S9037 (9%) (s9037-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S9037 (9%) (s9037-il) Reynolds number: 500,000 Max Cl/Cd: 104.81 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9037-il-500000.txt Download as CSV file: xf-s9037-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S9037 (9%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3451 0.08765 0.08548 -0.0355 1.0000 0.0147
-8.250 -0.3429 0.08531 0.08317 -0.0351 1.0000 0.0150
-8.000 -0.3429 0.08298 0.08088 -0.0347 1.0000 0.0153
-7.750 -0.3478 0.08102 0.07897 -0.0335 1.0000 0.0155
-7.500 -0.3697 0.07999 0.07802 -0.0293 1.0000 0.0155
-7.250 -0.3514 0.07544 0.07348 -0.0361 0.9952 0.0158
-7.000 -0.3270 0.07045 0.06848 -0.0446 0.9895 0.0169
-6.750 -0.2969 0.06371 0.06170 -0.0569 0.9846 0.0184
-6.500 -0.2571 0.05514 0.05299 -0.0717 0.9782 0.0198
-6.250 -0.2236 0.04774 0.04535 -0.0812 0.9734 0.0200
-6.000 -0.2082 0.03817 0.03544 -0.0884 0.9651 0.0209
-5.750 -0.1840 0.03554 0.03273 -0.0904 0.9590 0.0215
-5.500 -0.1621 0.03302 0.03005 -0.0915 0.9511 0.0223
-5.250 -0.1397 0.03037 0.02720 -0.0921 0.9434 0.0234
-5.000 -0.1190 0.02766 0.02421 -0.0917 0.9337 0.0253
-4.750 -0.0911 0.02762 0.02377 -0.0906 0.9258 0.0279
-4.500 -0.0768 0.02191 0.01762 -0.0904 0.9161 0.0299
-4.250 -0.0510 0.01674 0.01157 -0.0879 0.9076 0.0144
-4.000 -0.0276 0.01391 0.00841 -0.0869 0.9002 0.0128
-3.750 -0.0024 0.01248 0.00676 -0.0860 0.8914 0.0123
-3.500 0.0233 0.01147 0.00556 -0.0852 0.8838 0.0121
-3.250 0.0491 0.01070 0.00469 -0.0845 0.8748 0.0124
-3.000 0.0753 0.01011 0.00400 -0.0839 0.8661 0.0129
-2.750 0.1020 0.00967 0.00345 -0.0833 0.8575 0.0141
-2.500 0.1286 0.00912 0.00283 -0.0828 0.8475 0.0191
-2.250 0.1550 0.00848 0.00236 -0.0824 0.8381 0.0727
-2.000 0.1814 0.00807 0.00218 -0.0822 0.8289 0.1497
-1.750 0.2076 0.00763 0.00207 -0.0820 0.8184 0.2525
-1.500 0.2339 0.00726 0.00198 -0.0818 0.8083 0.3566
-1.250 0.2596 0.00684 0.00190 -0.0814 0.7983 0.4887
-1.000 0.2839 0.00635 0.00187 -0.0807 0.7874 0.6512
-0.750 0.3035 0.00582 0.00190 -0.0784 0.7757 0.8350
-0.500 0.3361 0.00564 0.00184 -0.0787 0.7640 0.9619
-0.250 0.3834 0.00562 0.00170 -0.0827 0.7518 1.0000
0.000 0.4088 0.00569 0.00165 -0.0821 0.7391 1.0000
0.250 0.4345 0.00576 0.00161 -0.0816 0.7264 1.0000
0.500 0.4604 0.00585 0.00159 -0.0810 0.7135 1.0000
0.750 0.4864 0.00593 0.00158 -0.0806 0.7001 1.0000
1.000 0.5126 0.00603 0.00158 -0.0801 0.6864 1.0000
1.250 0.5388 0.00613 0.00159 -0.0797 0.6716 1.0000
1.500 0.5650 0.00624 0.00161 -0.0793 0.6554 1.0000
1.750 0.5912 0.00635 0.00164 -0.0789 0.6388 1.0000
2.000 0.6175 0.00648 0.00170 -0.0785 0.6225 1.0000
2.250 0.6438 0.00662 0.00175 -0.0782 0.6063 1.0000
2.500 0.6700 0.00676 0.00182 -0.0778 0.5898 1.0000
2.750 0.6961 0.00692 0.00190 -0.0774 0.5724 1.0000
3.000 0.7221 0.00709 0.00198 -0.0770 0.5522 1.0000
3.250 0.7477 0.00729 0.00210 -0.0766 0.5318 1.0000
3.500 0.7737 0.00747 0.00222 -0.0762 0.5121 1.0000
3.750 0.7995 0.00767 0.00234 -0.0759 0.4928 1.0000
4.000 0.8251 0.00790 0.00249 -0.0755 0.4734 1.0000
4.250 0.8508 0.00812 0.00266 -0.0751 0.4532 1.0000
4.500 0.8762 0.00836 0.00284 -0.0747 0.4341 1.0000
4.750 0.9015 0.00862 0.00302 -0.0743 0.4143 1.0000
5.000 0.9265 0.00890 0.00324 -0.0739 0.3917 1.0000
5.250 0.9515 0.00919 0.00346 -0.0734 0.3696 1.0000
5.500 0.9762 0.00949 0.00369 -0.0730 0.3487 1.0000
5.750 1.0010 0.00980 0.00394 -0.0725 0.3298 1.0000
6.000 1.0255 0.01012 0.00422 -0.0720 0.3084 1.0000
6.250 1.0497 0.01048 0.00451 -0.0715 0.2875 1.0000
6.500 1.0739 0.01083 0.00482 -0.0710 0.2679 1.0000
6.750 1.0972 0.01125 0.00516 -0.0704 0.2460 1.0000
7.000 1.1203 0.01170 0.00551 -0.0698 0.2223 1.0000
7.250 1.1433 0.01214 0.00591 -0.0691 0.2012 1.0000
7.500 1.1658 0.01263 0.00632 -0.0684 0.1812 1.0000
7.750 1.1881 0.01312 0.00676 -0.0677 0.1642 1.0000
8.000 1.2104 0.01360 0.00721 -0.0669 0.1475 1.0000
8.250 1.2318 0.01414 0.00770 -0.0661 0.1296 1.0000
8.500 1.2521 0.01477 0.00824 -0.0651 0.1117 1.0000
8.750 1.2728 0.01534 0.00878 -0.0642 0.0971 1.0000
9.000 1.2928 0.01595 0.00935 -0.0632 0.0826 1.0000
9.250 1.3119 0.01661 0.00995 -0.0621 0.0692 1.0000
9.500 1.3304 0.01728 0.01061 -0.0609 0.0586 1.0000
9.750 1.3479 0.01800 0.01131 -0.0595 0.0493 1.0000
10.000 1.3645 0.01874 0.01205 -0.0581 0.0414 1.0000
10.250 1.3816 0.01940 0.01276 -0.0567 0.0355 1.0000
10.500 1.3952 0.02020 0.01357 -0.0547 0.0295 1.0000
10.750 1.4062 0.02104 0.01440 -0.0524 0.0236 1.0000
11.000 1.4137 0.02212 0.01548 -0.0497 0.0165 1.0000
11.250 1.4163 0.02358 0.01694 -0.0465 0.0105 1.0000
11.500 1.4236 0.02473 0.01819 -0.0441 0.0090 1.0000
11.750 1.4269 0.02621 0.01975 -0.0415 0.0079 1.0000
12.000 1.4265 0.02803 0.02171 -0.0388 0.0071 1.0000
12.250 1.4300 0.02965 0.02349 -0.0367 0.0068 1.0000
12.500 1.4327 0.03141 0.02538 -0.0349 0.0065 1.0000
12.750 1.4340 0.03340 0.02749 -0.0333 0.0062 1.0000
13.000 1.4339 0.03563 0.02985 -0.0319 0.0059 1.0000
13.250 1.4331 0.03806 0.03240 -0.0308 0.0057 1.0000
13.500 1.4303 0.04084 0.03532 -0.0300 0.0055 1.0000
13.750 1.4243 0.04415 0.03876 -0.0296 0.0053 1.0000
14.000 1.4177 0.04776 0.04250 -0.0296 0.0052 1.0000
14.250 1.4063 0.05218 0.04707 -0.0300 0.0050 1.0000
14.500 1.3988 0.05633 0.05137 -0.0307 0.0050 1.0000
14.750 1.3813 0.06215 0.05735 -0.0322 0.0049 1.0000
15.000 1.3718 0.06709 0.06244 -0.0337 0.0049 1.0000
15.250 1.3593 0.07274 0.06825 -0.0357 0.0048 1.0000
15.500 1.3435 0.07908 0.07475 -0.0380 0.0047 1.0000
15.750 1.3363 0.08432 0.08013 -0.0403 0.0048 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S9037 (9%) (s9037-il)