Design method of ejector nozzle experimental device for simulating aircraft outflow

Abstract

The invention discloses a design method of an ejector nozzle experimental device for simulating outflow of an aircraft. According to the method, an initial molded line of the meridian plane of the outflow nozzle under a specific flight Mach number is designed by adopting a characteristic line method, then an outer flow channel asymmetric nozzle meridian plane molded line meeting requirements is obtained by adjusting an outer flow channel symmetric factor G and a throat channel height h, and an outer flow channel three-dimensional model is further obtained; and finally, an outflow pressure stabilizing section and a circumferentially distributed air inlet section are designed. According to the design method, the outflow channel is designed through the characteristic line method, original experiment assemblies can be utilized to a large extent, the method is simple, programs are easy to achieve, and the profile of the outflow channel under different mach numbers can be designed. The supersonic airflow generated by adopting the design method does not have expansion waves or shock waves, the flow parameters are uniform, the outflow environment of the aircraft can be accurately simulatedon the premise of ensuring the economical efficiency, and a feasible experimental device design method is provided for researching the inflow and outflow coupling mechanism of the high-altitude flight working condition of the aircraft.

Description

technical field [0001] The invention relates to the field of aircraft aerodynamic experiments, in particular to a design method for an experimental device capable of simulating outflow. Background technique [0002] Since the TBCC tail nozzle works in a large range of falling pressure ratio, and the mass flow rate through it also varies greatly, its expansion ratio changes from 2 in the take-off state to 15-20 in the supersonic cruise state. Geometric methods are used to adjust the throat and expansion angle, which increases the complexity of the nozzle configuration and additional resistance. Therefore, it is necessary to design a nozzle containing multi-channel fluid through a pneumatic method, which is easy to realize in terms of configuration and does not bring additional resistance. The ejection nozzle applied to supersonic aircraft ejects the overflow from the inlet boundary layer or the gas (secondary flow) from the cooling flow path and external duct, and shears the...

AI Technical Summary

Problems solved by technology

This method can simulate the working state of the nozzle on the premise of less difficulty and better economy, but it cannot accurately simulate the outflow situation, especially the mutual coupling between the outflow and the main flow and further influence on the main flow field

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