Aerothermodynamic Characteristics of Boundary Layer Transition of the Lifting Body

In the FD-07 hypersonic wind tunnel of the China Academy of Aerospace Aerodynamics, phosphorescent thermography measurement technology was used to conduct wind tunnel tests on the lifting body model under different Mach numbers and angles of attack. The surface heat flux distribution of the lifting body model was obtained, and the effects of Mach number and angle of attack on the boundary layer transition of the hypersonic lifting body model were analyzed. The results show that: (1) For the lifting body shape, the transition end position at the centerline is further back, while the transition positions on both sides are influenced by transverse flow and reattachment and are closer to the leading edge. (2) Under Ma = 5 conditions, the heat flux rapidly increases near Y = 100mm from the head, forming a “W"-shaped division line of heat flux values and exhibiting obvious transition phenomena. With the increase of incoming Mach number, the transition position of Ma  =  8 moves further back, forming a narrow and elongated “W"-shaped division line of heat flux values near Y  =  240 mm from the head. (3) Under Ma  =  5 and different angles of attack conditions, the transition position is located near Y  =  100 from the head, and its variation is not significant with the increase of angle of attack. The shape of the division line of heat flux values changes significantly with the increase of angle of attack.