MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 500,000 Max Cl/Cd: 81.46 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh20-il-500000-n5.txt Download as CSV file: xf-mh20-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5294 0.08584 0.08391 -0.0027 1.0000 0.0083
-8.500 -0.5255 0.07984 0.07791 -0.0079 0.9349 0.0078
-8.250 -0.5327 0.07546 0.07340 -0.0103 0.8797 0.0079
-8.000 -0.5418 0.07150 0.06935 -0.0124 0.8507 0.0077
-7.750 -0.5439 0.06720 0.06495 -0.0149 0.8325 0.0076
-7.500 -0.5393 0.06491 0.06255 -0.0155 0.8184 0.0067
-7.250 -0.5452 0.05818 0.05567 -0.0186 0.8057 0.0063
-7.000 -0.5447 0.05170 0.04898 -0.0205 0.7952 0.0060
-6.750 -0.5408 0.04521 0.04222 -0.0212 0.7859 0.0057
-6.500 -0.5356 0.03830 0.03492 -0.0208 0.7782 0.0053
-6.250 -0.5297 0.03085 0.02688 -0.0190 0.7709 0.0047
-6.000 -0.5200 0.02406 0.01925 -0.0163 0.7643 0.0041
-5.750 -0.4996 0.02143 0.01616 -0.0150 0.7571 0.0039
-5.500 -0.4769 0.01961 0.01398 -0.0140 0.7506 0.0038
-5.250 -0.4531 0.01815 0.01224 -0.0132 0.7441 0.0037
-5.000 -0.4286 0.01687 0.01071 -0.0125 0.7383 0.0036
-4.750 -0.4036 0.01571 0.00929 -0.0118 0.7322 0.0036
-4.500 -0.3786 0.01464 0.00801 -0.0111 0.7269 0.0036
-4.250 -0.3534 0.01366 0.00688 -0.0105 0.7213 0.0036
-4.000 -0.3282 0.01279 0.00586 -0.0098 0.7160 0.0036
-3.750 -0.3029 0.01202 0.00494 -0.0092 0.7111 0.0036
-3.500 -0.2770 0.01139 0.00418 -0.0087 0.7059 0.0037
-3.250 -0.2507 0.01091 0.00355 -0.0082 0.7010 0.0039
-3.000 -0.2237 0.01056 0.00308 -0.0079 0.6957 0.0043
-2.750 -0.1966 0.01028 0.00270 -0.0076 0.6900 0.0050
-2.500 -0.1696 0.01002 0.00235 -0.0073 0.6847 0.0099
-2.250 -0.1441 0.00946 0.00207 -0.0070 0.6790 0.0719
-2.000 -0.1183 0.00908 0.00190 -0.0067 0.6738 0.1320
-1.750 -0.0928 0.00860 0.00176 -0.0065 0.6684 0.2216
-1.500 -0.0665 0.00831 0.00164 -0.0062 0.6630 0.2831
-1.250 -0.0401 0.00806 0.00153 -0.0060 0.6580 0.3399
-1.000 -0.0144 0.00771 0.00142 -0.0057 0.6525 0.4236
-0.750 0.0102 0.00732 0.00134 -0.0052 0.6475 0.5244
-0.500 0.0330 0.00685 0.00128 -0.0042 0.6424 0.6465
-0.250 0.0543 0.00637 0.00124 -0.0026 0.6370 0.7742
0.000 0.0951 0.00606 0.00130 -0.0050 0.6316 0.9071
0.250 0.1557 0.00614 0.00136 -0.0120 0.6247 0.9473
0.500 0.1898 0.00623 0.00139 -0.0132 0.6186 0.9640
0.750 0.2226 0.00630 0.00143 -0.0142 0.6117 0.9760
1.000 0.2577 0.00637 0.00144 -0.0158 0.6047 0.9840
1.250 0.2969 0.00641 0.00145 -0.0183 0.5963 0.9906
1.500 0.3445 0.00644 0.00145 -0.0227 0.5872 0.9982
1.750 0.3771 0.00647 0.00145 -0.0238 0.5776 1.0000
2.000 0.4032 0.00651 0.00145 -0.0234 0.5668 1.0000
2.250 0.4293 0.00655 0.00147 -0.0231 0.5548 1.0000
2.500 0.4554 0.00661 0.00149 -0.0228 0.5403 1.0000
2.750 0.4815 0.00669 0.00153 -0.0225 0.5227 1.0000
3.000 0.5073 0.00681 0.00161 -0.0222 0.5008 1.0000
3.250 0.5332 0.00696 0.00168 -0.0219 0.4758 1.0000
3.500 0.5589 0.00716 0.00179 -0.0216 0.4496 1.0000
3.750 0.5845 0.00738 0.00193 -0.0213 0.4244 1.0000
4.000 0.6100 0.00761 0.00211 -0.0210 0.4001 1.0000
4.250 0.6354 0.00786 0.00229 -0.0207 0.3755 1.0000
4.500 0.6608 0.00812 0.00249 -0.0204 0.3513 1.0000
4.750 0.6859 0.00842 0.00271 -0.0200 0.3244 1.0000
5.000 0.7107 0.00875 0.00296 -0.0197 0.2930 1.0000
5.250 0.7349 0.00918 0.00324 -0.0193 0.2560 1.0000
5.500 0.7577 0.00982 0.00362 -0.0189 0.1973 1.0000
5.750 0.7786 0.01074 0.00419 -0.0183 0.1238 1.0000
6.000 0.7989 0.01168 0.00479 -0.0176 0.0625 1.0000
6.250 0.8207 0.01234 0.00531 -0.0169 0.0337 1.0000
6.500 0.8413 0.01313 0.00595 -0.0160 0.0097 1.0000
6.750 0.8631 0.01373 0.00656 -0.0152 0.0037 1.0000
7.000 0.8853 0.01425 0.00716 -0.0143 0.0029 1.0000
7.250 0.9069 0.01481 0.00781 -0.0134 0.0025 1.0000
7.500 0.9276 0.01547 0.00857 -0.0124 0.0022 1.0000
7.750 0.9468 0.01627 0.00949 -0.0112 0.0020 1.0000
8.000 0.9652 0.01710 0.01043 -0.0099 0.0020 1.0000
8.250 0.9813 0.01813 0.01159 -0.0083 0.0019 1.0000
8.500 0.9964 0.01920 0.01285 -0.0067 0.0018 1.0000
8.750 1.0081 0.02055 0.01434 -0.0046 0.0018 1.0000
9.000 1.0196 0.02185 0.01577 -0.0025 0.0018 1.0000
9.250 1.0302 0.02318 0.01725 -0.0004 0.0018 1.0000
9.500 1.0387 0.02470 0.01891 0.0020 0.0018 1.0000
9.750 1.0474 0.02607 0.02042 0.0042 0.0018 1.0000
10.000 1.0493 0.02776 0.02228 0.0073 0.0018 1.0000
10.250 1.0518 0.02943 0.02411 0.0099 0.0018 1.0000
10.500 1.0523 0.03157 0.02644 0.0122 0.0018 1.0000
10.750 1.0538 0.03364 0.02870 0.0140 0.0018 1.0000
11.000 1.0571 0.03547 0.03068 0.0153 0.0018 1.0000
11.250 1.0544 0.03817 0.03358 0.0165 0.0018 1.0000
11.500 1.0481 0.04139 0.03702 0.0174 0.0018 1.0000
11.750 1.0441 0.04436 0.04018 0.0178 0.0018 1.0000
12.000 1.0364 0.04794 0.04395 0.0177 0.0018 1.0000
12.250 1.0323 0.05116 0.04732 0.0172 0.0018 1.0000
12.500 1.0191 0.05587 0.05223 0.0161 0.0018 1.0000
12.750 1.0101 0.06020 0.05672 0.0145 0.0018 1.0000
13.000 0.9963 0.06558 0.06228 0.0122 0.0018 1.0000
13.250 0.9815 0.07156 0.06843 0.0093 0.0019 1.0000
13.500 0.9708 0.07728 0.07429 0.0061 0.0019 1.0000
13.750 0.9540 0.08477 0.08192 0.0018 0.0019 1.0000
14.000 0.9381 0.09262 0.08992 -0.0027 0.0019 1.0000
14.250 0.9211 0.10128 0.09871 -0.0077 0.0019 1.0000
14.500 0.9051 0.11016 0.10769 -0.0126 0.0019 1.0000
14.750 0.8815 0.12174 0.11939 -0.0186 0.0020 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 20 9.01% (mh20-il)