That is, the tail section lacked horizontal stabilizers, so researchers could test a theory that those components were a key factor in stability problems at transonic speeds up to about Mach 0.9.
By using real time data gathering and test system of the aero engine test bed, the detail measurement of single stage transonic fan performance with and without different casing treatments were made.
The experimental investigation on aeroelastic instability and dynamic response of the BF-1 rotors by a transonic axial-flow compressor test rig are presented in this paper.