MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 100,000 Max Cl/Cd: 33.65 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh78-il-100000-n5.txt Download as CSV file: xf-mh78-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6339 0.07744 0.07274 0.0053 1.0000 0.0260
-10.000 -0.6505 0.07072 0.06594 -0.0002 1.0000 0.0257
-9.750 -0.6775 0.06435 0.05940 -0.0038 1.0000 0.0255
-9.500 -0.6994 0.05972 0.05459 -0.0043 1.0000 0.0253
-9.250 -0.7207 0.05565 0.05028 -0.0027 1.0000 0.0253
-9.000 -0.7317 0.05179 0.04612 -0.0011 1.0000 0.0253
-8.750 -0.7389 0.04778 0.04168 0.0007 1.0000 0.0257
-8.500 -0.7407 0.04393 0.03729 0.0026 1.0000 0.0260
-8.250 -0.7280 0.04162 0.03482 0.0036 1.0000 0.0265
-7.750 -0.6937 0.03789 0.03061 0.0055 0.8473 0.0274
-7.250 -0.6664 0.03433 0.02624 0.0103 0.7683 0.0280
-7.000 -0.6485 0.03264 0.02418 0.0121 0.7397 0.0285
-6.750 -0.6283 0.03106 0.02224 0.0137 0.7139 0.0290
-6.500 -0.6065 0.02959 0.02043 0.0151 0.6907 0.0296
-6.250 -0.5835 0.02827 0.01886 0.0163 0.6690 0.0303
-6.000 -0.5603 0.02724 0.01772 0.0172 0.6486 0.0310
-5.750 -0.5365 0.02627 0.01661 0.0182 0.6292 0.0321
-5.500 -0.5122 0.02537 0.01550 0.0192 0.6107 0.0340
-5.250 -0.4886 0.02456 0.01466 0.0201 0.5934 0.0358
-5.000 -0.4646 0.02381 0.01376 0.0211 0.5770 0.0382
-4.750 -0.4413 0.02304 0.01291 0.0221 0.5617 0.0404
-4.500 -0.4177 0.02234 0.01209 0.0232 0.5473 0.0431
-4.250 -0.3938 0.02168 0.01138 0.0241 0.5325 0.0473
-4.000 -0.3698 0.02107 0.01069 0.0250 0.5190 0.0532
-3.750 -0.3459 0.02045 0.01000 0.0260 0.5063 0.0617
-3.500 -0.3217 0.01979 0.00940 0.0269 0.4934 0.0761
-3.250 -0.2984 0.01905 0.00883 0.0279 0.4821 0.1090
-3.000 -0.2752 0.01830 0.00843 0.0287 0.4701 0.1784
-2.750 -0.2518 0.01768 0.00813 0.0295 0.4594 0.2559
-2.500 -0.2289 0.01708 0.00786 0.0305 0.4487 0.3409
-2.250 -0.2075 0.01639 0.00766 0.0319 0.4388 0.4534
-2.000 -0.1858 0.01564 0.00763 0.0339 0.4292 0.6119
-1.750 -0.1373 0.01579 0.00832 0.0327 0.4170 0.7797
-1.500 -0.1037 0.01618 0.00854 0.0330 0.4073 0.8338
-1.250 -0.0709 0.01651 0.00871 0.0331 0.3973 0.8633
-1.000 -0.0406 0.01681 0.00879 0.0335 0.3889 0.8859
-0.750 -0.0042 0.01712 0.00892 0.0326 0.3799 0.9025
-0.500 0.0361 0.01739 0.00898 0.0310 0.3710 0.9161
-0.250 0.0753 0.01764 0.00904 0.0294 0.3628 0.9295
0.000 0.1156 0.01786 0.00910 0.0275 0.3545 0.9431
0.250 0.1617 0.01808 0.00909 0.0244 0.3474 0.9557
0.500 0.2094 0.01820 0.00910 0.0209 0.3388 0.9663
0.750 0.2520 0.01828 0.00898 0.0181 0.3323 0.9756
1.000 0.2920 0.01838 0.00899 0.0158 0.3256 0.9838
1.250 0.3326 0.01841 0.00891 0.0132 0.3191 0.9901
1.500 0.3705 0.01846 0.00878 0.0111 0.3140 0.9960
1.750 0.4049 0.01856 0.00884 0.0097 0.3083 1.0000
2.000 0.4286 0.01872 0.00896 0.0102 0.3035 1.0000
2.250 0.4523 0.01888 0.00903 0.0109 0.2993 1.0000
2.500 0.4758 0.01908 0.00909 0.0115 0.2958 1.0000
2.750 0.4997 0.01932 0.00935 0.0121 0.2914 1.0000
3.000 0.5234 0.01957 0.00960 0.0126 0.2870 1.0000
3.250 0.5468 0.01981 0.00978 0.0133 0.2831 1.0000
3.500 0.5699 0.02005 0.00992 0.0141 0.2798 1.0000
3.750 0.5931 0.02038 0.01021 0.0147 0.2767 1.0000
4.000 0.6162 0.02075 0.01066 0.0153 0.2727 1.0000
4.250 0.6391 0.02110 0.01101 0.0160 0.2689 1.0000
4.500 0.6618 0.02141 0.01128 0.0168 0.2656 1.0000
4.750 0.6843 0.02172 0.01150 0.0176 0.2628 1.0000
5.000 0.7065 0.02216 0.01195 0.0184 0.2599 1.0000
5.250 0.7284 0.02268 0.01257 0.0191 0.2564 1.0000
5.500 0.7500 0.02315 0.01309 0.0199 0.2531 1.0000
5.750 0.7716 0.02356 0.01351 0.0208 0.2501 1.0000
6.000 0.7931 0.02393 0.01382 0.0217 0.2475 1.0000
6.250 0.8147 0.02434 0.01414 0.0227 0.2453 1.0000
6.500 0.8341 0.02506 0.01504 0.0235 0.2422 1.0000
6.750 0.8534 0.02576 0.01586 0.0245 0.2391 1.0000
7.000 0.8728 0.02636 0.01652 0.0255 0.2363 1.0000
7.250 0.8925 0.02686 0.01703 0.0265 0.2337 1.0000
7.500 0.9127 0.02729 0.01743 0.0276 0.2315 1.0000
7.750 0.9334 0.02774 0.01780 0.0287 0.2296 1.0000
8.000 0.9477 0.02881 0.01911 0.0298 0.2267 1.0000
8.250 0.9622 0.02982 0.02028 0.0310 0.2240 1.0000
8.500 0.9774 0.03069 0.02126 0.0323 0.2214 1.0000
8.750 0.9938 0.03139 0.02200 0.0335 0.2191 1.0000
9.000 1.0121 0.03193 0.02253 0.0346 0.2171 1.0000
9.250 1.0320 0.03238 0.02293 0.0356 0.2153 1.0000
9.500 1.0435 0.03355 0.02422 0.0369 0.2131 1.0000
9.750 1.0458 0.03537 0.02631 0.0385 0.2105 1.0000
10.000 1.0484 0.03711 0.02823 0.0398 0.2081 1.0000
10.250 1.0528 0.03863 0.02987 0.0411 0.2058 1.0000
10.500 1.0610 0.03980 0.03110 0.0422 0.2038 1.0000
10.750 1.0763 0.04051 0.03180 0.0431 0.2021 1.0000
11.000 1.0998 0.04075 0.03198 0.0438 0.2006 1.0000
12.500 0.6996 0.11405 0.10622 0.0092 0.1627 1.0000
12.750 0.7152 0.11512 0.10730 0.0093 0.1616 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 78 14.47% (mh78-il)