MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.79 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh116-il-1000000.txt Download as CSV file: xf-mh116-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3354 0.11235 0.11072 -0.0377 1.0000 0.0086
-10.250 -0.3345 0.10926 0.10765 -0.0380 1.0000 0.0088
-10.000 -0.3336 0.10640 0.10481 -0.0380 1.0000 0.0090
-9.750 -0.3328 0.10343 0.10187 -0.0383 0.9999 0.0090
-9.500 -0.3205 0.09878 0.09722 -0.0424 0.9989 0.0091
-9.250 -0.3079 0.09412 0.09257 -0.0467 0.9975 0.0091
-9.000 -0.2953 0.08924 0.08768 -0.0515 0.9956 0.0091
-8.750 -0.2971 0.08141 0.07988 -0.0579 0.9924 0.0096
-8.500 -0.2834 0.07803 0.07651 -0.0618 0.9888 0.0099
-8.250 -0.2685 0.07385 0.07233 -0.0670 0.9851 0.0102
-8.000 -0.2550 0.06939 0.06787 -0.0726 0.9796 0.0105
-7.750 -0.2419 0.06440 0.06289 -0.0793 0.9711 0.0108
-7.500 -0.2198 0.05690 0.05537 -0.0924 0.9612 0.0110
-7.250 -0.1919 0.04492 0.04326 -0.1124 0.9467 0.0113
-7.000 -0.1830 0.03409 0.03203 -0.1214 0.9263 0.0116
-6.750 -0.1724 0.02912 0.02668 -0.1229 0.9109 0.0123
-6.000 -0.1272 0.01478 0.01055 -0.1216 0.8778 0.0076
-5.750 -0.1035 0.01231 0.00758 -0.1207 0.8700 0.0060
-5.500 -0.0772 0.01171 0.00684 -0.1204 0.8624 0.0059
-5.250 -0.0506 0.01113 0.00616 -0.1201 0.8553 0.0058
-5.000 -0.0247 0.01030 0.00517 -0.1198 0.8480 0.0057
-4.750 0.0016 0.00953 0.00426 -0.1196 0.8409 0.0057
-4.500 0.0285 0.00899 0.00359 -0.1194 0.8338 0.0057
-4.250 0.0558 0.00853 0.00301 -0.1193 0.8269 0.0058
-4.000 0.0832 0.00810 0.00242 -0.1191 0.8201 0.0064
-3.750 0.1110 0.00782 0.00208 -0.1190 0.8133 0.0085
-3.500 0.1380 0.00733 0.00176 -0.1189 0.8065 0.0534
-3.250 0.1656 0.00712 0.00163 -0.1189 0.7998 0.0789
-3.000 0.1932 0.00696 0.00151 -0.1189 0.7930 0.1042
-2.750 0.2209 0.00679 0.00141 -0.1190 0.7863 0.1359
-2.500 0.2484 0.00661 0.00133 -0.1190 0.7794 0.1767
-2.250 0.2761 0.00646 0.00127 -0.1191 0.7728 0.2140
-2.000 0.3038 0.00632 0.00121 -0.1191 0.7657 0.2521
-1.750 0.3316 0.00622 0.00116 -0.1191 0.7589 0.2853
-1.500 0.3592 0.00611 0.00112 -0.1191 0.7515 0.3265
-1.250 0.3869 0.00600 0.00110 -0.1191 0.7441 0.3686
-1.000 0.4144 0.00591 0.00108 -0.1191 0.7364 0.4147
-0.750 0.4420 0.00578 0.00108 -0.1191 0.7286 0.4732
-0.500 0.4692 0.00567 0.00109 -0.1190 0.7210 0.5367
-0.250 0.4967 0.00553 0.00111 -0.1190 0.7130 0.6010
0.000 0.5236 0.00542 0.00114 -0.1189 0.7054 0.6694
0.250 0.5503 0.00529 0.00119 -0.1186 0.6971 0.7395
0.500 0.5761 0.00519 0.00124 -0.1181 0.6891 0.8072
0.750 0.5996 0.00509 0.00130 -0.1169 0.6806 0.8769
1.000 0.6216 0.00499 0.00132 -0.1153 0.6723 0.9479
1.250 0.6569 0.00501 0.00130 -0.1170 0.6635 1.0000
1.500 0.6843 0.00509 0.00134 -0.1169 0.6540 1.0000
1.750 0.7118 0.00516 0.00138 -0.1168 0.6442 1.0000
2.000 0.7389 0.00526 0.00143 -0.1167 0.6343 1.0000
2.250 0.7659 0.00537 0.00148 -0.1165 0.6235 1.0000
2.500 0.7930 0.00546 0.00154 -0.1164 0.6119 1.0000
2.750 0.8200 0.00557 0.00162 -0.1163 0.5994 1.0000
3.000 0.8467 0.00569 0.00170 -0.1161 0.5860 1.0000
3.250 0.8732 0.00582 0.00179 -0.1158 0.5722 1.0000
3.500 0.8995 0.00597 0.00188 -0.1156 0.5567 1.0000
3.750 0.9254 0.00614 0.00201 -0.1152 0.5401 1.0000
4.000 0.9515 0.00631 0.00213 -0.1149 0.5218 1.0000
4.250 0.9764 0.00655 0.00227 -0.1145 0.4983 1.0000
4.500 1.0011 0.00681 0.00244 -0.1139 0.4716 1.0000
4.750 1.0253 0.00710 0.00264 -0.1133 0.4432 1.0000
5.000 1.0487 0.00747 0.00286 -0.1126 0.4084 1.0000
5.250 1.0715 0.00787 0.00312 -0.1118 0.3744 1.0000
5.500 1.0938 0.00832 0.00340 -0.1109 0.3374 1.0000
5.750 1.1163 0.00874 0.00369 -0.1101 0.3063 1.0000
6.000 1.1384 0.00920 0.00402 -0.1092 0.2747 1.0000
6.250 1.1572 0.00989 0.00444 -0.1078 0.2236 1.0000
6.500 1.1754 0.01061 0.00490 -0.1063 0.1757 1.0000
6.750 1.1945 0.01126 0.00534 -0.1050 0.1401 1.0000
7.000 1.2150 0.01177 0.00575 -0.1039 0.1163 1.0000
7.250 1.2355 0.01227 0.00615 -0.1028 0.0972 1.0000
7.500 1.2546 0.01286 0.00661 -0.1015 0.0762 1.0000
7.750 1.2731 0.01347 0.00712 -0.1000 0.0562 1.0000
8.000 1.2914 0.01406 0.00763 -0.0986 0.0418 1.0000
8.250 1.3087 0.01469 0.00818 -0.0970 0.0279 1.0000
8.500 1.3231 0.01548 0.00886 -0.0949 0.0140 1.0000
8.750 1.3300 0.01659 0.00990 -0.0913 0.0028 1.0000
9.000 1.3454 0.01713 0.01051 -0.0893 0.0025 1.0000
9.250 1.3586 0.01783 0.01127 -0.0869 0.0021 1.0000
9.500 1.3692 0.01871 0.01225 -0.0842 0.0019 1.0000
9.750 1.3794 0.01962 0.01329 -0.0815 0.0018 1.0000
10.000 1.3875 0.02069 0.01447 -0.0787 0.0017 1.0000
10.250 1.3956 0.02178 0.01566 -0.0760 0.0017 1.0000
10.500 1.4040 0.02287 0.01684 -0.0735 0.0017 1.0000
10.750 1.4107 0.02411 0.01819 -0.0709 0.0017 1.0000
11.000 1.4160 0.02550 0.01969 -0.0684 0.0017 1.0000
11.250 1.4211 0.02697 0.02126 -0.0660 0.0017 1.0000
11.500 1.4240 0.02867 0.02308 -0.0636 0.0017 1.0000
11.750 1.4256 0.03056 0.02509 -0.0612 0.0017 1.0000
12.000 1.4264 0.03263 0.02729 -0.0591 0.0017 1.0000
12.250 1.4270 0.03481 0.02959 -0.0572 0.0017 1.0000
12.500 1.4248 0.03739 0.03230 -0.0553 0.0017 1.0000
12.750 1.4220 0.04016 0.03521 -0.0537 0.0017 1.0000
13.000 1.4183 0.04317 0.03838 -0.0523 0.0017 1.0000
13.250 1.4129 0.04652 0.04188 -0.0511 0.0017 1.0000
13.500 1.4016 0.05084 0.04639 -0.0500 0.0017 1.0000
13.750 1.3997 0.05403 0.04970 -0.0496 0.0017 1.0000
14.000 1.3971 0.05742 0.05323 -0.0495 0.0017 1.0000
14.250 1.3935 0.06111 0.05705 -0.0496 0.0017 1.0000
14.500 1.3898 0.06494 0.06102 -0.0501 0.0018 1.0000
14.750 1.3845 0.06919 0.06540 -0.0508 0.0018 1.0000
15.000 1.3788 0.07369 0.07003 -0.0519 0.0018 1.0000
15.250 1.3718 0.07861 0.07509 -0.0534 0.0018 1.0000
15.500 1.3642 0.08382 0.08044 -0.0553 0.0018 1.0000
15.750 1.3557 0.08942 0.08619 -0.0575 0.0018 1.0000
16.000 1.3464 0.09541 0.09232 -0.0602 0.0018 1.0000
16.250 1.3366 0.10176 0.09880 -0.0632 0.0019 1.0000
16.500 1.3254 0.10861 0.10581 -0.0667 0.0019 1.0000
16.750 1.3140 0.11577 0.11312 -0.0706 0.0019 1.0000
17.000 1.3013 0.12348 0.12098 -0.0749 0.0019 1.0000
17.250 1.2874 0.13174 0.12939 -0.0797 0.0020 1.0000
17.500 1.2721 0.14056 0.13838 -0.0850 0.0020 1.0000
17.750 1.0546 0.15632 0.15464 -0.0940 0.0019 1.0000
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Polar data table (+)
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