MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.15 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh82-il-1000000-n5.txt Download as CSV file: xf-mh82-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 82 13.31%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6855 0.03988 0.03675 -0.0255 0.6093 0.0052
-9.250 -0.6985 0.03270 0.02905 -0.0262 0.6030 0.0052
-8.750 -0.6699 0.02785 0.02363 -0.0254 0.5823 0.0053
-8.500 -0.6544 0.02532 0.02077 -0.0248 0.5723 0.0053
-8.250 -0.6368 0.02304 0.01816 -0.0242 0.5619 0.0053
-8.000 -0.6149 0.02165 0.01653 -0.0236 0.5519 0.0053
-7.750 -0.5927 0.02018 0.01482 -0.0230 0.5413 0.0053
-7.500 -0.5691 0.01897 0.01340 -0.0225 0.5314 0.0053
-7.250 -0.5448 0.01789 0.01212 -0.0220 0.5215 0.0053
-7.000 -0.5198 0.01694 0.01099 -0.0216 0.5117 0.0053
-6.750 -0.4942 0.01609 0.00997 -0.0211 0.5027 0.0053
-6.500 -0.4683 0.01529 0.00902 -0.0207 0.4924 0.0054
-6.250 -0.4419 0.01464 0.00824 -0.0203 0.4836 0.0054
-6.000 -0.4153 0.01400 0.00748 -0.0200 0.4741 0.0054
-5.750 -0.3882 0.01348 0.00686 -0.0196 0.4653 0.0055
-5.500 -0.3610 0.01301 0.00628 -0.0193 0.4558 0.0055
-5.250 -0.3335 0.01257 0.00576 -0.0190 0.4485 0.0056
-5.000 -0.3058 0.01220 0.00531 -0.0188 0.4401 0.0057
-4.750 -0.2779 0.01187 0.00492 -0.0185 0.4321 0.0057
-4.500 -0.2499 0.01159 0.00456 -0.0183 0.4232 0.0058
-4.250 -0.2217 0.01132 0.00423 -0.0181 0.4160 0.0060
-4.000 -0.1934 0.01108 0.00394 -0.0179 0.4085 0.0061
-3.750 -0.1651 0.01086 0.00366 -0.0178 0.4020 0.0062
-3.500 -0.1366 0.01066 0.00341 -0.0176 0.3949 0.0064
-3.250 -0.1082 0.01049 0.00318 -0.0175 0.3874 0.0067
-3.000 -0.0796 0.01032 0.00297 -0.0173 0.3803 0.0070
-2.750 -0.0509 0.01020 0.00279 -0.0172 0.3730 0.0073
-2.500 -0.0224 0.01002 0.00259 -0.0171 0.3676 0.0081
-2.250 0.0064 0.00991 0.00245 -0.0170 0.3613 0.0089
-2.000 0.0351 0.00982 0.00232 -0.0169 0.3553 0.0100
-1.750 0.0639 0.00971 0.00220 -0.0168 0.3497 0.0119
-1.500 0.0926 0.00963 0.00209 -0.0167 0.3430 0.0155
-1.250 0.1213 0.00954 0.00201 -0.0167 0.3373 0.0226
-1.000 0.1500 0.00941 0.00192 -0.0166 0.3322 0.0385
-0.750 0.1783 0.00922 0.00184 -0.0166 0.3268 0.0741
-0.500 0.2066 0.00904 0.00180 -0.0165 0.3223 0.1195
-0.250 0.2351 0.00889 0.00177 -0.0165 0.3175 0.1625
0.000 0.2631 0.00867 0.00175 -0.0165 0.3121 0.2357
0.250 0.2911 0.00846 0.00174 -0.0165 0.3072 0.3130
0.500 0.3192 0.00825 0.00174 -0.0165 0.3033 0.3920
0.750 0.3471 0.00806 0.00175 -0.0165 0.2990 0.4703
1.000 0.3749 0.00789 0.00178 -0.0164 0.2948 0.5533
1.250 0.4024 0.00769 0.00181 -0.0162 0.2912 0.6419
1.500 0.4291 0.00745 0.00185 -0.0158 0.2876 0.7380
1.750 0.4548 0.00729 0.00192 -0.0151 0.2834 0.8237
2.000 0.4807 0.00726 0.00201 -0.0144 0.2795 0.8769
2.250 0.5071 0.00729 0.00208 -0.0138 0.2765 0.9101
2.500 0.5333 0.00731 0.00215 -0.0130 0.2739 0.9426
2.750 0.5645 0.00738 0.00221 -0.0134 0.2705 0.9685
3.000 0.6004 0.00749 0.00228 -0.0149 0.2663 0.9831
3.250 0.6386 0.00762 0.00236 -0.0170 0.2624 0.9912
3.500 0.6764 0.00770 0.00242 -0.0190 0.2601 0.9967
3.750 0.7116 0.00780 0.00249 -0.0205 0.2573 1.0000
4.000 0.7376 0.00792 0.00258 -0.0201 0.2543 1.0000
4.250 0.7638 0.00806 0.00268 -0.0197 0.2511 1.0000
4.500 0.7901 0.00821 0.00280 -0.0193 0.2478 1.0000
4.750 0.8169 0.00831 0.00290 -0.0190 0.2461 1.0000
5.000 0.8439 0.00843 0.00300 -0.0188 0.2440 1.0000
5.250 0.8710 0.00856 0.00312 -0.0186 0.2414 1.0000
5.500 0.8982 0.00871 0.00324 -0.0185 0.2384 1.0000
5.750 0.9254 0.00887 0.00339 -0.0184 0.2355 1.0000
6.000 0.9527 0.00903 0.00353 -0.0183 0.2331 1.0000
6.250 0.9802 0.00916 0.00367 -0.0183 0.2314 1.0000
6.500 1.0078 0.00930 0.00381 -0.0183 0.2292 1.0000
6.750 1.0352 0.00945 0.00397 -0.0182 0.2264 1.0000
7.000 1.0626 0.00963 0.00413 -0.0182 0.2239 1.0000
7.250 1.0898 0.00982 0.00431 -0.0182 0.2213 1.0000
7.500 1.1170 0.01001 0.00450 -0.0182 0.2189 1.0000
7.750 1.1444 0.01016 0.00467 -0.0182 0.2170 1.0000
8.000 1.1717 0.01032 0.00485 -0.0183 0.2146 1.0000
8.250 1.1988 0.01051 0.00505 -0.0183 0.2121 1.0000
8.500 1.2256 0.01072 0.00526 -0.0183 0.2096 1.0000
8.750 1.2522 0.01097 0.00550 -0.0183 0.2065 1.0000
9.000 1.2790 0.01116 0.00572 -0.0183 0.2044 1.0000
9.250 1.3058 0.01135 0.00594 -0.0183 0.2022 1.0000
9.500 1.3323 0.01157 0.00618 -0.0183 0.1994 1.0000
9.750 1.3584 0.01182 0.00644 -0.0182 0.1963 1.0000
10.000 1.3840 0.01212 0.00673 -0.0182 0.1930 1.0000
10.250 1.4101 0.01234 0.00700 -0.0181 0.1907 1.0000
10.500 1.4359 0.01259 0.00727 -0.0181 0.1878 1.0000
10.750 1.4611 0.01288 0.00757 -0.0180 0.1844 1.0000
11.000 1.4855 0.01323 0.00793 -0.0179 0.1807 1.0000
11.250 1.5104 0.01351 0.00825 -0.0177 0.1780 1.0000
11.500 1.5350 0.01381 0.00858 -0.0176 0.1746 1.0000
11.750 1.5586 0.01418 0.00896 -0.0174 0.1708 1.0000
12.000 1.5812 0.01461 0.00940 -0.0171 0.1671 1.0000
12.250 1.6046 0.01494 0.00978 -0.0168 0.1640 1.0000
12.500 1.6267 0.01535 0.01021 -0.0164 0.1601 1.0000
12.750 1.6468 0.01588 0.01075 -0.0159 0.1557 1.0000
13.000 1.6676 0.01632 0.01123 -0.0154 0.1525 1.0000
13.250 1.6869 0.01682 0.01176 -0.0148 0.1485 1.0000
13.500 1.7027 0.01749 0.01245 -0.0138 0.1440 1.0000
13.750 1.7177 0.01810 0.01310 -0.0127 0.1401 1.0000
14.000 1.7235 0.01893 0.01395 -0.0105 0.1353 1.0000
14.250 1.7258 0.02012 0.01517 -0.0085 0.1311 1.0000
14.500 1.7309 0.02141 0.01650 -0.0074 0.1261 1.0000
14.750 1.7292 0.02341 0.01851 -0.0064 0.1200 1.0000
15.000 1.7281 0.02562 0.02075 -0.0059 0.1130 1.0000
15.250 1.7232 0.02835 0.02352 -0.0058 0.1072 1.0000
15.500 1.7173 0.03134 0.02654 -0.0059 0.1018 1.0000
15.750 1.7099 0.03463 0.02989 -0.0062 0.0980 1.0000
16.000 1.7040 0.03787 0.03320 -0.0067 0.0949 1.0000
16.250 1.6907 0.04199 0.03739 -0.0075 0.0913 1.0000
16.500 1.6582 0.04838 0.04382 -0.0090 0.0829 1.0000
16.750 1.6578 0.05129 0.04684 -0.0097 0.0844 1.0000
17.000 1.6235 0.05840 0.05400 -0.0119 0.0785 1.0000
17.250 1.6139 0.06271 0.05842 -0.0133 0.0782 1.0000
17.500 1.5874 0.06937 0.06515 -0.0156 0.0735 1.0000
17.750 1.5593 0.07651 0.07236 -0.0184 0.0701 1.0000
18.000 1.5462 0.08170 0.07765 -0.0204 0.0688 1.0000
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Polar data table (+)
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