Method for obtaining static aeroelastic deformation influencing quantity of wind tunnel model

A technology of static aeroelasticity and influence quantity, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of inability to realize real-time data analysis, high time and calculation costs, reliability dependence, etc., to avoid Test the scrapping of trains, reduce the difficulty and preparation period, and reduce the effect of dependence

Active Publication Date: 2017-11-24
AERODYNAMICS NAT KEY LAB
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Problems solved by technology

The method of numerical simulation / model deformation measurement has good calculation resolution, but the reliability of the correction results depends on the accuracy of model deformation measurement and deformation shape reconstruction, and the time and calculation costs are high, so real-time analysis of data cannot be realized

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  • Method for obtaining static aeroelastic deformation influencing quantity of wind tunnel model
  • Method for obtaining static aeroelastic deformation influencing quantity of wind tunnel model
  • Method for obtaining static aeroelastic deformation influencing quantity of wind tunnel model

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Embodiment Construction

[0026] In order to clearly illustrate the technical features of the solution, the solution will be described below through a specific implementation mode combined with the accompanying drawings.

[0027] In the wind tunnel test, without considering the changes of other parameters (such as Mach number Ma, model angle of attack α), the aerodynamic coefficient C under the elastic shape f,elastic It can be expressed as a function of Reynolds number Re and incoming flow velocity and pressure q

[0028] C f,elastic = f(Re,q) (1)

[0029] The existence of flow velocity pressure will cause the static elastic deformation of the wing structure of the wind tunnel model, so the aerodynamic coefficient can be divided into the rigid shape aerodynamic coefficient C f,rigid The change of aerodynamic coefficient ΔC caused by the static aeroelastic deformation of the wing f,elastic Two parts, where C f,rigid Only varies with Re, ΔC f,elastic With the change of Re and q, the formula can be ...

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Abstract

The invention provides a method for obtaining the static aeroelastic deformation influencing quantity of a wind tunnel model. According to the scheme, for solving the problem that different incoming flow velocity pressure test data extrapolation methods depend on the capability of total temperature and total pressure independently controlled test facilities, an independently-variable total pressure wind tunnel testing method which can be achieved by most wind tunnels is adopted to obtain wind tunnel test data of different Reynolds number and incoming flow velocity pressure combinations, the difficulty and cost of an air tunnel test is remarkably reduced, and a preparation period of the air tunnel test is remarkably shortened, the dependency of static aeroelastic deformation influence correction on wind tunnels is eliminated, and a technical support is provided for corresponding correction tests carried out for various conventional air tunnels. For solving the problem that the time and calculation costs of numerical simulation / model deformation measurement combined methods are high and the static aeroelastic deformation influence cannot be analyzed in real time, an algebraic equation solving method is adopted, rapid separation of a Reynolds number effect and a static aeroelastic deformation influencing effect can be achieved, and accordingly the influencing quantity of static aeroelastic deformation to aerodynamic force characteristics can be analyzed in real time.

Description

technical field [0001] The invention relates to the field of aircraft wind tunnel tests, in particular to a method for obtaining the influence quantity of static aeroelastic deformation of a wind tunnel model. Background technique [0002] In the wind tunnel test of aircraft, designers expect to obtain the aerodynamic data of the aircraft model in a rigid shape state. However, due to the effect of the incoming aerodynamic load in the wind tunnel, the model wing will undergo static aeroelastic deformation, thereby changing the flow field around the model, and then changing the aerodynamic load borne by the wind tunnel model. At the same time, the wind tunnel balance measures the aerodynamic load data of the model under the deformed shape, which is different from the expected rigid shape load. Therefore, when the model has a large static aeroelastic deformation during the test, the wind tunnel test data will contain systematic errors that cannot be ignored, and the accuracy o...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23Y02T90/00
Inventor 孙岩孟德虹王运涛洪俊武张书俊李伟杨小川
Owner AERODYNAMICS NAT KEY LAB
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