S4310 (s4310-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4310 (s4310-il) Reynolds number: 500,000 Max Cl/Cd: 102.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4310-il-500000-n5.txt Download as CSV file: xf-s4310-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4310
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2539 0.08158 0.07915 -0.0567 0.9009 0.0075
-8.750 -0.2551 0.07754 0.07505 -0.0584 0.8827 0.0074
-8.500 -0.2585 0.07347 0.07094 -0.0600 0.8664 0.0074
-8.250 -0.2659 0.06901 0.06645 -0.0619 0.8508 0.0074
-8.000 -0.2772 0.06471 0.06213 -0.0637 0.8362 0.0073
-7.750 -0.2900 0.05813 0.05550 -0.0696 0.8226 0.0075
-7.500 -0.3695 0.02329 0.01894 -0.0844 0.8082 0.0079
-7.250 -0.3521 0.02002 0.01508 -0.0839 0.8004 0.0083
-7.000 -0.3300 0.01823 0.01289 -0.0835 0.7935 0.0086
-6.750 -0.3058 0.01710 0.01154 -0.0833 0.7861 0.0090
-6.500 -0.2797 0.01672 0.01107 -0.0831 0.7794 0.0094
-6.250 -0.2532 0.01635 0.01061 -0.0830 0.7722 0.0098
-6.000 -0.2272 0.01569 0.00978 -0.0828 0.7656 0.0104
-5.750 -0.2012 0.01484 0.00874 -0.0825 0.7586 0.0110
-5.500 -0.1750 0.01411 0.00780 -0.0822 0.7521 0.0116
-5.250 -0.1486 0.01339 0.00694 -0.0820 0.7453 0.0122
-5.000 -0.1218 0.01294 0.00641 -0.0819 0.7387 0.0128
-4.750 -0.0946 0.01256 0.00597 -0.0818 0.7323 0.0136
-4.500 -0.0674 0.01218 0.00550 -0.0816 0.7257 0.0145
-4.250 -0.0398 0.01192 0.00514 -0.0815 0.7195 0.0156
-4.000 -0.0128 0.01144 0.00459 -0.0814 0.7129 0.0168
-3.750 0.0144 0.01110 0.00419 -0.0812 0.7068 0.0179
-3.500 0.0420 0.01080 0.00384 -0.0811 0.7001 0.0191
-3.250 0.0696 0.01058 0.00354 -0.0810 0.6939 0.0205
-3.000 0.0975 0.01037 0.00328 -0.0810 0.6875 0.0216
-2.750 0.1250 0.01004 0.00289 -0.0809 0.6811 0.0233
-2.500 0.1529 0.00985 0.00264 -0.0808 0.6749 0.0250
-2.250 0.1808 0.00970 0.00244 -0.0808 0.6682 0.0274
-2.000 0.2087 0.00955 0.00224 -0.0807 0.6620 0.0304
-1.750 0.2367 0.00939 0.00209 -0.0806 0.6551 0.0387
-1.500 0.2643 0.00919 0.00195 -0.0806 0.6488 0.0691
-1.250 0.2921 0.00897 0.00186 -0.0806 0.6419 0.1128
-1.000 0.3195 0.00876 0.00179 -0.0806 0.6352 0.1683
-0.750 0.3471 0.00855 0.00175 -0.0807 0.6281 0.2293
-0.500 0.3745 0.00837 0.00171 -0.0807 0.6208 0.2931
-0.250 0.4016 0.00809 0.00170 -0.0807 0.6131 0.3909
0.250 0.4517 0.00723 0.00177 -0.0798 0.5970 0.7081
0.500 0.4728 0.00693 0.00184 -0.0780 0.5894 0.8464
0.750 0.4978 0.00685 0.00187 -0.0769 0.5808 0.9263
1.000 0.5357 0.00687 0.00185 -0.0789 0.5718 0.9722
1.250 0.5755 0.00693 0.00183 -0.0815 0.5623 1.0000
1.500 0.6022 0.00702 0.00186 -0.0812 0.5531 1.0000
1.750 0.6287 0.00712 0.00189 -0.0810 0.5439 1.0000
2.000 0.6553 0.00724 0.00194 -0.0807 0.5338 1.0000
2.250 0.6820 0.00735 0.00199 -0.0805 0.5232 1.0000
2.500 0.7086 0.00747 0.00206 -0.0803 0.5120 1.0000
2.750 0.7351 0.00762 0.00213 -0.0800 0.5000 1.0000
3.000 0.7615 0.00777 0.00222 -0.0798 0.4872 1.0000
3.250 0.7878 0.00794 0.00233 -0.0796 0.4740 1.0000
3.750 0.8401 0.00830 0.00256 -0.0790 0.4456 1.0000
4.000 0.8660 0.00851 0.00270 -0.0788 0.4307 1.0000
4.250 0.8918 0.00872 0.00286 -0.0785 0.4149 1.0000
4.500 0.9174 0.00895 0.00303 -0.0782 0.3989 1.0000
4.750 0.9427 0.00921 0.00322 -0.0778 0.3816 1.0000
5.000 0.9678 0.00948 0.00342 -0.0775 0.3647 1.0000
5.250 0.9925 0.00978 0.00365 -0.0771 0.3472 1.0000
5.500 1.0170 0.01009 0.00389 -0.0766 0.3305 1.0000
5.750 1.0412 0.01041 0.00414 -0.0762 0.3134 1.0000
6.000 1.0653 0.01073 0.00442 -0.0757 0.2969 1.0000
6.250 1.0891 0.01108 0.00471 -0.0752 0.2808 1.0000
6.500 1.1127 0.01143 0.00500 -0.0747 0.2659 1.0000
6.750 1.1359 0.01179 0.00532 -0.0741 0.2509 1.0000
7.000 1.1590 0.01216 0.00565 -0.0735 0.2373 1.0000
7.250 1.1815 0.01255 0.00600 -0.0728 0.2230 1.0000
7.500 1.2039 0.01294 0.00636 -0.0721 0.2111 1.0000
7.750 1.2257 0.01334 0.00673 -0.0713 0.1993 1.0000
8.000 1.2468 0.01379 0.00714 -0.0705 0.1864 1.0000
8.250 1.2677 0.01422 0.00756 -0.0696 0.1750 1.0000
8.500 1.2881 0.01466 0.00798 -0.0686 0.1642 1.0000
8.750 1.3068 0.01518 0.00846 -0.0674 0.1512 1.0000
9.000 1.3247 0.01571 0.00896 -0.0661 0.1393 1.0000
9.250 1.3399 0.01635 0.00954 -0.0644 0.1240 1.0000
9.500 1.3532 0.01695 0.01010 -0.0624 0.1123 1.0000
9.750 1.3654 0.01760 0.01072 -0.0602 0.1017 1.0000
10.000 1.3774 0.01829 0.01139 -0.0582 0.0931 1.0000
10.250 1.3906 0.01894 0.01206 -0.0563 0.0859 1.0000
10.500 1.4017 0.01974 0.01285 -0.0544 0.0777 1.0000
10.750 1.4114 0.02067 0.01377 -0.0525 0.0687 1.0000
11.000 1.4211 0.02164 0.01473 -0.0506 0.0608 1.0000
11.250 1.4317 0.02260 0.01571 -0.0490 0.0550 1.0000
11.500 1.4392 0.02381 0.01690 -0.0472 0.0471 1.0000
11.750 1.4450 0.02520 0.01826 -0.0455 0.0384 1.0000
12.000 1.4513 0.02662 0.01968 -0.0439 0.0315 1.0000
12.250 1.4544 0.02835 0.02139 -0.0423 0.0238 1.0000
12.500 1.4582 0.03011 0.02316 -0.0409 0.0180 1.0000
12.750 1.4587 0.03222 0.02528 -0.0394 0.0114 1.0000
13.000 1.4588 0.03446 0.02756 -0.0382 0.0073 1.0000
13.250 1.4614 0.03656 0.02973 -0.0372 0.0059 1.0000
13.500 1.4637 0.03877 0.03203 -0.0364 0.0051 1.0000
13.750 1.4672 0.04094 0.03429 -0.0358 0.0047 1.0000
14.000 1.4700 0.04323 0.03668 -0.0353 0.0044 1.0000
14.250 1.4712 0.04577 0.03933 -0.0349 0.0041 1.0000
14.500 1.4712 0.04857 0.04223 -0.0347 0.0039 1.0000
14.750 1.4712 0.05144 0.04522 -0.0347 0.0038 1.0000
15.000 1.4699 0.05460 0.04849 -0.0348 0.0037 1.0000
15.250 1.4659 0.05822 0.05223 -0.0352 0.0035 1.0000
15.500 1.4646 0.06160 0.05574 -0.0357 0.0034 1.0000
15.750 1.4610 0.06541 0.05968 -0.0365 0.0033 1.0000
16.000 1.4572 0.06937 0.06379 -0.0374 0.0033 1.0000
16.250 1.4523 0.07363 0.06817 -0.0386 0.0032 1.0000
16.500 1.4477 0.07795 0.07262 -0.0399 0.0031 1.0000
16.750 1.4401 0.08288 0.07768 -0.0416 0.0031 1.0000
17.000 1.4316 0.08811 0.08305 -0.0435 0.0029 1.0000
17.250 1.4228 0.09352 0.08859 -0.0456 0.0029 1.0000
17.500 1.4129 0.09924 0.09444 -0.0480 0.0028 1.0000
17.750 1.4025 0.10521 0.10056 -0.0507 0.0028 1.0000
18.000 1.3922 0.11127 0.10674 -0.0534 0.0028 1.0000
18.250 1.3790 0.11800 0.11362 -0.0567 0.0028 1.0000
18.500 1.3678 0.12446 0.12021 -0.0599 0.0028 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4310 (s4310-il)