Fig.1

Integration configurations with a head intake operating with a specific angle of attack under cruising conditions

Fig.2

Schematic of LTOCs method［35］

Fig.3

Schematic of inward-turning inlet design methodology considering cruising angle of attack

Fig.4

Schematic of internal contraction incident shock wave defined by Bezier surface

Fig.5

Definition of shock shape on symmetry plane for axisymmetric curved incident shock wave

Fig.6

Discretization of 3D internal contraction incident shock wave based on LTOCs method

Fig.7

Calculation of internal contraction basic flowfield in meridian plane

Fig.8

Space reconstruction for compression surface of 3D inward-turning inlet

Fig.9

Inlet geometric model of Case A

Table 1

Comparison of design parameters of two 3D inward-turning inlets

Fig.10

Comparison of geometric profiles at critical sections of two 3D inward-turning inlets

Table 2

Comparison of critical geometrical parameters of two 3D inward-turning inlets

Fig.11

Integrated model of curved fore-body and inward-turning inlet

Fig.12

Comparison of numerical and experimental

Fig.13

Mesh and boundary conditions of Case A

Table 3

Comparison of viscous aerodynamic parameters on throat planes for different grid scales

Fig.14

Comparison of incident shock wave structures for two inlets under inviscid condition

Fig.15

Comparison of inviscid pressure ratio contours on symmetry plane for two inlets

Fig.16

Comparison of inviscid pressure ratio distributions along upper wall of two inlet symmetry planes

Table 4

Comparison of inviscid aerodynamic parameters on throat planes of two inlets

Fig.17

Comparison of incident shock wave structures for two inlets under viscous condition

Fig.18

Comparison of numerical schlieren on symmetry planes of two inlets under viscous condition

Fig.19

Comparison of total pressure recovery contours along two inlets under viscous condition

Fig.20

Comparison of X-vorticity contours on different cross sections for isolators of two inlets

Table 5

Comparison of viscous aerodynamic parameters for two inlets