MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 500,000 Max Cl/Cd: 72.3 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh64-il-500000-n5.txt Download as CSV file: xf-mh64-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 64 8.59%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5774 0.10585 0.10370 0.0172 1.0000 0.0089
-9.500 -0.5772 0.10117 0.09904 0.0150 1.0000 0.0084
-9.250 -0.5774 0.09640 0.09429 0.0126 1.0000 0.0080
-9.000 -0.5786 0.09147 0.08939 0.0099 1.0000 0.0076
-8.750 -0.5867 0.08349 0.08147 0.0063 1.0000 0.0051
-8.500 -0.5926 0.07807 0.07608 0.0029 1.0000 0.0050
-8.250 -0.6015 0.07224 0.07031 -0.0012 1.0000 0.0049
-8.000 -0.6119 0.06547 0.06356 -0.0080 1.0000 0.0049
-7.750 -0.6176 0.05528 0.05323 -0.0164 1.0000 0.0048
-7.500 -0.6199 0.04751 0.04522 -0.0201 1.0000 0.0046
-7.250 -0.6171 0.04076 0.03814 -0.0220 1.0000 0.0044
-7.000 -0.6070 0.03434 0.03126 -0.0232 0.9705 0.0041
-6.750 -0.5944 0.02829 0.02457 -0.0229 0.9327 0.0038
-6.500 -0.5822 0.02322 0.01877 -0.0208 0.9115 0.0035
-6.250 -0.5632 0.02040 0.01545 -0.0193 0.8964 0.0033
-6.000 -0.5412 0.01852 0.01320 -0.0182 0.8835 0.0032
-5.750 -0.5179 0.01709 0.01144 -0.0173 0.8720 0.0032
-5.500 -0.4938 0.01587 0.00999 -0.0165 0.8612 0.0032
-5.250 -0.4691 0.01479 0.00871 -0.0158 0.8508 0.0031
-5.000 -0.4442 0.01380 0.00755 -0.0152 0.8409 0.0032
-4.750 -0.4189 0.01296 0.00655 -0.0146 0.8314 0.0032
-4.500 -0.3931 0.01224 0.00569 -0.0141 0.8217 0.0033
-4.250 -0.3669 0.01160 0.00492 -0.0137 0.8122 0.0034
-4.000 -0.3404 0.01111 0.00430 -0.0133 0.8031 0.0035
-3.750 -0.3135 0.01069 0.00374 -0.0129 0.7938 0.0038
-3.500 -0.2862 0.01035 0.00328 -0.0127 0.7844 0.0042
-3.250 -0.2588 0.01007 0.00289 -0.0124 0.7753 0.0050
-3.000 -0.2316 0.00972 0.00251 -0.0121 0.7659 0.0130
-2.750 -0.2052 0.00915 0.00218 -0.0119 0.7562 0.0691
-2.500 -0.1797 0.00844 0.00193 -0.0118 0.7468 0.1822
-2.250 -0.1528 0.00815 0.00175 -0.0116 0.7373 0.2347
-2.000 -0.1258 0.00785 0.00162 -0.0115 0.7272 0.2950
-1.750 -0.0985 0.00762 0.00151 -0.0114 0.7172 0.3415
-1.500 -0.0711 0.00746 0.00141 -0.0112 0.7069 0.3813
-1.250 -0.0438 0.00731 0.00132 -0.0111 0.6962 0.4204
-1.000 -0.0163 0.00717 0.00124 -0.0110 0.6846 0.4593
-0.750 0.0110 0.00703 0.00117 -0.0108 0.6725 0.4999
-0.500 0.0382 0.00689 0.00113 -0.0106 0.6598 0.5430
-0.250 0.0651 0.00675 0.00109 -0.0103 0.6464 0.5900
0.000 0.0917 0.00660 0.00105 -0.0100 0.6323 0.6430
0.250 0.1178 0.00644 0.00104 -0.0095 0.6172 0.7023
0.500 0.1430 0.00626 0.00104 -0.0088 0.6013 0.7696
0.750 0.1676 0.00607 0.00105 -0.0078 0.5841 0.8457
1.000 0.2012 0.00599 0.00108 -0.0086 0.5636 0.9275
1.250 0.2488 0.00607 0.00109 -0.0129 0.5387 0.9747
1.500 0.2863 0.00620 0.00111 -0.0150 0.5142 0.9955
1.750 0.3165 0.00635 0.00116 -0.0155 0.4902 1.0000
2.000 0.3431 0.00651 0.00121 -0.0153 0.4662 1.0000
2.250 0.3697 0.00667 0.00127 -0.0150 0.4421 1.0000
2.500 0.3963 0.00686 0.00135 -0.0148 0.4178 1.0000
2.750 0.4229 0.00704 0.00146 -0.0146 0.3951 1.0000
3.000 0.4496 0.00724 0.00157 -0.0144 0.3725 1.0000
3.250 0.4763 0.00743 0.00169 -0.0142 0.3507 1.0000
3.500 0.5029 0.00765 0.00183 -0.0141 0.3286 1.0000
3.750 0.5297 0.00786 0.00199 -0.0139 0.3077 1.0000
4.000 0.5563 0.00811 0.00216 -0.0137 0.2854 1.0000
4.250 0.5828 0.00836 0.00234 -0.0136 0.2634 1.0000
4.500 0.6093 0.00862 0.00253 -0.0134 0.2414 1.0000
4.750 0.6357 0.00891 0.00275 -0.0133 0.2203 1.0000
5.000 0.6621 0.00921 0.00301 -0.0131 0.1976 1.0000
5.250 0.6883 0.00953 0.00327 -0.0130 0.1762 1.0000
5.500 0.7143 0.00988 0.00355 -0.0128 0.1552 1.0000
5.750 0.7402 0.01024 0.00386 -0.0126 0.1348 1.0000
6.000 0.7661 0.01062 0.00418 -0.0124 0.1172 1.0000
6.250 0.7915 0.01106 0.00454 -0.0122 0.0962 1.0000
6.500 0.8167 0.01154 0.00494 -0.0120 0.0764 1.0000
6.750 0.8420 0.01198 0.00538 -0.0118 0.0624 1.0000
7.000 0.8670 0.01246 0.00583 -0.0115 0.0489 1.0000
7.250 0.8908 0.01313 0.00639 -0.0112 0.0298 1.0000
7.500 0.9146 0.01378 0.00698 -0.0109 0.0173 1.0000
7.750 0.9385 0.01439 0.00758 -0.0105 0.0111 1.0000
8.000 0.9626 0.01494 0.00817 -0.0101 0.0082 1.0000
8.250 0.9858 0.01563 0.00891 -0.0097 0.0050 1.0000
8.500 1.0083 0.01643 0.00977 -0.0091 0.0034 1.0000
8.750 1.0300 0.01733 0.01080 -0.0084 0.0028 1.0000
9.000 1.0515 0.01819 0.01185 -0.0078 0.0025 1.0000
9.250 1.0721 0.01914 0.01293 -0.0070 0.0023 1.0000
9.500 1.0916 0.02015 0.01408 -0.0062 0.0022 1.0000
9.750 1.1098 0.02128 0.01536 -0.0053 0.0021 1.0000
10.000 1.1265 0.02248 0.01672 -0.0043 0.0020 1.0000
10.250 1.1412 0.02385 0.01824 -0.0031 0.0019 1.0000
10.500 1.1540 0.02528 0.01983 -0.0018 0.0019 1.0000
10.750 1.1646 0.02679 0.02151 -0.0003 0.0019 1.0000
11.000 1.1716 0.02847 0.02336 0.0014 0.0018 1.0000
11.250 1.1725 0.03012 0.02516 0.0039 0.0018 1.0000
11.500 1.1704 0.03208 0.02729 0.0059 0.0018 1.0000
11.750 1.1669 0.03448 0.02987 0.0072 0.0018 1.0000
12.000 1.1626 0.03726 0.03282 0.0077 0.0018 1.0000
12.250 1.1574 0.04040 0.03617 0.0077 0.0018 1.0000
12.500 1.1522 0.04383 0.03977 0.0069 0.0018 1.0000
12.750 1.1439 0.04798 0.04410 0.0055 0.0018 1.0000
13.000 1.1343 0.05269 0.04898 0.0034 0.0017 1.0000
13.250 1.1254 0.05767 0.05411 0.0007 0.0017 1.0000
13.500 1.1090 0.06429 0.06092 -0.0030 0.0017 1.0000
13.750 1.0944 0.07101 0.06780 -0.0069 0.0018 1.0000
14.000 1.0777 0.07846 0.07540 -0.0113 0.0018 1.0000
14.250 1.0644 0.08552 0.08258 -0.0155 0.0017 1.0000
14.500 1.0388 0.09552 0.09276 -0.0212 0.0018 1.0000
14.750 1.0167 0.10521 0.10256 -0.0266 0.0018 1.0000
15.000 0.9977 0.11460 0.11206 -0.0317 0.0019 1.0000
15.250 0.9784 0.12443 0.12200 -0.0370 0.0019 1.0000
15.500 0.9559 0.13561 0.13329 -0.0428 0.0020 1.0000
15.750 0.9316 0.14801 0.14579 -0.0491 0.0020 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 64 8.59% (mh64-il)