MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 100,000 Max Cl/Cd: 63.01 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh116-il-100000.txt Download as CSV file: xf-mh116-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 116 9.84%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3411 0.10974 0.10510 -0.0421 1.0000 0.0790
-8.750 -0.3574 0.10879 0.10428 -0.0422 1.0000 0.0794
-8.500 -0.3762 0.10796 0.10358 -0.0410 1.0000 0.0795
-8.250 -0.3400 0.10049 0.09602 -0.0370 1.0000 0.0824
-8.000 -0.3428 0.09853 0.09413 -0.0347 1.0000 0.0842
-7.750 -0.3518 0.09695 0.09263 -0.0323 1.0000 0.0860
-7.500 -0.3649 0.09567 0.09145 -0.0298 1.0000 0.0874
-7.250 -0.3813 0.09463 0.09051 -0.0271 1.0000 0.0885
-7.000 -0.4023 0.09386 0.08984 -0.0241 1.0000 0.0897
-6.750 -0.4230 0.09275 0.08883 -0.0228 1.0000 0.0910
-6.500 -0.4472 0.09070 0.08690 -0.0302 1.0000 0.0928
-6.250 -0.4529 0.08677 0.08301 -0.0326 1.0000 0.0935
-6.000 -0.4508 0.08421 0.08048 -0.0264 1.0000 0.0948
-5.750 -0.4498 0.08191 0.07822 -0.0236 1.0000 0.0966
-5.500 -0.4281 0.07771 0.07398 -0.0287 0.9955 0.1016
-5.250 -0.3967 0.07038 0.06651 -0.0426 0.9879 0.1091
-5.000 -0.3677 0.06659 0.06267 -0.0464 0.9828 0.1155
-4.750 -0.3129 0.04541 0.04022 -0.0682 0.9783 0.0512
-4.500 -0.2765 0.03959 0.03387 -0.0733 0.9739 0.0480
-4.250 -0.2332 0.03470 0.02815 -0.0782 0.9705 0.0490
-4.000 -0.1962 0.03110 0.02377 -0.0806 0.9659 0.0502
-3.750 -0.1579 0.02841 0.02035 -0.0824 0.9612 0.0523
-3.500 -0.1166 0.02661 0.01817 -0.0850 0.9573 0.0660
-3.250 -0.0851 0.02508 0.01667 -0.0860 0.9515 0.0876
-3.000 -0.0485 0.02395 0.01553 -0.0879 0.9462 0.1271
-2.750 -0.0095 0.02325 0.01487 -0.0902 0.9416 0.1780
-2.500 0.0188 0.02276 0.01457 -0.0908 0.9343 0.2260
-2.250 0.0586 0.02226 0.01429 -0.0934 0.9298 0.2958
-2.000 0.0844 0.02189 0.01418 -0.0934 0.9222 0.3674
-1.750 0.1199 0.02140 0.01414 -0.0949 0.9171 0.4795
-1.500 0.1443 0.02101 0.01428 -0.0941 0.9101 0.6211
-1.250 0.1653 0.02040 0.01437 -0.0911 0.9042 0.8595
-1.000 0.2082 0.02046 0.01415 -0.0944 0.8977 1.0000
-0.750 0.2429 0.02071 0.01410 -0.0961 0.8908 1.0000
-0.500 0.2763 0.02099 0.01415 -0.0975 0.8840 1.0000
-0.250 0.3098 0.02123 0.01420 -0.0988 0.8769 1.0000
0.000 0.3419 0.02151 0.01430 -0.0999 0.8699 1.0000
0.250 0.3760 0.02171 0.01437 -0.1012 0.8629 1.0000
0.500 0.4064 0.02200 0.01454 -0.1019 0.8554 1.0000
0.750 0.4429 0.02211 0.01454 -0.1035 0.8488 1.0000
1.000 0.4713 0.02240 0.01476 -0.1038 0.8406 1.0000
1.250 0.5114 0.02236 0.01466 -0.1059 0.8346 1.0000
1.500 0.5387 0.02264 0.01490 -0.1059 0.8259 1.0000
1.750 0.5817 0.02246 0.01468 -0.1083 0.8205 1.0000
2.000 0.6077 0.02272 0.01493 -0.1080 0.8111 1.0000
2.250 0.6506 0.02239 0.01460 -0.1100 0.8061 1.0000
2.500 0.6749 0.02266 0.01489 -0.1094 0.7958 1.0000
2.750 0.7203 0.02212 0.01437 -0.1116 0.7914 1.0000
3.000 0.7438 0.02235 0.01462 -0.1107 0.7803 1.0000
3.250 0.7742 0.02229 0.01461 -0.1106 0.7711 1.0000
3.500 0.8143 0.02176 0.01416 -0.1118 0.7643 1.0000
3.750 0.8408 0.02178 0.01424 -0.1111 0.7532 1.0000
4.000 0.8717 0.02157 0.01410 -0.1109 0.7430 1.0000
4.250 0.9129 0.02084 0.01346 -0.1120 0.7352 1.0000
4.500 0.9406 0.02067 0.01337 -0.1112 0.7225 1.0000
4.750 0.9695 0.02042 0.01320 -0.1106 0.7094 1.0000
5.000 0.9992 0.02010 0.01296 -0.1100 0.6956 1.0000
5.250 1.0295 0.01972 0.01270 -0.1094 0.6809 1.0000
5.500 1.0590 0.01938 0.01243 -0.1086 0.6648 1.0000
5.750 1.0820 0.01930 0.01245 -0.1071 0.6452 1.0000
6.000 1.1101 0.01900 0.01220 -0.1061 0.6255 1.0000
6.250 1.1328 0.01892 0.01226 -0.1045 0.6021 1.0000
6.500 1.1559 0.01884 0.01223 -0.1028 0.5763 1.0000
6.750 1.1768 0.01886 0.01229 -0.1009 0.5465 1.0000
7.000 1.1966 0.01899 0.01238 -0.0988 0.5129 1.0000
7.250 1.2123 0.01933 0.01269 -0.0962 0.4732 1.0000
7.500 1.2260 0.01988 0.01310 -0.0934 0.4297 1.0000
7.750 1.2364 0.02069 0.01372 -0.0902 0.3827 1.0000
8.000 1.2445 0.02175 0.01461 -0.0869 0.3366 1.0000
8.250 1.2505 0.02298 0.01560 -0.0835 0.2932 1.0000
8.500 1.2555 0.02433 0.01674 -0.0801 0.2542 1.0000
8.750 1.2580 0.02574 0.01791 -0.0764 0.2213 1.0000
9.000 1.2606 0.02722 0.01923 -0.0729 0.1914 1.0000
9.250 1.2627 0.02879 0.02065 -0.0696 0.1647 1.0000
9.500 1.2645 0.03050 0.02225 -0.0664 0.1403 1.0000
9.750 1.2666 0.03236 0.02408 -0.0634 0.1174 1.0000
10.000 1.2674 0.03454 0.02613 -0.0606 0.0973 1.0000
10.250 1.2698 0.03683 0.02840 -0.0579 0.0795 1.0000
10.500 1.2727 0.03919 0.03072 -0.0556 0.0658 1.0000
10.750 1.2784 0.04170 0.03326 -0.0535 0.0546 1.0000
11.000 1.2850 0.04437 0.03608 -0.0517 0.0456 1.0000
11.250 1.3018 0.04778 0.03946 -0.0506 0.0389 1.0000
11.500 1.3046 0.05012 0.04213 -0.0486 0.0347 1.0000
11.750 1.3110 0.05286 0.04495 -0.0472 0.0314 1.0000
12.000 1.3275 0.05841 0.05078 -0.0465 0.0295 1.0000
12.250 1.3242 0.06203 0.05478 -0.0446 0.0291 1.0000
12.500 1.3159 0.06602 0.05915 -0.0429 0.0287 1.0000
12.750 1.3043 0.07026 0.06374 -0.0416 0.0285 1.0000
13.000 1.2903 0.07483 0.06863 -0.0408 0.0285 1.0000
13.250 1.2741 0.07973 0.07383 -0.0407 0.0285 1.0000
13.500 1.2563 0.08505 0.07943 -0.0412 0.0285 1.0000
13.750 1.2370 0.09078 0.08541 -0.0425 0.0286 1.0000
14.000 1.2178 0.09697 0.09183 -0.0445 0.0288 1.0000
14.250 1.1979 0.10362 0.09869 -0.0473 0.0290 1.0000
14.500 1.1787 0.11076 0.10600 -0.0507 0.0293 1.0000
14.750 1.1603 0.11840 0.11379 -0.0547 0.0296 1.0000
15.000 1.1441 0.12575 0.12133 -0.0594 0.0300 1.0000
15.250 1.0675 0.15292 0.14884 -0.0808 0.0355 1.0000
15.500 1.0523 0.16474 0.16062 -0.0874 0.0377 1.0000
15.750 1.0465 0.17325 0.16908 -0.0918 0.0386 1.0000
16.000 1.0442 0.18052 0.17631 -0.0954 0.0392 1.0000
16.250 0.8404 0.19688 0.19327 -0.0925 0.1000 1.0000
16.500 0.8303 0.20124 0.19762 -0.0963 0.0997 1.0000
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Polar data table (+)
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