METHOD OF MEASURING STATIC PRESSURE IN THE NEAR FIELD OF AN AIRCRAFT OUTSIDE THE BOUNDARY LAYER IN WIND TUNNELS Russian patent published in 2024 - IPC G01M9/06 

FIELD: aerodynamics.

SUBSTANCE: invention relates to aerodynamics and is intended for investigation of near pressure field of aircraft model at supersonic flow in wind tunnel (WT). Method is implemented as follows: aircraft model is fixed on blade holder to wall of TS of wind tunnel with such calculation that to provide position of shock wave (SW) from aircraft model nose, reflected from nearest wall of TS WT, downstream relative to SW from aircraft model tail. In the TS WT, outside the boundary layer region, a measuring device is placed, which comprises a set of static pressure nozzles connected to electronic pressure gauges and fixed on a coordinate device, which provides the possibility of moving the coordinate device along the axis of the TS WT along a given set of coordinates. During the tests, the metering device is used to measure the distribution of static pressure along the TS axis by each of the static pressure nozzles. Parameters of the incident flow are measured: total and static pressure in the TS of wind tunnel, which are involved in calculating the Mach number. Measurements of static pressure, incident flow parameters and data on the spatial position of the set of static pressure nozzles are carried out using a measurement system providing synchronized data collection. Distribution of static pressure in the near field of the aircraft, as well as parameters of the incident flow, are then used to calculate the levels of sonic boom in the far field.

EFFECT: increasing the productivity and quality of research conducted in the field of sonic boom.

8 cl, 4 dwg