Method for determining high-speed wind tunnel large aircraft model scale

Abstract

The invention discloses a method for determining a high-speed wind tunnel large aircraft model scale and aims at solving the problems that an existing method for determining a large aircraft model scale is high in difficulty, high in costs and inaccurate. The method comprises the following steps of step 1, generating testing computational grids of different model elongations according to numerical simulation of a model; step 2, setting boundary conditions according to testing operating conditions; step 3, performing numerical simulation of testing conditions by utilizing a CFD (computational fluid dynamics ) calculation procedure and obtaining pressure distribution data of side walls; step 4, comparing the pressure distribution date with pressure distribution data of side walls of an empty wind tunnel, performing statistic analysis on the data and substituting the data into judgment criteria, determining the scale of the full elongation of the model and the width of a testing section to further obtain a proper model scale. The method for the high-speed wind tunnel large aircraft model scale determines the high-speed wind tunnel large aircraft model scale according to disturbance pressure distribution of the side walls of panels of the testing section and provides the basis for the formulation of a testing scheme and the design of a model.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a calculation method for determining the scale ratio of a large aircraft model in a high-speed wind tunnel by using model far-field disturbance evaluation in a high-speed wind tunnel test. Background technique [0002] Determining the scale of the test model is one of the key contents in the design phase of the high-speed wind tunnel test plan. Especially for large aircraft, increasing the scale of the model can not only simulate the surface shape and attachments of the aircraft more accurately, but also increase the size of the test model. The Reynolds number is convenient for the installation and laying of sensors, modules, lines and other equipment, which can greatly improve the quality of test data. However, increasing the scale of the model will inevitably lead to an increase in the amount of cave wall interference, and in severe cases, it will affect t...

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Problems solved by technology

However, the operation of this method is quite random, and the scale ratio of different models or the same model in different periods is different. The most suitable scale ratio can only be determined after the actual blowing data inspection, which is likely to cause scale effect deviations between different periods of data, and increase the test volume. Difficulty, risk and initial cost

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