MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 100,000 Max Cl/Cd: 53.89 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh32-il-100000.txt Download as CSV file: xf-mh32-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3364 0.09505 0.09051 -0.0266 1.0000 0.0849
-8.750 -0.3509 0.09205 0.08759 -0.0304 1.0000 0.0876
-8.500 -0.3616 0.08880 0.08442 -0.0334 1.0000 0.0880
-8.250 -0.3348 0.08395 0.07955 -0.0287 1.0000 0.0951
-8.000 -0.3411 0.08064 0.07631 -0.0304 1.0000 0.0993
-7.750 -0.3552 0.07743 0.07320 -0.0330 1.0000 0.1007
-7.500 -0.4474 0.08273 0.07831 -0.0398 1.0000 0.0889
-7.250 -0.4236 0.08041 0.07602 -0.0304 1.0000 0.0960
-7.000 -0.4283 0.07709 0.07277 -0.0326 1.0000 0.0977
-6.750 -0.4508 0.07344 0.06901 -0.0414 1.0000 0.1015
-6.500 -0.4388 0.07007 0.06584 -0.0354 1.0000 0.1051
-6.250 -0.4052 0.05782 0.05401 -0.0307 1.0000 0.1180
-6.000 -0.4064 0.05538 0.05161 -0.0287 1.0000 0.1251
-5.750 -0.4388 0.06151 0.05728 -0.0339 1.0000 0.1243
-5.500 -0.4375 0.05822 0.05394 -0.0338 1.0000 0.1330
-5.250 -0.4334 0.05520 0.05084 -0.0337 1.0000 0.1455
-5.000 -0.4264 0.05230 0.04784 -0.0334 1.0000 0.1584
-4.750 -0.4170 0.04951 0.04491 -0.0328 1.0000 0.1719
-4.500 -0.3757 0.03525 0.02887 -0.0380 1.0000 0.0594
-4.250 -0.3519 0.03153 0.02418 -0.0365 1.0000 0.0493
-4.000 -0.3307 0.02804 0.02038 -0.0358 1.0000 0.0473
-3.750 -0.3072 0.02540 0.01724 -0.0348 1.0000 0.0467
-3.500 -0.2826 0.02340 0.01484 -0.0338 1.0000 0.0472
-3.250 -0.2580 0.02138 0.01257 -0.0329 1.0000 0.0515
-3.000 -0.2349 0.02038 0.01143 -0.0319 1.0000 0.0611
-2.750 -0.2118 0.01891 0.00999 -0.0309 1.0000 0.0743
-2.500 -0.1893 0.01740 0.00878 -0.0300 1.0000 0.1181
-2.250 -0.1677 0.01508 0.00805 -0.0295 1.0000 0.3875
-2.000 -0.1539 0.01410 0.00823 -0.0263 1.0000 0.6685
-1.750 -0.1162 0.01348 0.00805 -0.0269 1.0000 1.0000
-1.500 -0.0957 0.01371 0.00794 -0.0265 1.0000 1.0000
-1.250 -0.0529 0.01419 0.00804 -0.0302 0.9932 1.0000
-1.000 -0.0047 0.01466 0.00819 -0.0349 0.9835 1.0000
-0.750 0.0407 0.01506 0.00832 -0.0390 0.9732 1.0000
-0.500 0.0860 0.01543 0.00848 -0.0429 0.9628 1.0000
-0.250 0.1331 0.01576 0.00863 -0.0471 0.9529 1.0000
0.000 0.1797 0.01601 0.00873 -0.0511 0.9425 1.0000
0.250 0.2216 0.01618 0.00880 -0.0541 0.9306 1.0000
0.500 0.2642 0.01630 0.00885 -0.0570 0.9188 1.0000
0.750 0.3084 0.01634 0.00884 -0.0601 0.9072 1.0000
1.000 0.3559 0.01627 0.00875 -0.0637 0.8965 1.0000
1.250 0.4038 0.01607 0.00854 -0.0670 0.8864 1.0000
1.500 0.4432 0.01588 0.00835 -0.0686 0.8739 1.0000
1.750 0.4783 0.01568 0.00818 -0.0692 0.8603 1.0000
2.000 0.5095 0.01551 0.00802 -0.0691 0.8453 1.0000
2.250 0.5374 0.01537 0.00790 -0.0683 0.8285 1.0000
2.500 0.5660 0.01517 0.00773 -0.0675 0.8119 1.0000
2.750 0.5947 0.01495 0.00757 -0.0666 0.7951 1.0000
3.000 0.6224 0.01474 0.00737 -0.0655 0.7773 1.0000
3.250 0.6474 0.01464 0.00729 -0.0641 0.7560 1.0000
3.500 0.6735 0.01452 0.00717 -0.0628 0.7346 1.0000
3.750 0.6994 0.01444 0.00713 -0.0615 0.7115 1.0000
4.000 0.7240 0.01447 0.00715 -0.0601 0.6855 1.0000
4.250 0.7486 0.01456 0.00721 -0.0588 0.6582 1.0000
4.500 0.7730 0.01472 0.00731 -0.0574 0.6294 1.0000
4.750 0.7963 0.01497 0.00753 -0.0561 0.5979 1.0000
5.000 0.8194 0.01527 0.00784 -0.0547 0.5652 1.0000
5.250 0.8421 0.01563 0.00812 -0.0533 0.5317 1.0000
5.500 0.8639 0.01603 0.00848 -0.0519 0.4956 1.0000
5.750 0.8853 0.01650 0.00888 -0.0505 0.4585 1.0000
6.000 0.9060 0.01704 0.00933 -0.0490 0.4208 1.0000
6.250 0.9260 0.01767 0.00984 -0.0475 0.3823 1.0000
6.500 0.9452 0.01837 0.01052 -0.0459 0.3427 1.0000
6.750 0.9636 0.01916 0.01121 -0.0444 0.3025 1.0000
7.000 0.9810 0.02006 0.01200 -0.0428 0.2625 1.0000
7.250 0.9973 0.02108 0.01290 -0.0411 0.2226 1.0000
7.500 1.0125 0.02221 0.01390 -0.0393 0.1834 1.0000
7.750 1.0264 0.02357 0.01512 -0.0374 0.1458 1.0000
8.000 1.0395 0.02534 0.01668 -0.0354 0.1152 1.0000
8.250 1.0536 0.02729 0.01855 -0.0334 0.0907 1.0000
8.500 1.0689 0.02955 0.02076 -0.0317 0.0731 1.0000
8.750 1.0832 0.03156 0.02288 -0.0299 0.0583 1.0000
9.000 1.0992 0.03433 0.02581 -0.0283 0.0478 1.0000
9.250 1.1146 0.03720 0.02870 -0.0270 0.0401 1.0000
9.500 1.1300 0.04095 0.03295 -0.0251 0.0372 1.0000
9.750 1.1392 0.04391 0.03636 -0.0228 0.0342 1.0000
10.000 1.1463 0.04615 0.03876 -0.0210 0.0309 1.0000
10.250 1.1497 0.05044 0.04325 -0.0194 0.0292 1.0000
10.500 1.1453 0.05501 0.04821 -0.0170 0.0289 1.0000
10.750 1.1357 0.05896 0.05251 -0.0143 0.0288 1.0000
11.000 1.1231 0.06228 0.05612 -0.0115 0.0289 1.0000
11.250 1.1090 0.06555 0.05964 -0.0094 0.0290 1.0000
11.500 1.0932 0.06909 0.06344 -0.0082 0.0291 1.0000
11.750 1.0757 0.07301 0.06761 -0.0081 0.0293 1.0000
12.000 1.0561 0.07765 0.07248 -0.0093 0.0296 1.0000
12.250 1.0321 0.08349 0.07860 -0.0123 0.0302 1.0000
12.500 0.9739 0.09754 0.09306 -0.0232 0.0343 1.0000
12.750 0.9484 0.10803 0.10362 -0.0302 0.0367 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 32 8.7% (mh32-il)