MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 200,000 Max Cl/Cd: 66.28 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh84-il-200000-n5.txt Download as CSV file: xf-mh84-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 84 13.69%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3170 0.07024 0.06639 -0.0278 0.7546 0.0179
-8.000 -0.4061 0.04099 0.03664 -0.0591 0.7505 0.0169
-7.750 -0.4000 0.03389 0.02880 -0.0664 0.7394 0.0169
-7.500 -0.3816 0.03022 0.02461 -0.0688 0.7272 0.0169
-7.250 -0.3596 0.02765 0.02159 -0.0700 0.7159 0.0171
-7.000 -0.3355 0.02564 0.01919 -0.0706 0.7041 0.0173
-6.750 -0.3100 0.02398 0.01719 -0.0710 0.6927 0.0176
-6.500 -0.2839 0.02263 0.01552 -0.0711 0.6814 0.0179
-6.250 -0.2573 0.02155 0.01430 -0.0711 0.6698 0.0182
-6.000 -0.2306 0.02069 0.01330 -0.0711 0.6590 0.0186
-5.750 -0.2031 0.01988 0.01237 -0.0711 0.6474 0.0191
-5.500 -0.1756 0.01913 0.01145 -0.0710 0.6367 0.0197
-5.250 -0.1476 0.01841 0.01057 -0.0709 0.6254 0.0204
-5.000 -0.1195 0.01775 0.00977 -0.0708 0.6148 0.0212
-4.750 -0.0913 0.01720 0.00913 -0.0708 0.6037 0.0221
-4.500 -0.0627 0.01673 0.00854 -0.0708 0.5933 0.0238
-4.250 -0.0342 0.01629 0.00800 -0.0707 0.5825 0.0257
-4.000 -0.0053 0.01586 0.00746 -0.0706 0.5720 0.0283
-3.750 0.0234 0.01546 0.00695 -0.0706 0.5619 0.0312
-3.500 0.0525 0.01504 0.00648 -0.0705 0.5511 0.0354
-3.250 0.0812 0.01468 0.00605 -0.0705 0.5414 0.0431
-3.000 0.1103 0.01430 0.00570 -0.0705 0.5308 0.0562
-2.750 0.1391 0.01401 0.00541 -0.0704 0.5211 0.0762
-2.500 0.1680 0.01377 0.00522 -0.0704 0.5107 0.0996
-2.250 0.1968 0.01361 0.00506 -0.0703 0.5012 0.1236
-2.000 0.2258 0.01348 0.00495 -0.0702 0.4909 0.1470
-1.750 0.2546 0.01339 0.00486 -0.0701 0.4816 0.1694
-1.500 0.2835 0.01333 0.00479 -0.0700 0.4716 0.1911
-1.250 0.3123 0.01330 0.00471 -0.0699 0.4625 0.2108
-1.000 0.3412 0.01326 0.00465 -0.0698 0.4528 0.2291
-0.750 0.3699 0.01324 0.00460 -0.0697 0.4440 0.2471
-0.500 0.3988 0.01321 0.00456 -0.0696 0.4346 0.2655
-0.250 0.4274 0.01321 0.00454 -0.0694 0.4260 0.2852
0.000 0.4561 0.01320 0.00453 -0.0693 0.4168 0.3071
0.250 0.4846 0.01322 0.00454 -0.0692 0.4086 0.3318
0.500 0.5132 0.01320 0.00457 -0.0691 0.3997 0.3607
1.000 0.5697 0.01318 0.00469 -0.0688 0.3835 0.4416
1.500 0.6248 0.01310 0.00489 -0.0683 0.3678 0.5683
1.750 0.6509 0.01302 0.00501 -0.0676 0.3601 0.6554
2.000 0.6748 0.01285 0.00511 -0.0663 0.3535 0.7650
2.250 0.7048 0.01265 0.00510 -0.0661 0.3457 1.0000
2.500 0.7330 0.01289 0.00520 -0.0660 0.3388 1.0000
2.750 0.7614 0.01309 0.00534 -0.0660 0.3314 1.0000
3.000 0.7894 0.01335 0.00547 -0.0659 0.3247 1.0000
3.250 0.8175 0.01358 0.00563 -0.0658 0.3184 1.0000
3.500 0.8454 0.01382 0.00580 -0.0656 0.3115 1.0000
3.750 0.8727 0.01412 0.00598 -0.0655 0.3054 1.0000
4.000 0.9006 0.01435 0.00619 -0.0654 0.2991 1.0000
4.250 0.9279 0.01464 0.00640 -0.0652 0.2931 1.0000
4.500 0.9550 0.01495 0.00664 -0.0651 0.2877 1.0000
4.750 0.9824 0.01522 0.00688 -0.0649 0.2817 1.0000
5.000 1.0091 0.01554 0.00714 -0.0647 0.2761 1.0000
5.250 1.0357 0.01587 0.00741 -0.0645 0.2713 1.0000
5.500 1.0626 0.01617 0.00772 -0.0643 0.2659 1.0000
5.750 1.0888 0.01652 0.00801 -0.0641 0.2607 1.0000
6.000 1.1146 0.01691 0.00833 -0.0638 0.2562 1.0000
6.250 1.1409 0.01723 0.00869 -0.0636 0.2515 1.0000
6.500 1.1666 0.01760 0.00904 -0.0634 0.2469 1.0000
6.750 1.1916 0.01802 0.00940 -0.0630 0.2427 1.0000
7.000 1.2169 0.01841 0.00980 -0.0627 0.2385 1.0000
7.250 1.2419 0.01880 0.01022 -0.0624 0.2342 1.0000
7.500 1.2663 0.01923 0.01064 -0.0620 0.2304 1.0000
7.750 1.2897 0.01973 0.01109 -0.0616 0.2269 1.0000
8.000 1.3139 0.02016 0.01157 -0.0612 0.2232 1.0000
8.250 1.3376 0.02060 0.01205 -0.0608 0.2193 1.0000
8.500 1.3604 0.02110 0.01255 -0.0603 0.2157 1.0000
8.750 1.3821 0.02166 0.01309 -0.0597 0.2127 1.0000
9.000 1.4042 0.02220 0.01366 -0.0591 0.2097 1.0000
9.250 1.4260 0.02272 0.01425 -0.0585 0.2064 1.0000
9.500 1.4466 0.02328 0.01486 -0.0579 0.2031 1.0000
9.750 1.4658 0.02391 0.01549 -0.0571 0.2001 1.0000
10.000 1.4835 0.02463 0.01618 -0.0562 0.1975 1.0000
10.250 1.5022 0.02525 0.01690 -0.0553 0.1948 1.0000
10.500 1.5193 0.02594 0.01767 -0.0543 0.1921 1.0000
10.750 1.5331 0.02667 0.01847 -0.0530 0.1896 1.0000
11.000 1.5445 0.02752 0.01935 -0.0515 0.1872 1.0000
11.250 1.5548 0.02850 0.02032 -0.0501 0.1849 1.0000
11.500 1.5656 0.02954 0.02141 -0.0490 0.1827 1.0000
11.750 1.5766 0.03062 0.02262 -0.0480 0.1803 1.0000
12.000 1.5867 0.03182 0.02391 -0.0471 0.1780 1.0000
12.250 1.5959 0.03312 0.02529 -0.0463 0.1759 1.0000
12.500 1.6045 0.03453 0.02674 -0.0456 0.1739 1.0000
12.750 1.6126 0.03603 0.02827 -0.0450 0.1721 1.0000
13.000 1.6210 0.03759 0.02985 -0.0445 0.1702 1.0000
13.250 1.6275 0.03937 0.03179 -0.0442 0.1681 1.0000
13.500 1.6331 0.04128 0.03382 -0.0439 0.1660 1.0000
13.750 1.6380 0.04331 0.03595 -0.0438 0.1639 1.0000
14.000 1.6426 0.04539 0.03811 -0.0437 0.1621 1.0000
14.250 1.6474 0.04750 0.04027 -0.0437 0.1604 1.0000
14.500 1.6529 0.04953 0.04232 -0.0436 0.1588 1.0000
14.750 1.6563 0.05191 0.04479 -0.0437 0.1572 1.0000
15.000 1.6554 0.05486 0.04792 -0.0442 0.1554 1.0000
15.250 1.6539 0.05791 0.05111 -0.0448 0.1535 1.0000
15.500 1.6526 0.06102 0.05434 -0.0455 0.1517 1.0000
15.750 1.6514 0.06418 0.05759 -0.0463 0.1499 1.0000
16.000 1.6524 0.06712 0.06059 -0.0470 0.1484 1.0000
16.250 1.6566 0.06962 0.06313 -0.0475 0.1470 1.0000
16.500 1.6566 0.07283 0.06643 -0.0483 0.1455 1.0000
16.750 1.6444 0.07796 0.07177 -0.0503 0.1437 1.0000
17.000 1.6325 0.08316 0.07715 -0.0524 0.1419 1.0000
17.250 1.6219 0.08827 0.08240 -0.0546 0.1400 1.0000
17.500 1.6148 0.09293 0.08717 -0.0565 0.1383 1.0000
17.750 1.6130 0.09672 0.09103 -0.0580 0.1368 1.0000
18.000 1.6209 0.09883 0.09315 -0.0585 0.1354 1.0000
18.250 1.6003 0.10599 0.10049 -0.0620 0.1336 1.0000
18.500 1.5354 0.12157 0.11644 -0.0707 0.1305 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 84 13.69% (mh84-il)