Grid wing wind tunnel test model scaling method

Abstract

The invention discloses a grid wing wind tunnel test model scaling method. According to the method, every two adjacent unit grids are combined, the grid wing chord length is increased, the wall thickness of each grid and the thickness of a frame are increased, and therefore it is guaranteed that the attach angle lift force area is zero and the windward resistance area is kept unchanged after a model is scaled, and the increase multiples of the chord length and the increase multiples of the wall thickness of each grid are proportional to the combination number of the unit grids. By means of the grid wing wind tunnel test model scaling method, processing difficulty is greatly lowered, a processing period is shortened, and in a wind tunnel test process, under the action of supersonic velocity air flow, the grid wing model is not broken off or damaged. Through verification of a wind tunnel test, pneumatic characteristics of an original design scheme is restored really, and the grid wing wind tunnel test model scaling method is suitable for wind tunnel test model design that the size is too small after grid wings are scaled.

Description

technical field [0001] The invention relates to a scaling method, in particular to a grid wing wind tunnel test model scaling method, which belongs to the field of experimental aerodynamics. Background technique [0002] The wind tunnel test model is usually scaled down according to similarity criteria to simulate the real flight environment of the aircraft, but due to the large number of grid wing grids, small grid spacing and thin grid walls, the scaled down size will become smaller , it is easy to block the flow field of the grid wing during the wind tunnel test, and it is impossible to truly restore the flow field of the high-speed airflow passing through the grid wing, so that the blowing result of the missile with the grid wing is seriously inconsistent with the design state, and the wind tunnel test verification design is lost meaning of the program. At the same time, the scaled model is difficult to realize in terms of technology, and even if the model is finished, ...

AI Technical Summary

Problems solved by technology

[0002] The wind tunnel test model is usually scaled down according to similarity criteria to simulate the real flight environment of the aircraft, but due to the large number of grid wing grids, small grid spacing and thin grid walls, the scaled down size will become smaller , it is easy to block the flow field of the grid wing during the wind tunnel test, and it is impossible to truly restore the flow field of the high-speed airflow passing through the grid wing, so that the blowing result of the missile with the grid wing is seriously inconsistent with the design state, and the wind tunnel test verification design is lost Significance of the program

At the same time, the scaled model is difficult to realize in terms of technology. Even if the model is finished, the strength of the model cannot meet the requirements of the high Mach number wind tunnel test.

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