A data processing method of wind tunnel test for sonic boom measurement

Abstract

The invention discloses a sonic boom measurement wind tunnel test data processing method, which belongs to the aerospace wind tunnel test field and aims to solve the problem that the existing sonic boom measurement wind tunnel test data processing method is incomplete in eliminating background pressure interference. The processing method includes the following steps: A. According to the configuration of the probe and the opening position, the pressure recovery coefficient of the probe is obtained through theoretical calculation or numerical simulation; B. Move the measurement probe along the axial direction of the wind tunnel, carry out flow field calibration, and obtain the pressure measurement value of the measurement probe along the way; C. Carry out the model sonic boom measurement wind tunnel test, obtain the pressure measurement value of the measurement probe at each point along the way, etc. This application introduces the pressure recovery coefficient and the background pressure calibration data under the same wind tunnel body conditions to participate in the sonic boom measurement wind tunnel test data processing. On the one hand, the reference pressure calculated by the overpressure value can be normalized to the wind tunnel flow Static pressure, on the other hand, can accurately eliminate background pressure fluctuations in sonic boom measurement wind tunnel test data point-to-point.

Description

technical field [0001] The invention relates to the field of aerospace wind tunnel tests, in particular to a method for processing wind tunnel test data for sonic boom measurement. Background technique [0002] When the operating speed of the aircraft reaches supersonic speed, a series of wave systems generated by the shape of the aircraft interfere with each other in the process of propagating far away, and finally converge into a front shock wave including the head of the aircraft and a rear shock wave trailing the tail of the aircraft. . When this wave system propagates to the ground, it is perceived as two thunderous loud noises, called sonic booms. [0003] As an independent test technique, the sonic boom measurement test refers to obtaining the characteristics of the sonic boom produced by the aircraft through experiments. The basic idea of ​​a typical sonic boom measurement wind tunnel test is to keep the attitude of the aircraft model and the vertical distance betw...

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Problems solved by technology

[0032] The purpose of the present invention is to provide a sonic boom measurement wind tunnel test data processing method to overcome the incomplete problem of eliminating background pressure interference in the existing sonic boom measurement wind tunnel test data processing method

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