An aero damping measurement system (100) is provided. The system includes a shroud (104) defining a tunnel, a hub (102) disposed within the tunnel, and a plurality of blades (103) coupled to the hub (102). The blades (103) may rotate about the hub (102). A gas pressure probe (108) may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system (168) may include a pressurized gas source (170), a valve (132) in fluid communication with the pressurized gas source (170), and the gas pressure probe (108) may be in fluid communication with the valve (132). The valve (132) may control a flow of a pressurized gas from the pressurized gas source (170) into the gas pressure probe (108). A pressure sensor (160) may be coupled to the gas pressure probe (108) and configured to measure a pressure within the gas pressure probe (108).