A device for testing a flow field state within a high-speed train bogie cabin; the periphery of a bogie consists of apron plates and end plates; the test device comprises: a plurality of test points evenly distributed on the inner walls of the apron plates and end plates, a plurality of image pickup devices installed in the bogie cabin, a smoke generator communicating with an inner cavity of the bogie via pipes, and one or more smoke exits provided on top of the bogie; each test point is connected to a test tape, and the distance between the test points is more than twice the test tape length. The test device monitors and records in real time the air flow direction at the end plates and apron plates by means of viewing of a fluorescent test tape. Also provided is a method of testing a flow field state within a high-speed train bogie cabin.

In an embodiment, a test section comprises at least one surface defining an at least partially enclosed space. The at least partially enclosed space defines an airflow path for air to flow. The test section also comprises a nozzle disposed in the at least partially enclosed space. The nozzle is configured to spray an agricultural spray and is positioned to emit the agricultural spray such that at least a section of the agricultural spray exhibits a non-parallel angle relative to the airflow path defined by the at least partially enclosed space. The test section further comprises at least one stimulus source positioned to illuminate at least a portion of the agricultural spray adjacent to the nozzle. Additionally, the test section comprises at least one detector positioned to image at least the portion of the agricultural spray adjacent to the nozzle.

A method of manufacturing. The method includes receiving, by a processor, image data of a first aircraft component subjected to an airflow. A plurality of tufts has been attached to the aircraft component. The method also includes classifying, by the processor, the plurality of tufts into a first set of separated tufts and a second set of attached tufts to form a classification output. The method also includes manufacturing a second aircraft component or reconfiguring the first aircraft component based on a design change to the first aircraft component that results from an aerodynamic analysis of the classification output.

An apparatus is provided for providing simulated smoke. The apparatus comprises a reservoir including a reservoir port, and a bladder disposed in the reservoir. The bladder can be deflated to cause a fluid substance to flow through the reservoir port into the reservoir to fill the reservoir with the fluid substance to generate smoke. The bladder can be inflated to cause smoke to flow out of the reservoir through the reservoir port to provide simulated smoke.

A system and method for monitoring a flow of a fluid on an external surface of a structure in motion. The structure defines an external side comprising the external surface and an internal side opposed from the external side. The system comprises a fluid dispensing device located on the internal side of the structure. The fluid dispensing device comprises the fluid and a conduit that directs the fluid onto the external surface of the structure. An observation device is located on the external side of the structure. The observation device is positioned to observe the flow of fluid on the external surface of the structure.

A method of analyzing and characterizing aerodynamic characteristics of a golf ball is disclosed. The method involves utilizing a schlieren system to observe, study, and capture aerodynamic related information of a golf ball, particularly at subsonic speeds. Due to the inherent operating principals of schlieren systems, the present disclosure includes a treatment of the golf ball prior to or during analysis within the schlieren system. For example, the method can include applying a refractive index altering treatment to the golf ball. The treatment to the golf ball results in a non-homogenous density-altering effect being emitted from the golf ball such that quantitative and qualitative aerodynamic information can be captured by the schlieren system.

A system reproduces aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions. The system includes a test component disposed in the test environment that defines an exterior surface. A trip dot is mounted on the test component and has a first state, in which a distal surface of the trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the trip dot is at a second elevation relative to the exterior surface of the test component. An actuator is operably coupled to the trip dot and configured to transition the trip dot between first and second states. A controller remotely causes the actuator to transition the trip dot between the first and second states.

A method and a system for diagnosing high-enthalpy shock tunnel flow field parameters are provided. In the method, the parameters of the reservoir at the end of shock tunnel and nozzle free flow are measured by using a contact measurement technology and a non-contact spectrum measurement technology to diagnose the high-enthalpy shock tunnel flow field. With the method, not only flow field temperature, pressure, component category and component concentration, but also non-equilibrium state information of the flow field and the effective wind tunnel working time can be obtained.

A seeding device 1 includes a seeder 3 that jets out a jet flow 2 containing oil particles and gas therein, and a tubular body 5, 23 surrounding the jet flow 2. The distance X from a starting end S of the jet flow 2 to the tip end T of the tubular body 5, 23 is set so that the progressing rate of atomization of the oil particles at the tip end T of the tubular body 5, 23 is a predetermined rate or less.

An air-data probe system measures at least one component of freestream velocity by tracking the motion of a laser-induced breakdown (LIB) spark created in a freestream flow. Neutral density filters are positioned or deployed so that the brightness of the initial LIB spark doesn't over saturate the LIB sensor system. This allows for more consistent tracking of the LIB spark throughout the duration of the LIB spark, including the later stages where the LIB spark is not nearly as bright as the initial LIB spark, thereby allowing all or substantially all of the light generated by the LIB spark to reach the sensors. This provides for enhanced visibility and more accurate detection of the LIB spark over time and as air density changes.