Abstract
The aero-optical effects of a hypersonic dome with cooling jet device can be mitigated by micro vortex generators (MVGs) at 0°angle of attack (AoA) and 0°angle of sideslip (AoS). However, the attitude angle of an aircraft is constantly changing during actual flight. In this research, experiment was carried out at the KD-01 hypersonic gun tunnel at Mach 6.0. Using the schlieren technique, the flow field density distribution of a hypersonic optical dome under different pressure ratios of jet (PRJ) was observed. The optical path difference (OPD) was obtained by background-oriented schlieren (BOS). Experimental results showed that a 4°AoA could increase the OPD value more obviously with or without MVGs; and that the use of MVGs under 4°AoS would aggravate the aero-optical effects. These findings place new demands on the design and installation of MVGs.
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