Aeroelastic Stability Tests of Thin Cylindrical Shells at Supersonic Speeds.

摘要

Dynamic characteristics of thin cylindrical shells were investigated for Mach numbers from 2.2 to 3.0. The Reynolds number based on the model diameter varied from 0.34 to 2.58 million. Limit cycle oscillations in a standing wave mode occurred on a 0.0020-in. shell at Mach number 2.2. The limit cycle motion was damped completely by blowing air into the boundary layer at a very low rate. A 0.0028-in. shell was destroyed during high amplitude oscillations at Mach number 2.2. Pressure distribution and boundary-layer measurements were also made. (Author)