0.3877 0.7418
2.250 0.3020 0.02257 0.01448 -0.0139 0.3662 0.7814
2.500 0.3164 0.02345 0.01541 -0.0114 0.3520 0.8192
2.750 0.3379 0.02433 0.01630 -0.0102 0.3428 0.8527
3.000 0.3603 0.02521 0.01714 -0.0093 0.3359 0.8782
3.250 0.3839 0.02617 0.01800 -0.0088 0.3306 0.8977
3.500 0.4118 0.02697 0.01877 -0.0090 0.3266 0.9143
3.750 0.4376 0.02775 0.01949 -0.0088 0.3230 0.9306
4.000 0.4777 0.02880 0.02048 -0.0116 0.3194 0.9401
4.250 0.5166 0.02985 0.02144 -0.0142 0.3164 0.9515
4.500 0.5680 0.03090 0.02237 -0.0195 0.3136 0.9555
4.750 0.6130 0.03167 0.02302 -0.0236 0.3112 0.9604
5.000 0.6488 0.03237 0.02367 -0.0256 0.3097 0.9696
5.250 0.6947 0.03296 0.02423 -0.0300 0.3081 0.9721
5.500 0.7390 0.03352 0.02475 -0.0340 0.3064 0.9754
5.750 0.7831 0.03410 0.02529 -0.0380 0.3049 0.9798
6.000 0.8246 0.03471 0.02586 -0.0415 0.3033 0.9855
6.250 0.8646 0.03521 0.02632 -0.0447 0.3017 0.9893
6.500 0.9067 0.03562 0.02668 -0.0485 0.3001 0.9921
6.750 0.9502 0.03606 0.02708 -0.0524 0.2986 0.9956
7.000 0.9935 0.03651 0.02746 -0.0563 0.2971 0.9990
7.250 1.0204 0.03668 0.02756 -0.0570 0.2957 1.0000
7.500 1.0408 0.03669 0.02747 -0.0563 0.2945 1.0000
7.750 1.0608 0.03676 0.02749 -0.0555 0.2934 1.0000
8.000 1.0718 0.03698 0.02773 -0.0531 0.2927 1.0000
8.250 1.0840 0.03723 0.02800 -0.0509 0.2919 1.0000
8.500 1.0967 0.03751 0.02829 -0.0489 0.2910 1.0000
8.750 1.1094 0.03782 0.02863 -0.0468 0.2900 1.0000
9.000 1.1224 0.03816 0.02898 -0.0448 0.2888 1.0000
9.250 1.1356 0.03852 0.02935 -0.0428 0.2876 1.0000
9.500 1.1486 0.03890 0.02973 -0.0408 0.2861 1.0000
9.750 1.1614 0.03928 0.03011 -0.0388 0.2843 1.0000
10.000 1.1778 0.03963 0.03042 -0.0374 0.2828 1.0000
10.250 1.1973 0.03993 0.03068 -0.0366 0.2812 1.0000
10.500 1.2238 0.04016 0.03082 -0.0368 0.2796 1.0000
10.750 1.2554 0.04047 0.03105 -0.0380 0.2778 1.0000
11.000 1.2571 0.04115 0.03183 -0.0343 0.2766 1.0000
11.250 1.2600 0.04187 0.03264 -0.0309 0.2751 1.0000
11.500 1.2654 0.04259 0.03342 -0.0280 0.2734 1.0000
11.750 1.2737 0.04326 0.03413 -0.0256 0.2716 1.0000
12.000 1.2854 0.04386 0.03475 -0.0237 0.2698 1.0000
12.250 1.3018 0.04435 0.03521 -0.0226 0.2680 1.0000
12.500 1.3262 0.04465 0.03543 -0.0226 0.2662 1.0000
12.750 1.3676 0.04483 0.03546 -0.0252 0.2639 1.0000
13.000 1.3564 0.04606 0.03686 -0.0202 0.2623 1.0000
13.250 1.3512 0.04727 0.03820 -0.0162 0.2603 1.0000
13.500 1.3519 0.04839 0.03940 -0.0132 0.2582 1.0000
13.750 1.3610 0.04925 0.04028 -0.0114 0.2561 1.0000
14.000 1.3811 0.04973 0.04071 -0.0110 0.2541 1.0000
14.250 1.4204 0.04973 0.04055 -0.0131 0.2522 1.0000
14.500 1.4220 0.05112 0.04204 -0.0105 0.2503 1.0000
14.750 1.4078 0.05308 0.04419 -0.0062 0.2482 1.0000
15.000 1.4046 0.05473 0.04595 -0.0035 0.2461 1.0000
15.250 1.4122 0.05593 0.04718 -0.0020 0.2441 1.0000
15.500 1.4328 0.05652 0.04772 -0.0019 0.2423 1.0000
15.750 1.4785 0.05615 0.04717 -0.0046 0.2405 1.0000
16.000 1.4558 0.05902 0.05028 -0.0003 0.2387 1.0000
16.250 1.4317 0.06221 0.05369 0.0037 0.2367 1.0000
16.500 1.4264 0.06444 0.05604 0.0057 0.2347 1.0000
16.750 1.4370 0.06571 0.05733 0.0064 0.2329 1.0000
17.000 1.4640 0.06593 0.05747 0.0057 0.2314 1.0000
17.250 1.5011 0.06577 0.05719 0.0041 0.2299 1.0000
17.500 1.4241 0.07313 0.06503 0.0108 0.2277 1.0000
17.750 1.3896 0.07817 0.07031 0.0135 0.2255 1.0000
18.000 1.3955 0.08000 0.07216 0.0138 0.2238 1.0000
18.250 1.4266 0.07969 0.07178 0.0130 0.2224 1.0000
18.500 1.4786 0.07787 0.06977 0.0110 0.2213 1.0000
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