The invention discloses a wind tunnel test device for separating a hood of a plane-symmetric hypersonic aircraft. The test device comprises a
projectile body model supported by a
tail supporting rod of a hypersonic wind tunnel upper mechanism and a cover body model supported by an
abdomen of a hypersonic wind tunnel lower mechanism. In an initial state, the cover body model covers the head of theprojectile body model and is separated from the
projectile body model without contact; in a test state, the cover body model and the
projectile body model are separated and do relatively
independent motion; the cover body model adopts a rod-type six-component balance to measure
aerodynamic force of the cover body model, and spray pipes are symmetrically arranged on the left and right sides of thecover body model for spray
pipe jet flow simulation; the projectile body model adopts a rod type six-component balance to measure the
aerodynamic force of the projectile body model; the abdominal support is communicated with a pore
plate pressure regulating device. The test device solves the key technical problems of two-stage model relative attitude, two-stage model separation distance adjustment,
jet flow simulation, small-size
balance design, model connection and the like, improves the
jet flow stability of the jet
pipe, and reduces the interference of abdominal support.