Continuous transonic speed wind tunnel spray liquid nitrogen cooling test operation method

Abstract

The invention provides a continuous transonic speed wind tunnel spray liquid nitrogen cooling test operation method. The method comprises three stages of work which includes preparation, operation and end. Preparation work comprises liquid nitrogen preparation, push and shove gas preparation, gas distribution bench preparation, wind tunnel preparation, measurement and control system preparation, liquid nitrogen conveying pipeline preparation, storage tank pre-pressurization and gas replacement in a wind tunnel. Operation stage work comprises wind tunnel cleaning, gas flow cooling, parameter transition and stable parameter testing. An end stage comprises steps that data recording is stopped; liquid nitrogen is stopped to be injected into the wind tunnel; through an exhaust system, wind tunnel decompression is performed; and a compressor continuously runs under a set work condition and heat released by the compressor is used to heat a gas flow and a wind tunnel body to a set temperature or to a normal temperature, and then the compressor stops running. By using the method of the invention, operation of a spray liquid nitrogen cooling system and operation of the wind tunnel are integrated into one body so that spray liquid nitrogen cooling testing can be safely and effectively performed in a continuous transonic speed wind tunnel.

Description

technical field [0001] The invention relates to the technical field of wind tunnels, in particular to a continuous transonic wind tunnel spraying liquid nitrogen cooling test operation method. Background technique [0002] The Reynolds number is an important similar parameter for wind tunnel experiments to simulate the actual flight capabilities of aircraft. Theoretically speaking, in order to make the wind tunnel experiment fully simulate the real flight state, the Reynolds number of the wind tunnel experiment and the actual flight must be consistent. However, due to the limitation of model size, wind tunnel power equipment, energy system and other factors, the current wind tunnel experiment Reynolds number is still difficult to reach the actual flight Reynolds number. The difference between the experimental Reynolds number and the flight Reynolds number will lead to significant differences between the aerodynamic characteristics of the boundary layer transition, separatio...

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Problems solved by technology

However, because the continuous high-speed wind tunnel is driven by a high-power motor, limited by the energy system, there is still a certain gap between the Reynolds number in the experimental section and the actual flight Reynolds number, which cannot well meet the needs of fighter jets and large-scale high-speed civil aircraft model experiments

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