MH 81 13% (mh81-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 81 13% (mh81-il) Reynolds number: 100,000 Max Cl/Cd: 40.99 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh81-il-100000-n5.txt Download as CSV file: xf-mh81-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4273 0.08816 0.08412 -0.0011 1.0000 0.0244
-8.500 -0.4237 0.08423 0.08026 -0.0035 1.0000 0.0241
-8.250 -0.4203 0.07969 0.07572 -0.0076 0.8949 0.0237
-8.000 -0.4261 0.07459 0.07052 -0.0115 0.8429 0.0234
-7.750 -0.4367 0.06950 0.06531 -0.0148 0.8124 0.0228
-7.250 -0.4706 0.05141 0.04636 -0.0221 0.7801 0.0207
-6.750 -0.4578 0.04387 0.03804 -0.0213 0.7453 0.0205
-6.500 -0.4469 0.04022 0.03390 -0.0206 0.7295 0.0204
-6.250 -0.4328 0.03681 0.02993 -0.0197 0.7145 0.0204
-6.000 -0.4155 0.03385 0.02641 -0.0186 0.6998 0.0205
-5.750 -0.3955 0.03133 0.02334 -0.0175 0.6856 0.0208
-5.500 -0.3733 0.03008 0.02194 -0.0169 0.6710 0.0217
-5.000 -0.3260 0.02697 0.01801 -0.0151 0.6434 0.0242
-4.750 -0.3012 0.02564 0.01647 -0.0144 0.6299 0.0253
-4.500 -0.2760 0.02446 0.01509 -0.0137 0.6171 0.0262
-4.250 -0.2506 0.02331 0.01372 -0.0128 0.6050 0.0273
-4.000 -0.2245 0.02227 0.01246 -0.0120 0.5921 0.0287
-3.750 -0.1994 0.02142 0.01157 -0.0114 0.5803 0.0308
-3.500 -0.1740 0.02072 0.01071 -0.0107 0.5693 0.0344
-3.250 -0.1481 0.02005 0.00992 -0.0101 0.5572 0.0388
-3.000 -0.1226 0.01938 0.00917 -0.0094 0.5464 0.0446
-2.750 -0.0971 0.01871 0.00850 -0.0087 0.5359 0.0565
-2.500 -0.0717 0.01796 0.00792 -0.0081 0.5252 0.0879
-2.250 -0.0470 0.01725 0.00749 -0.0075 0.5161 0.1655
-2.000 -0.0219 0.01662 0.00723 -0.0071 0.5053 0.2568
-1.750 0.0009 0.01580 0.00701 -0.0062 0.4965 0.4082
-1.500 0.0212 0.01483 0.00696 -0.0042 0.4871 0.6318
-1.250 0.0558 0.01457 0.00715 -0.0032 0.4774 0.8298
-1.000 0.0952 0.01472 0.00711 -0.0043 0.4673 0.9016
-0.750 0.1352 0.01488 0.00703 -0.0059 0.4575 0.9402
-0.500 0.1840 0.01500 0.00684 -0.0094 0.4480 0.9655
-0.250 0.2382 0.01506 0.00666 -0.0144 0.4367 0.9869
0.000 0.2836 0.01511 0.00644 -0.0179 0.4282 1.0000
0.250 0.3075 0.01522 0.00641 -0.0172 0.4205 1.0000
0.500 0.3311 0.01535 0.00634 -0.0165 0.4143 1.0000
0.750 0.3552 0.01549 0.00639 -0.0159 0.4068 1.0000
1.000 0.3792 0.01565 0.00639 -0.0152 0.4003 1.0000
1.250 0.4031 0.01583 0.00643 -0.0144 0.3945 1.0000
1.500 0.4273 0.01603 0.00655 -0.0138 0.3880 1.0000
1.750 0.4513 0.01623 0.00661 -0.0131 0.3825 1.0000
2.000 0.4755 0.01646 0.00674 -0.0125 0.3768 1.0000
2.250 0.4998 0.01669 0.00691 -0.0118 0.3708 1.0000
2.500 0.5239 0.01692 0.00702 -0.0111 0.3658 1.0000
2.750 0.5482 0.01720 0.00722 -0.0105 0.3610 1.0000
3.000 0.5725 0.01748 0.00748 -0.0100 0.3555 1.0000
3.250 0.5968 0.01775 0.00766 -0.0093 0.3508 1.0000
3.500 0.6210 0.01804 0.00784 -0.0087 0.3466 1.0000
3.750 0.6453 0.01838 0.00821 -0.0082 0.3412 1.0000
4.000 0.6697 0.01870 0.00850 -0.0076 0.3367 1.0000
4.250 0.6941 0.01901 0.00873 -0.0070 0.3330 1.0000
4.500 0.7184 0.01939 0.00908 -0.0065 0.3288 1.0000
4.750 0.7427 0.01978 0.00951 -0.0061 0.3240 1.0000
5.000 0.7672 0.02013 0.00985 -0.0056 0.3198 1.0000
5.250 0.7919 0.02048 0.01012 -0.0051 0.3165 1.0000
5.500 0.8162 0.02093 0.01061 -0.0047 0.3127 1.0000
5.750 0.8403 0.02140 0.01115 -0.0043 0.3083 1.0000
6.000 0.8646 0.02181 0.01158 -0.0039 0.3044 1.0000
6.250 0.8894 0.02218 0.01190 -0.0035 0.3011 1.0000
6.500 0.9135 0.02268 0.01241 -0.0031 0.2978 1.0000
6.750 0.9368 0.02328 0.01316 -0.0028 0.2937 1.0000
7.000 0.9605 0.02378 0.01372 -0.0024 0.2899 1.0000
7.250 0.9848 0.02421 0.01414 -0.0020 0.2866 1.0000
7.500 1.0096 0.02463 0.01451 -0.0017 0.2839 1.0000
7.750 1.0310 0.02540 0.01549 -0.0013 0.2799 1.0000
8.000 1.0531 0.02608 0.01629 -0.0010 0.2762 1.0000
8.250 1.0760 0.02662 0.01690 -0.0006 0.2728 1.0000
8.500 1.1001 0.02707 0.01733 -0.0002 0.2699 1.0000
8.750 1.1222 0.02775 0.01807 0.0002 0.2669 1.0000
9.000 1.1407 0.02872 0.01929 0.0006 0.2631 1.0000
9.250 1.1607 0.02951 0.02020 0.0011 0.2596 1.0000
9.500 1.1825 0.03008 0.02082 0.0015 0.2565 1.0000
9.750 1.2064 0.03052 0.02125 0.0019 0.2539 1.0000
10.000 1.2220 0.03166 0.02260 0.0025 0.2505 1.0000
10.250 1.2352 0.03291 0.02408 0.0032 0.2469 1.0000
10.500 1.2515 0.03383 0.02512 0.0038 0.2436 1.0000
10.750 1.2720 0.03441 0.02575 0.0044 0.2407 1.0000
11.000 1.2967 0.03478 0.02608 0.0047 0.2383 1.0000
11.250 1.2941 0.03694 0.02859 0.0060 0.2346 1.0000
11.500 1.2942 0.03878 0.03064 0.0072 0.2311 1.0000
11.750 1.2982 0.04014 0.03212 0.0085 0.2282 1.0000
12.000 1.3157 0.04070 0.03271 0.0092 0.2256 1.0000
12.250 1.3296 0.04160 0.03364 0.0099 0.2231 1.0000
12.500 1.2585 0.04974 0.04216 0.0087 0.2192 1.0000
12.750 1.1440 0.06677 0.05940 0.0005 0.2118 1.0000
13.000 1.1903 0.06334 0.05601 0.0031 0.2110 1.0000
13.250 1.2528 0.05819 0.05086 0.0066 0.2100 1.0000
16.750 0.9737 0.15804 0.15157 -0.0419 0.1328 1.0000
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Polar data table (+)
Polar graphs
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