Method for controlling variable Reynolds number of continuous transonic speed wind tunnel experimental section flow field

Abstract

The invention relates to a method for controlling the variable Reynolds number of a continuous transonic speed wind tunnel experimental section flow field. The method includes the steps that a set of mach numbers and total pressure values of experimental sections corresponding to the mach numbers are obtained through a BP algorithm according to a given target Reynolds number; then, a set of rotating speeds of a compressor, stationary blade angles of the compressor and choke finger positions of the experimental sections corresponding to the mach numbers are obtained through the BP algorithm; the experiment is conducted at normal pressure, when the mach number requirement is met, pressurizing is carried out towards the inside of a wind tunnel, so that the Reynolds number is changed, after the Reynolds number reaches the order of magnitude of 107, pressurizing in the wind tunnel is stopped, the rotating speeds are regulated in a closed-loop mode, and accordingly the mach numbers and the Reynolds number of the wind tunnel flow field can meet the experimental index requirement at the same time. By the adoption of the method, the choke finger, a motor and the axial flow compressor can be controlled simultaneously, the mach numbers can be measured in real time, on the basis that the experimental section flow velocity field is stable, the wind tunnel experimental section Reynolds number can be changed continuously by controlling wind tunnel air supply pressure, and therefore a method is provided for controlling the variable Reynolds number of the continuous transonic speed high Reynolds number wind tunnel flow field.

Description

technical field [0001] The invention belongs to the field of aerospace, and relates to a method for controlling the variable Reynolds number of the flow field in the experimental section of a continuous transonic wind tunnel. Background technique [0002] The birth of advanced aircraft depends on advanced design and manufacturing technology and first-class wind tunnel experiment technology. Mach number and Reynolds number are one of the key indicators. At present, domestic wind tunnel experiments can meet the Mach number index, and the corresponding experimental Reynolds number However, it is far lower than the actual flight Reynolds number of the aircraft. The flight Reynolds number can be approached by pressurizing or increasing the model size, and the aerodynamic characteristic data of the aircraft flying under the Reynolds number can be obtained by extrapolation. This will inevitably bring about certain data errors. It is not conducive to the design and selection of airc...

AI Technical Summary

Problems solved by technology

[0011] The existing temporary wind tunnels in China, because they use high pressure as power, can only make the wind tunnel work for a few seconds to tens of seconds each time, and then recompress the air, so there are characteristics of low efficiency and high cost

Images