Abstract:
To induce the near-wall low-momentum fluids moving laterally, an aerodynamic design method of hypersonic forebody/compression surface with the controlled lateral surface pressure is proposed. The basic principle is that the lateral pressure distribution on one section after the external conical flow field is prescribed, and the spatial coordinates of the section can be derived inversely through the coordinate transform, then the forebody/compression surface can be obtained by the stream tracing method. The numerical results demonstrate that the lateral pressure gradient dominates the motion of the near-wall low-momentum fluids on the forebody/compression surface. For the conventional forebody/compression surface, it has strong lateral pressure gradient on the 1
st stage of the forebody, which can induce a lateral flow with a deflection angle below 3° at the design point (
Ma = 7.0 and
H = 28 km). However, it almost has no lateral pressure gradient on the subsequent compression surfaces, and the lateral flow is also fairly weak. The controlled lateral pressure distribution forebody can intensify the lateral pressure gradient about 7 times within the sector-angle ranging from 0° to 40°, the deflection angle increases about 5° on the 1
st stage of the forebody, and the lateral pressure gradient increases significantly with the deflection angle increased over 7° on the 2
st and 3
rd stages of the forebody. Consequently, the boundary layer thickness decreases about 20%, and the total-pressure recovery coefficient in the sector region of the inlet increases about 1.56%.