MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.56 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh106-il-1000000.txt Download as CSV file: xf-mh106-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 106 13.07%
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7052 0.13312 0.13147 0.0199 1.0000 0.0053
-14.500 -0.7541 0.11366 0.11188 0.0107 1.0000 0.0046
-14.250 -0.7862 0.10058 0.09867 0.0032 1.0000 0.0045
-14.000 -0.8098 0.09062 0.08860 -0.0029 1.0000 0.0045
-13.750 -0.8294 0.08217 0.08004 -0.0083 1.0000 0.0045
-13.500 -0.8603 0.07199 0.06969 -0.0150 1.0000 0.0044
-13.250 -0.8713 0.06608 0.06368 -0.0190 1.0000 0.0044
-13.000 -0.8986 0.05777 0.05517 -0.0245 1.0000 0.0043
-12.750 -0.9101 0.05269 0.04995 -0.0276 1.0000 0.0043
-12.500 -0.9457 0.04495 0.04191 -0.0309 1.0000 0.0041
-12.250 -0.9619 0.04063 0.03739 -0.0315 1.0000 0.0040
-12.000 -1.0035 0.03410 0.03036 -0.0296 1.0000 0.0037
-11.750 -1.0151 0.03123 0.02728 -0.0270 1.0000 0.0037
-11.500 -1.0168 0.02948 0.02538 -0.0243 1.0000 0.0037
-11.250 -1.0170 0.02791 0.02369 -0.0213 1.0000 0.0037
-11.000 -1.0165 0.02643 0.02207 -0.0179 1.0000 0.0038
-10.750 -1.0126 0.02501 0.02050 -0.0148 1.0000 0.0038
-10.500 -1.0036 0.02361 0.01897 -0.0124 1.0000 0.0038
-10.250 -0.9909 0.02249 0.01775 -0.0104 1.0000 0.0039
-10.000 -0.9770 0.02139 0.01655 -0.0085 1.0000 0.0040
-9.750 -0.9619 0.02035 0.01541 -0.0067 1.0000 0.0040
-9.500 -0.9452 0.01944 0.01441 -0.0051 1.0000 0.0042
-9.250 -0.9279 0.01855 0.01343 -0.0036 1.0000 0.0043
-9.000 -0.9097 0.01772 0.01253 -0.0021 1.0000 0.0044
-8.750 -0.8901 0.01703 0.01177 -0.0008 1.0000 0.0047
-8.500 -0.8694 0.01644 0.01112 0.0004 1.0000 0.0048
-8.250 -0.8467 0.01604 0.01069 0.0013 1.0000 0.0050
-8.000 -0.8292 0.01513 0.00970 0.0030 1.0000 0.0050
-7.750 -0.8138 0.01404 0.00850 0.0052 1.0000 0.0053
-7.500 -0.7939 0.01341 0.00781 0.0066 1.0000 0.0056
-7.250 -0.7680 0.01290 0.00728 0.0068 0.9955 0.0058
-7.000 -0.7267 0.01231 0.00664 0.0037 0.9620 0.0063
-6.750 -0.6933 0.01194 0.00607 0.0026 0.8872 0.0066
-6.500 -0.6719 0.01173 0.00565 0.0041 0.8375 0.0070
-6.250 -0.6484 0.01152 0.00527 0.0051 0.8006 0.0073
-6.000 -0.6255 0.01110 0.00472 0.0061 0.7711 0.0088
-5.750 -0.6010 0.01082 0.00432 0.0069 0.7456 0.0110
-5.500 -0.5777 0.01035 0.00384 0.0078 0.7223 0.0234
-5.250 -0.5544 0.00987 0.00344 0.0086 0.7010 0.0512
-5.000 -0.5318 0.00930 0.00304 0.0095 0.6802 0.0991
-4.750 -0.5091 0.00876 0.00270 0.0103 0.6611 0.1573
-4.500 -0.4848 0.00838 0.00246 0.0110 0.6432 0.2046
-4.250 -0.4595 0.00811 0.00229 0.0114 0.6265 0.2409
-4.000 -0.4335 0.00792 0.00214 0.0118 0.6105 0.2698
-3.750 -0.4073 0.00775 0.00202 0.0121 0.5953 0.2982
-3.500 -0.3804 0.00765 0.00191 0.0124 0.5803 0.3183
-3.250 -0.3538 0.00752 0.00181 0.0127 0.5658 0.3422
-3.000 -0.3269 0.00742 0.00172 0.0130 0.5518 0.3641
-2.750 -0.2998 0.00734 0.00163 0.0132 0.5390 0.3809
-2.250 -0.2454 0.00720 0.00148 0.0136 0.5152 0.4146
-2.000 -0.2181 0.00713 0.00142 0.0138 0.5044 0.4323
-1.750 -0.1907 0.00708 0.00136 0.0140 0.4939 0.4507
-1.500 -0.1637 0.00701 0.00131 0.0142 0.4836 0.4703
-1.250 -0.1364 0.00693 0.00127 0.0144 0.4744 0.4922
-1.000 -0.1094 0.00687 0.00124 0.0146 0.4661 0.5152
-0.750 -0.0823 0.00679 0.00121 0.0149 0.4581 0.5410
-0.500 -0.0555 0.00672 0.00119 0.0151 0.4507 0.5685
-0.250 -0.0287 0.00663 0.00117 0.0155 0.4435 0.5985
0.000 -0.0022 0.00657 0.00117 0.0158 0.4372 0.6292
0.250 0.0245 0.00648 0.00117 0.0161 0.4311 0.6599
0.500 0.0506 0.00642 0.00119 0.0166 0.4252 0.6920
0.750 0.0771 0.00635 0.00121 0.0170 0.4202 0.7229
1.000 0.1034 0.00628 0.00123 0.0175 0.4148 0.7538
1.250 0.1293 0.00625 0.00127 0.0180 0.4094 0.7853
1.500 0.1558 0.00619 0.00131 0.0185 0.4050 0.8149
1.750 0.1823 0.00615 0.00136 0.0189 0.4001 0.8442
2.000 0.2090 0.00617 0.00142 0.0193 0.3949 0.8711
2.250 0.2370 0.00615 0.00149 0.0195 0.3909 0.8963
2.500 0.2671 0.00618 0.00157 0.0192 0.3863 0.9176
2.750 0.2990 0.00628 0.00167 0.0185 0.3812 0.9346
3.000 0.3332 0.00636 0.00177 0.0173 0.3767 0.9465
3.250 0.3660 0.00645 0.00186 0.0163 0.3716 0.9563
3.500 0.4007 0.00659 0.00197 0.0149 0.3660 0.9627
3.750 0.4321 0.00668 0.00207 0.0143 0.3615 0.9696
4.000 0.4698 0.00678 0.00217 0.0123 0.3557 0.9721
4.250 0.5057 0.00692 0.00229 0.0105 0.3498 0.9754
4.500 0.5389 0.00700 0.00239 0.0095 0.3444 0.9798
4.750 0.5729 0.00713 0.00250 0.0082 0.3381 0.9829
5.000 0.6104 0.00721 0.00259 0.0061 0.3314 0.9846
5.250 0.6471 0.00732 0.00269 0.0042 0.3234 0.9867
5.500 0.6831 0.00741 0.00279 0.0024 0.3153 0.9892
5.750 0.7179 0.00755 0.00291 0.0009 0.3054 0.9921
6.000 0.7537 0.00770 0.00303 -0.0009 0.2933 0.9943
6.250 0.7920 0.00783 0.00314 -0.0032 0.2782 0.9963
6.500 0.8294 0.00803 0.00328 -0.0055 0.2571 0.9985
6.750 0.8637 0.00834 0.00349 -0.0071 0.2316 1.0000
7.000 0.8856 0.00866 0.00372 -0.0062 0.2112 1.0000
7.250 0.9071 0.00902 0.00400 -0.0052 0.1888 1.0000
7.500 0.9281 0.00944 0.00432 -0.0041 0.1674 1.0000
7.750 0.9496 0.00980 0.00462 -0.0031 0.1507 1.0000
8.000 0.9707 0.01018 0.00494 -0.0020 0.1345 1.0000
8.250 0.9913 0.01062 0.00530 -0.0009 0.1180 1.0000
8.500 1.0117 0.01106 0.00568 0.0002 0.1037 1.0000
8.750 1.0322 0.01147 0.00606 0.0014 0.0920 1.0000
9.000 1.0525 0.01190 0.00645 0.0025 0.0811 1.0000
9.250 1.0725 0.01235 0.00686 0.0037 0.0711 1.0000
9.500 1.0918 0.01283 0.00730 0.0050 0.0615 1.0000
9.750 1.1104 0.01336 0.00778 0.0064 0.0522 1.0000
10.000 1.1295 0.01383 0.00825 0.0076 0.0455 1.0000
10.250 1.1478 0.01435 0.00875 0.0090 0.0386 1.0000
10.500 1.1648 0.01494 0.00932 0.0105 0.0325 1.0000
10.750 1.1829 0.01544 0.00983 0.0119 0.0284 1.0000
11.000 1.1986 0.01608 0.01046 0.0136 0.0238 1.0000
11.250 1.2146 0.01668 0.01106 0.0152 0.0204 1.0000
11.500 1.2291 0.01734 0.01173 0.0169 0.0173 1.0000
11.750 1.2421 0.01805 0.01245 0.0188 0.0145 1.0000
12.000 1.2542 0.01877 0.01322 0.0208 0.0123 1.0000
12.250 1.2637 0.01958 0.01404 0.0230 0.0105 1.0000
12.500 1.2664 0.02039 0.01490 0.0264 0.0091 1.0000
12.750 1.2700 0.02130 0.01586 0.0292 0.0083 1.0000
13.000 1.2718 0.02258 0.01719 0.0312 0.0074 1.0000
13.250 1.2728 0.02430 0.01900 0.0324 0.0065 1.0000
13.500 1.2778 0.02604 0.02082 0.0327 0.0061 1.0000
13.750 1.2793 0.02836 0.02321 0.0325 0.0053 1.0000
14.000 1.2803 0.03096 0.02590 0.0320 0.0050 1.0000
14.250 1.2758 0.03432 0.02936 0.0310 0.0045 1.0000
14.500 1.2767 0.03714 0.03228 0.0302 0.0044 1.0000
14.750 1.2747 0.04031 0.03554 0.0292 0.0041 1.0000
15.000 1.2728 0.04348 0.03880 0.0282 0.0038 1.0000
15.250 1.2655 0.04733 0.04276 0.0270 0.0037 1.0000
15.500 1.2601 0.05097 0.04647 0.0258 0.0035 1.0000
15.750 1.2494 0.05530 0.05090 0.0243 0.0034 1.0000
16.000 1.2351 0.06014 0.05585 0.0226 0.0032 1.0000
16.250 1.2269 0.06437 0.06016 0.0211 0.0031 1.0000
16.500 1.2017 0.07118 0.06711 0.0183 0.0030 1.0000
16.750 1.1939 0.07563 0.07165 0.0166 0.0029 1.0000
17.000 1.1809 0.08095 0.07708 0.0144 0.0029 1.0000
17.250 1.1727 0.08560 0.08181 0.0126 0.0029 1.0000
17.500 1.1597 0.09111 0.08743 0.0103 0.0027 1.0000
17.750 1.1512 0.09599 0.09239 0.0083 0.0028 1.0000
18.000 1.1334 0.10245 0.09896 0.0055 0.0027 1.0000
18.250 1.1214 0.10809 0.10469 0.0031 0.0028 1.0000
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Polar data table (+)
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