MH 81 13% (mh81-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 81 13% (mh81-il) Reynolds number: 500,000 Max Cl/Cd: 88.34 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh81-il-500000-n5.txt Download as CSV file: xf-mh81-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 81 13%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4704 0.08570 0.08258 0.0079 0.6291 0.0088
-8.500 -0.6528 0.03788 0.03397 -0.0155 0.6551 0.0069
-8.250 -0.6503 0.03354 0.02918 -0.0147 0.6436 0.0069
-8.000 -0.6411 0.02997 0.02516 -0.0137 0.6323 0.0068
-7.750 -0.6260 0.02733 0.02211 -0.0128 0.6199 0.0068
-7.500 -0.6079 0.02511 0.01952 -0.0119 0.6074 0.0068
-7.250 -0.5875 0.02324 0.01731 -0.0111 0.5957 0.0068
-7.000 -0.5651 0.02180 0.01558 -0.0104 0.5834 0.0068
-6.750 -0.5416 0.02051 0.01402 -0.0097 0.5712 0.0068
-6.500 -0.5172 0.01941 0.01270 -0.0091 0.5596 0.0068
-6.250 -0.4922 0.01845 0.01153 -0.0085 0.5484 0.0069
-6.000 -0.4666 0.01761 0.01051 -0.0080 0.5367 0.0069
-5.750 -0.4409 0.01682 0.00957 -0.0075 0.5260 0.0070
-5.500 -0.4153 0.01600 0.00860 -0.0070 0.5155 0.0071
-5.250 -0.3892 0.01532 0.00782 -0.0065 0.5048 0.0072
-5.000 -0.3626 0.01477 0.00716 -0.0061 0.4947 0.0073
-4.750 -0.3357 0.01430 0.00661 -0.0058 0.4846 0.0075
-4.500 -0.3086 0.01388 0.00611 -0.0054 0.4752 0.0077
-4.000 -0.2539 0.01314 0.00521 -0.0048 0.4558 0.0082
-3.750 -0.2263 0.01282 0.00480 -0.0045 0.4473 0.0087
-3.500 -0.1985 0.01253 0.00444 -0.0042 0.4390 0.0091
-3.250 -0.1709 0.01224 0.00408 -0.0040 0.4303 0.0098
-3.000 -0.1429 0.01201 0.00380 -0.0038 0.4216 0.0106
-2.750 -0.1148 0.01182 0.00353 -0.0036 0.4132 0.0118
-2.500 -0.0867 0.01162 0.00330 -0.0034 0.4056 0.0137
-2.250 -0.0586 0.01145 0.00309 -0.0032 0.3981 0.0174
-2.000 -0.0306 0.01124 0.00290 -0.0030 0.3912 0.0268
-1.750 -0.0029 0.01101 0.00272 -0.0028 0.3834 0.0474
-1.500 0.0246 0.01071 0.00258 -0.0027 0.3764 0.0920
-1.250 0.0522 0.01047 0.00248 -0.0026 0.3690 0.1379
-1.000 0.0797 0.01023 0.00240 -0.0024 0.3628 0.1931
-0.750 0.1071 0.00996 0.00233 -0.0023 0.3569 0.2595
-0.500 0.1335 0.00955 0.00227 -0.0021 0.3507 0.3724
-0.250 0.1592 0.00911 0.00222 -0.0018 0.3450 0.5013
0.000 0.1848 0.00874 0.00219 -0.0012 0.3388 0.6110
0.250 0.2088 0.00838 0.00220 -0.0003 0.3329 0.7295
0.500 0.2327 0.00818 0.00229 0.0011 0.3282 0.8241
0.750 0.2586 0.00817 0.00236 0.0020 0.3232 0.8741
1.000 0.2856 0.00824 0.00241 0.0026 0.3180 0.9031
1.250 0.3135 0.00833 0.00247 0.0030 0.3133 0.9234
1.500 0.3426 0.00842 0.00251 0.0031 0.3081 0.9390
1.750 0.3735 0.00853 0.00257 0.0028 0.3030 0.9557
2.000 0.4085 0.00867 0.00264 0.0016 0.2985 0.9711
2.250 0.4491 0.00877 0.00271 -0.0008 0.2941 0.9800
2.500 0.4895 0.00890 0.00277 -0.0033 0.2891 0.9857
2.750 0.5286 0.00904 0.00283 -0.0055 0.2842 0.9901
3.000 0.5648 0.00914 0.00290 -0.0072 0.2804 0.9941
3.250 0.6010 0.00924 0.00296 -0.0089 0.2766 0.9969
3.500 0.6355 0.00936 0.00303 -0.0103 0.2726 0.9995
3.750 0.6624 0.00952 0.00314 -0.0101 0.2689 1.0000
4.000 0.6872 0.00963 0.00325 -0.0095 0.2659 1.0000
4.250 0.7120 0.00975 0.00336 -0.0089 0.2628 1.0000
4.500 0.7369 0.00989 0.00348 -0.0083 0.2598 1.0000
4.750 0.7616 0.01006 0.00361 -0.0077 0.2567 1.0000
5.000 0.7863 0.01025 0.00377 -0.0072 0.2535 1.0000
5.250 0.8115 0.01039 0.00391 -0.0066 0.2509 1.0000
5.500 0.8368 0.01054 0.00407 -0.0062 0.2481 1.0000
5.750 0.8621 0.01071 0.00424 -0.0057 0.2453 1.0000
6.000 0.8874 0.01090 0.00441 -0.0052 0.2425 1.0000
6.250 0.9126 0.01111 0.00461 -0.0048 0.2394 1.0000
6.500 0.9382 0.01130 0.00481 -0.0045 0.2368 1.0000
6.750 0.9642 0.01147 0.00500 -0.0042 0.2343 1.0000
7.000 0.9901 0.01166 0.00521 -0.0039 0.2317 1.0000
7.250 1.0160 0.01188 0.00543 -0.0037 0.2290 1.0000
7.500 1.0418 0.01212 0.00567 -0.0035 0.2260 1.0000
7.750 1.0674 0.01238 0.00593 -0.0032 0.2232 1.0000
8.000 1.0937 0.01257 0.00617 -0.0031 0.2210 1.0000
8.250 1.1197 0.01279 0.00643 -0.0029 0.2185 1.0000
8.500 1.1455 0.01303 0.00669 -0.0028 0.2156 1.0000
8.750 1.1710 0.01331 0.00698 -0.0026 0.2126 1.0000
9.000 1.1960 0.01363 0.00730 -0.0024 0.2097 1.0000
9.250 1.2218 0.01387 0.00760 -0.0023 0.2075 1.0000
9.500 1.2473 0.01412 0.00791 -0.0021 0.2047 1.0000
9.750 1.2723 0.01441 0.00823 -0.0019 0.2015 1.0000
10.000 1.2968 0.01474 0.00859 -0.0017 0.1984 1.0000
10.250 1.3207 0.01511 0.00898 -0.0015 0.1955 1.0000
10.500 1.3456 0.01540 0.00934 -0.0013 0.1927 1.0000
10.750 1.3697 0.01572 0.00972 -0.0011 0.1894 1.0000
11.000 1.3929 0.01611 0.01014 -0.0008 0.1860 1.0000
11.250 1.4148 0.01658 0.01062 -0.0004 0.1825 1.0000
11.500 1.4381 0.01692 0.01105 -0.0001 0.1796 1.0000
11.750 1.4602 0.01733 0.01152 0.0003 0.1760 1.0000
12.000 1.4807 0.01783 0.01206 0.0008 0.1723 1.0000
12.250 1.4998 0.01839 0.01265 0.0014 0.1690 1.0000
12.500 1.5199 0.01886 0.01321 0.0019 0.1657 1.0000
12.750 1.5373 0.01945 0.01385 0.0027 0.1617 1.0000
13.000 1.5506 0.02020 0.01464 0.0038 0.1580 1.0000
13.250 1.5608 0.02092 0.01544 0.0054 0.1550 1.0000
13.500 1.5694 0.02182 0.01642 0.0068 0.1516 1.0000
13.750 1.5753 0.02307 0.01772 0.0078 0.1481 1.0000
14.000 1.5782 0.02473 0.01943 0.0085 0.1448 1.0000
14.250 1.5864 0.02615 0.02095 0.0088 0.1413 1.0000
14.500 1.5901 0.02807 0.02293 0.0089 0.1371 1.0000
14.750 1.5881 0.03063 0.02555 0.0087 0.1333 1.0000
15.000 1.5898 0.03296 0.02796 0.0084 0.1291 1.0000
15.250 1.5861 0.03592 0.03099 0.0079 0.1247 1.0000
15.500 1.5763 0.03961 0.03474 0.0071 0.1208 1.0000
15.750 1.5703 0.04298 0.03819 0.0062 0.1165 1.0000
16.000 1.5591 0.04703 0.04232 0.0051 0.1129 1.0000
16.250 1.5430 0.05173 0.04708 0.0037 0.1095 1.0000
16.500 1.5311 0.05606 0.05150 0.0023 0.1058 1.0000
16.750 1.5148 0.06113 0.05665 0.0004 0.1024 1.0000
17.000 1.4954 0.06684 0.06242 -0.0018 0.0990 1.0000
17.250 1.4811 0.07200 0.06767 -0.0039 0.0954 1.0000
17.500 1.4641 0.07769 0.07343 -0.0063 0.0922 1.0000
17.750 1.4440 0.08396 0.07977 -0.0091 0.0890 1.0000
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Polar data table (+)
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