MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.52 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh106-il-1000000-n5.txt Download as CSV file: xf-mh106-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9275 0.11156 0.10913 0.0100 1.0000 0.0018
-16.250 -0.9616 0.10001 0.09741 0.0035 1.0000 0.0018
-16.000 -0.9967 0.08900 0.08623 -0.0028 1.0000 0.0018
-15.750 -1.0234 0.08017 0.07726 -0.0077 1.0000 0.0018
-15.500 -1.0240 0.07606 0.07311 -0.0099 1.0000 0.0018
-15.250 -1.0486 0.06809 0.06499 -0.0144 1.0000 0.0018
-15.000 -1.0870 0.05823 0.05489 -0.0200 1.0000 0.0018
-14.750 -1.0742 0.05645 0.05310 -0.0210 1.0000 0.0018
-14.500 -1.0868 0.05090 0.04741 -0.0241 1.0000 0.0018
-14.000 -1.1046 0.04182 0.03806 -0.0285 1.0000 0.0018
-13.750 -1.1149 0.03778 0.03388 -0.0297 1.0000 0.0018
-13.500 -1.1402 0.03292 0.02876 -0.0298 1.0000 0.0019
-13.250 -1.1311 0.03165 0.02745 -0.0292 1.0000 0.0018
-13.000 -1.1484 0.02856 0.02415 -0.0268 1.0000 0.0019
-12.750 -1.1427 0.02736 0.02288 -0.0251 1.0000 0.0019
-12.500 -1.1477 0.02560 0.02098 -0.0219 1.0000 0.0020
-12.250 -1.1420 0.02459 0.01988 -0.0194 1.0000 0.0019
-12.000 -1.1386 0.02351 0.01871 -0.0162 1.0000 0.0020
-11.750 -1.1319 0.02259 0.01772 -0.0133 1.0000 0.0021
-11.500 -1.1187 0.02183 0.01689 -0.0114 1.0000 0.0021
-11.250 -1.1028 0.02115 0.01615 -0.0098 1.0000 0.0022
-11.000 -1.0867 0.02042 0.01535 -0.0082 1.0000 0.0023
-10.750 -1.0703 0.01966 0.01452 -0.0066 1.0000 0.0023
-10.500 -1.0532 0.01892 0.01370 -0.0052 1.0000 0.0024
-10.250 -1.0343 0.01828 0.01301 -0.0039 1.0000 0.0025
-10.000 -1.0151 0.01764 0.01231 -0.0026 1.0000 0.0026
-9.750 -0.9955 0.01701 0.01162 -0.0014 1.0000 0.0026
-9.500 -0.9750 0.01644 0.01099 -0.0002 1.0000 0.0027
-9.250 -0.9542 0.01587 0.01037 0.0009 1.0000 0.0027
-9.000 -0.9331 0.01533 0.00977 0.0020 1.0000 0.0028
-8.750 -0.8910 0.01469 0.00903 -0.0014 0.9305 0.0029
-8.500 -0.8710 0.01447 0.00854 0.0002 0.8511 0.0030
-8.250 -0.8496 0.01419 0.00808 0.0014 0.8088 0.0031
-8.000 -0.8273 0.01385 0.00758 0.0024 0.7772 0.0031
-7.500 -0.7813 0.01310 0.00656 0.0042 0.7229 0.0034
-7.250 -0.7572 0.01278 0.00614 0.0049 0.7013 0.0036
-7.000 -0.7327 0.01248 0.00575 0.0055 0.6819 0.0039
-6.750 -0.7077 0.01222 0.00540 0.0061 0.6629 0.0042
-6.500 -0.6823 0.01198 0.00507 0.0066 0.6448 0.0046
-6.250 -0.6567 0.01176 0.00477 0.0070 0.6270 0.0050
-6.000 -0.6314 0.01148 0.00443 0.0075 0.6112 0.0062
-5.750 -0.6056 0.01126 0.00414 0.0079 0.5968 0.0075
-5.500 -0.5798 0.01101 0.00386 0.0084 0.5831 0.0105
-5.250 -0.5541 0.01076 0.00358 0.0088 0.5697 0.0159
-5.000 -0.5283 0.01051 0.00332 0.0092 0.5558 0.0243
-4.750 -0.5026 0.01024 0.00307 0.0096 0.5427 0.0372
-4.500 -0.4778 0.00986 0.00278 0.0102 0.5306 0.0661
-4.250 -0.4543 0.00933 0.00246 0.0109 0.5203 0.1190
-4.000 -0.4303 0.00887 0.00219 0.0115 0.5102 0.1740
-3.750 -0.4052 0.00853 0.00201 0.0119 0.5001 0.2189
-3.500 -0.3787 0.00835 0.00189 0.0122 0.4906 0.2433
-3.250 -0.3523 0.00817 0.00177 0.0125 0.4807 0.2714
-3.000 -0.3256 0.00803 0.00167 0.0128 0.4709 0.2947
-2.750 -0.2982 0.00795 0.00158 0.0130 0.4628 0.3090
-2.500 -0.2707 0.00788 0.00151 0.0131 0.4548 0.3220
-2.250 -0.2431 0.00781 0.00144 0.0132 0.4480 0.3349
-2.000 -0.2155 0.00776 0.00137 0.0134 0.4408 0.3478
-1.750 -0.1879 0.00770 0.00132 0.0135 0.4343 0.3607
-1.500 -0.1603 0.00764 0.00127 0.0136 0.4272 0.3737
-1.250 -0.1327 0.00759 0.00123 0.0138 0.4213 0.3873
-1.000 -0.1050 0.00754 0.00120 0.0139 0.4158 0.4013
-0.750 -0.0774 0.00750 0.00117 0.0140 0.4104 0.4162
-0.500 -0.0496 0.00745 0.00114 0.0141 0.4056 0.4312
-0.250 -0.0220 0.00740 0.00112 0.0142 0.4003 0.4483
0.000 0.0055 0.00737 0.00111 0.0143 0.3955 0.4656
0.250 0.0331 0.00731 0.00111 0.0145 0.3913 0.4839
0.500 0.0606 0.00725 0.00111 0.0146 0.3869 0.5055
0.750 0.0880 0.00721 0.00111 0.0148 0.3824 0.5265
1.000 0.1152 0.00716 0.00112 0.0149 0.3784 0.5505
1.250 0.1425 0.00709 0.00114 0.0151 0.3743 0.5769
1.500 0.1696 0.00704 0.00116 0.0153 0.3697 0.6031
1.750 0.1964 0.00701 0.00119 0.0156 0.3652 0.6316
2.000 0.2235 0.00695 0.00123 0.0158 0.3613 0.6593
2.250 0.2503 0.00690 0.00127 0.0161 0.3569 0.6882
2.750 0.3032 0.00681 0.00137 0.0169 0.3485 0.7484
3.000 0.3295 0.00676 0.00143 0.0173 0.3439 0.7790
3.250 0.3557 0.00674 0.00149 0.0177 0.3385 0.8087
3.500 0.3820 0.00671 0.00157 0.0182 0.3337 0.8384
3.750 0.4086 0.00670 0.00165 0.0186 0.3278 0.8672
4.000 0.4360 0.00673 0.00175 0.0188 0.3216 0.8938
4.250 0.4659 0.00677 0.00186 0.0185 0.3150 0.9164
4.500 0.4986 0.00688 0.00198 0.0175 0.3075 0.9343
4.750 0.5333 0.00699 0.00211 0.0161 0.2987 0.9463
5.000 0.5665 0.00713 0.00224 0.0149 0.2889 0.9556
5.250 0.6011 0.00730 0.00238 0.0134 0.2763 0.9617
5.500 0.6308 0.00749 0.00253 0.0130 0.2620 0.9689
5.750 0.6651 0.00775 0.00272 0.0114 0.2422 0.9725
6.000 0.6961 0.00805 0.00294 0.0106 0.2217 0.9775
6.250 0.7255 0.00835 0.00317 0.0101 0.2033 0.9826
6.500 0.7605 0.00873 0.00346 0.0083 0.1816 0.9853
6.750 0.7938 0.00907 0.00373 0.0068 0.1625 0.9882
7.000 0.8248 0.00944 0.00403 0.0059 0.1442 0.9910
7.250 0.8541 0.00980 0.00432 0.0053 0.1295 0.9934
7.500 0.8857 0.01021 0.00466 0.0041 0.1119 0.9949
7.750 0.9173 0.01059 0.00498 0.0029 0.0984 0.9966
8.250 0.9798 0.01139 0.00569 0.0007 0.0751 0.9997
8.500 1.0036 0.01180 0.00607 0.0011 0.0650 1.0000
8.750 1.0244 0.01217 0.00642 0.0022 0.0576 1.0000
9.000 1.0444 0.01261 0.00683 0.0034 0.0497 1.0000
9.250 1.0639 0.01307 0.00726 0.0047 0.0425 1.0000
9.500 1.0837 0.01349 0.00767 0.0059 0.0367 1.0000
9.750 1.1022 0.01401 0.00816 0.0073 0.0303 1.0000
10.000 1.1201 0.01455 0.00868 0.0087 0.0247 1.0000
10.250 1.1378 0.01509 0.00922 0.0102 0.0200 1.0000
10.500 1.1555 0.01560 0.00974 0.0116 0.0170 1.0000
10.750 1.1725 0.01616 0.01031 0.0131 0.0144 1.0000
11.000 1.1890 0.01672 0.01088 0.0146 0.0123 1.0000
11.250 1.2043 0.01733 0.01151 0.0163 0.0101 1.0000
11.500 1.2192 0.01794 0.01215 0.0180 0.0087 1.0000
11.750 1.2318 0.01864 0.01288 0.0199 0.0072 1.0000
12.000 1.2439 0.01933 0.01361 0.0219 0.0062 1.0000
12.250 1.2521 0.02005 0.01438 0.0244 0.0054 1.0000
12.500 1.2544 0.02089 0.01526 0.0277 0.0047 1.0000
12.750 1.2598 0.02182 0.01625 0.0299 0.0045 1.0000
13.000 1.2646 0.02303 0.01753 0.0314 0.0039 1.0000
13.250 1.2694 0.02454 0.01911 0.0323 0.0036 1.0000
13.500 1.2741 0.02634 0.02098 0.0326 0.0033 1.0000
13.750 1.2773 0.02851 0.02323 0.0324 0.0029 1.0000
14.000 1.2818 0.03072 0.02552 0.0319 0.0028 1.0000
14.250 1.2849 0.03318 0.02806 0.0313 0.0027 1.0000
14.500 1.2862 0.03591 0.03088 0.0305 0.0025 1.0000
14.750 1.2858 0.03887 0.03393 0.0296 0.0024 1.0000
15.000 1.2826 0.04218 0.03733 0.0286 0.0021 1.0000
15.250 1.2788 0.04558 0.04081 0.0275 0.0021 1.0000
15.500 1.2738 0.04914 0.04446 0.0264 0.0020 1.0000
15.750 1.2673 0.05291 0.04832 0.0251 0.0019 1.0000
16.000 1.2590 0.05693 0.05243 0.0238 0.0018 1.0000
16.250 1.2522 0.06082 0.05641 0.0225 0.0017 1.0000
16.500 1.2438 0.06510 0.06078 0.0209 0.0017 1.0000
16.750 1.2350 0.06953 0.06530 0.0192 0.0016 1.0000
17.000 1.2262 0.07404 0.06990 0.0175 0.0016 1.0000
17.250 1.2180 0.07855 0.07450 0.0157 0.0016 1.0000
17.500 1.2069 0.08356 0.07961 0.0137 0.0014 1.0000
17.750 1.1997 0.08806 0.08419 0.0119 0.0016 1.0000
18.000 1.1865 0.09358 0.08981 0.0095 0.0015 1.0000
18.250 1.1762 0.09869 0.09501 0.0074 0.0015 1.0000
18.500 1.1632 0.10434 0.10076 0.0050 0.0014 1.0000
18.750 1.1532 0.10961 0.10612 0.0027 0.0015 1.0000
19.000 1.1400 0.11546 0.11206 0.0001 0.0014 1.0000
19.250 1.1278 0.12125 0.11795 -0.0025 0.0015 1.0000
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Polar data table (+)
Polar graphs
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