S2091-101-83 (s2091-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S2091-101-83 (s2091-il) Reynolds number: 200,000 Max Cl/Cd: 77.91 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2091-il-200000.txt Download as CSV file: xf-s2091-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S2091-101-83
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3043 0.08947 0.08617 -0.0336 1.0000 0.0494
-8.000 -0.3026 0.08657 0.08333 -0.0348 1.0000 0.0509
-7.750 -0.3067 0.08400 0.08085 -0.0358 1.0000 0.0522
-7.500 -0.3306 0.08346 0.08045 -0.0322 1.0000 0.0528
-7.250 -0.3254 0.07658 0.07357 -0.0530 0.9872 0.0546
-7.000 -0.3062 0.06982 0.06681 -0.0580 0.9822 0.0556
-6.750 -0.2835 0.06744 0.06444 -0.0572 0.9773 0.0570
-6.500 -0.2524 0.06330 0.06026 -0.0633 0.9727 0.0597
-6.250 -0.2159 0.05134 0.04774 -0.0866 0.9599 0.0671
-6.000 -0.1914 0.04970 0.04632 -0.0854 0.9548 0.0694
-5.750 -0.1651 0.04661 0.04313 -0.0883 0.9462 0.0733
-5.500 -0.1487 0.02886 0.02373 -0.0967 0.9321 0.0434
-5.250 -0.1257 0.02518 0.01952 -0.0969 0.9230 0.0429
-5.000 -0.1000 0.02313 0.01682 -0.0965 0.9148 0.0450
-4.750 -0.0774 0.02088 0.01436 -0.0959 0.9053 0.0470
-4.500 -0.0519 0.01964 0.01293 -0.0951 0.8982 0.0490
-4.250 -0.0270 0.01881 0.01187 -0.0943 0.8883 0.0527
-4.000 -0.0017 0.01755 0.01032 -0.0933 0.8809 0.0560
-3.750 0.0232 0.01670 0.00946 -0.0926 0.8716 0.0601
-3.500 0.0492 0.01623 0.00882 -0.0917 0.8635 0.0657
-3.250 0.0741 0.01521 0.00781 -0.0909 0.8550 0.0719
-3.000 0.1000 0.01463 0.00716 -0.0901 0.8465 0.0814
-2.750 0.1260 0.01417 0.00665 -0.0893 0.8384 0.0935
-2.500 0.1516 0.01358 0.00613 -0.0888 0.8294 0.1107
-2.250 0.1776 0.01314 0.00572 -0.0881 0.8217 0.1311
-2.000 0.2039 0.01273 0.00542 -0.0877 0.8121 0.1598
-1.750 0.2299 0.01221 0.00507 -0.0871 0.8049 0.2155
-1.500 0.2549 0.01149 0.00495 -0.0868 0.7946 0.3620
-1.250 0.2786 0.01087 0.00490 -0.0858 0.7865 0.5381
-1.000 0.2998 0.01033 0.00487 -0.0838 0.7771 0.6981
-0.750 0.3246 0.00977 0.00477 -0.0817 0.7683 0.9113
-0.500 0.3653 0.00967 0.00447 -0.0839 0.7595 1.0000
-0.250 0.3922 0.00973 0.00439 -0.0836 0.7490 1.0000
0.000 0.4193 0.00978 0.00428 -0.0832 0.7398 1.0000
0.250 0.4464 0.00983 0.00419 -0.0828 0.7297 1.0000
0.500 0.4735 0.00990 0.00415 -0.0824 0.7190 1.0000
0.750 0.5007 0.00997 0.00407 -0.0820 0.7094 1.0000
1.000 0.5279 0.01004 0.00403 -0.0817 0.6986 1.0000
1.250 0.5551 0.01012 0.00403 -0.0814 0.6872 1.0000
1.500 0.5823 0.01021 0.00402 -0.0810 0.6764 1.0000
1.750 0.6096 0.01030 0.00398 -0.0806 0.6660 1.0000
2.000 0.6366 0.01040 0.00403 -0.0803 0.6536 1.0000
2.250 0.6637 0.01051 0.00408 -0.0800 0.6415 1.0000
2.500 0.6908 0.01063 0.00412 -0.0797 0.6296 1.0000
2.750 0.7178 0.01076 0.00416 -0.0793 0.6178 1.0000
3.000 0.7448 0.01089 0.00422 -0.0790 0.6053 1.0000
3.250 0.7715 0.01103 0.00433 -0.0787 0.5918 1.0000
3.500 0.7982 0.01119 0.00444 -0.0783 0.5782 1.0000
3.750 0.8248 0.01136 0.00456 -0.0780 0.5646 1.0000
4.000 0.8513 0.01154 0.00471 -0.0776 0.5506 1.0000
4.250 0.8776 0.01174 0.00486 -0.0773 0.5365 1.0000
4.500 0.9038 0.01195 0.00502 -0.0769 0.5220 1.0000
4.750 0.9298 0.01217 0.00522 -0.0765 0.5073 1.0000
5.000 0.9556 0.01242 0.00542 -0.0761 0.4921 1.0000
5.250 0.9812 0.01267 0.00565 -0.0757 0.4768 1.0000
5.500 1.0066 0.01295 0.00589 -0.0752 0.4611 1.0000
5.750 1.0317 0.01325 0.00617 -0.0747 0.4453 1.0000
6.000 1.0565 0.01356 0.00646 -0.0742 0.4292 1.0000
6.250 1.0811 0.01390 0.00676 -0.0737 0.4131 1.0000
6.500 1.1053 0.01426 0.00711 -0.0731 0.3969 1.0000
6.750 1.1291 0.01464 0.00746 -0.0725 0.3805 1.0000
7.000 1.1526 0.01504 0.00784 -0.0719 0.3643 1.0000
7.250 1.1757 0.01547 0.00825 -0.0712 0.3483 1.0000
7.500 1.1983 0.01593 0.00868 -0.0705 0.3323 1.0000
7.750 1.2203 0.01642 0.00914 -0.0697 0.3164 1.0000
8.000 1.2421 0.01690 0.00963 -0.0689 0.3002 1.0000
8.250 1.2633 0.01740 0.01016 -0.0681 0.2842 1.0000
8.500 1.2838 0.01794 0.01071 -0.0671 0.2684 1.0000
8.750 1.3037 0.01851 0.01129 -0.0661 0.2529 1.0000
9.000 1.3227 0.01912 0.01191 -0.0650 0.2375 1.0000
9.250 1.3408 0.01976 0.01258 -0.0638 0.2220 1.0000
9.500 1.3577 0.02045 0.01328 -0.0625 0.2065 1.0000
9.750 1.3731 0.02120 0.01403 -0.0610 0.1909 1.0000
10.000 1.3867 0.02203 0.01486 -0.0592 0.1754 1.0000
10.250 1.3973 0.02294 0.01576 -0.0571 0.1603 1.0000
10.500 1.4047 0.02394 0.01675 -0.0547 0.1462 1.0000
10.750 1.4107 0.02510 0.01789 -0.0522 0.1326 1.0000
11.000 1.4157 0.02640 0.01919 -0.0500 0.1201 1.0000
11.250 1.4199 0.02787 0.02067 -0.0479 0.1089 1.0000
11.500 1.4226 0.02956 0.02235 -0.0459 0.0995 1.0000
11.750 1.4228 0.03153 0.02427 -0.0440 0.0916 1.0000
12.000 1.4279 0.03324 0.02611 -0.0426 0.0840 1.0000
12.250 1.4266 0.03559 0.02842 -0.0411 0.0784 1.0000
12.500 1.4310 0.03751 0.03048 -0.0400 0.0727 1.0000
12.750 1.4290 0.04011 0.03304 -0.0389 0.0684 1.0000
13.000 1.4320 0.04236 0.03545 -0.0380 0.0641 1.0000
13.250 1.4334 0.04482 0.03799 -0.0374 0.0604 1.0000
13.500 1.4311 0.04779 0.04088 -0.0366 0.0570 1.0000
13.750 1.4335 0.05032 0.04364 -0.0363 0.0542 1.0000
14.000 1.4344 0.05306 0.04650 -0.0361 0.0514 1.0000
14.250 1.4339 0.05602 0.04949 -0.0360 0.0490 1.0000
14.500 1.4348 0.05896 0.05246 -0.0355 0.0466 1.0000
14.750 1.4341 0.06215 0.05587 -0.0358 0.0447 1.0000
15.000 1.4336 0.06539 0.05924 -0.0361 0.0427 1.0000
15.250 1.4338 0.06858 0.06249 -0.0365 0.0411 1.0000
15.500 1.4369 0.07146 0.06534 -0.0361 0.0390 1.0000
15.750 1.4338 0.07537 0.06946 -0.0368 0.0379 1.0000
16.000 1.4295 0.07952 0.07382 -0.0380 0.0367 1.0000
16.250 1.4246 0.08385 0.07833 -0.0394 0.0355 1.0000
16.500 1.4207 0.08810 0.08272 -0.0408 0.0343 1.0000
16.750 1.4181 0.09221 0.08695 -0.0422 0.0333 1.0000
17.000 1.4181 0.09585 0.09062 -0.0431 0.0322 1.0000
17.250 1.4124 0.10068 0.09558 -0.0442 0.0312 1.0000
17.500 1.3998 0.10686 0.10201 -0.0474 0.0308 1.0000
17.750 1.3863 0.11345 0.10884 -0.0510 0.0304 1.0000
18.000 1.3722 0.12037 0.11599 -0.0549 0.0300 1.0000
18.250 1.3565 0.12786 0.12371 -0.0594 0.0297 1.0000
18.500 1.3392 0.13597 0.13203 -0.0644 0.0294 1.0000
18.750 1.3189 0.14510 0.14138 -0.0704 0.0294 1.0000
19.000 1.2937 0.15588 0.15238 -0.0777 0.0296 1.0000
19.250 1.2606 0.16937 0.16607 -0.0870 0.0303 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S2091-101-83 (s2091-il)