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An Experimental Method to Obtain the Influence of Flow Field Non-uniformity on Model Aerodynamic Characteristics

A non-uniformity and test method technology, applied in the field of wind tunnel test, can solve the problem of inability to accurately evaluate the influence of the aerodynamic characteristics of the flow field, and achieve the effect of simple test method and comprehensive data acquisition

Active Publication Date: 2022-04-12
中国空气动力研究与发展中心超高速空气动力研究所
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Problems solved by technology

Existing methods for evaluating test data cannot accurately evaluate the influence of flow field non-uniformity on aerodynamic characteristics

Method used

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  • An Experimental Method to Obtain the Influence of Flow Field Non-uniformity on Model Aerodynamic Characteristics
  • An Experimental Method to Obtain the Influence of Flow Field Non-uniformity on Model Aerodynamic Characteristics
  • An Experimental Method to Obtain the Influence of Flow Field Non-uniformity on Model Aerodynamic Characteristics

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Embodiment 1

[0062] The model 2 of this embodiment is a ventilated model, the total length of the model 2 after scaling is 0.932m, the test Mach number is 4, and the total pressure P 0 =0.5MPa, total temperature T 0 =280K.

[0063] From Figure 7 ~ Figure 12 It can be seen that the absolute value of the aerodynamic force / moment coefficient 2 times the mean square error δ obtained from the test is small, much smaller than the initial uncertainty U and the maximum deviation δ of the multi-position test. For the aerodynamic coefficient CA, the maximum deviation δ of the multi-position test is slightly smaller than the initial uncertainty U; for the aerodynamic coefficient CN, the maximum deviation of the multi-position test is equivalent to the initial uncertainty; and for the aerodynamic moment coefficient CMz, the maximum deviation of the multi-position test δ is obviously greater than the initial uncertainty U. This is because the flow field of the hypersonic wind tunnel is "non-uniform...

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Abstract

The invention discloses a test method for obtaining the influence of flow field non-uniformity on model aerodynamic characteristics. In this method, the model is placed in multiple positions such as the upstream, center, and downstream of the uniform area of ​​the wind tunnel test section, and the force measurement test is carried out at different positions along the airflow direction; the model is placed on the axis, above the axis, and on the axis of the uniform area of ​​the wind tunnel test section. The force measurement tests at different positions in the vertical direction were carried out at multiple positions such as the bottom; by changing the length of the balance rod, the rotation center of the mechanism was at the front, middle, and tail ends of the model, and the force measurement tests were carried out at different positions of the model with the rotation center; Under the same angle of attack, the continuous force measurement test along the airflow direction and the continuous force measurement test perpendicular to the airflow direction were carried out. It is also possible to separately assess the influence of the non-uniformity of the flow field of each factor on the aerodynamic characteristics of the model by combining one or more methods. The method is simple and comprehensive, and can accurately analyze the influence of flow field inhomogeneity on the aerodynamic characteristics of the model.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a test method for obtaining the influence of flow field non-uniformity on model aerodynamic characteristics. Background technique [0002] In the process of aircraft development, it is necessary to verify the performance of the aircraft through wind tunnel tests. The quality of wind tunnel test data directly affects the design and development cycle of aircraft. Therefore, it is necessary to evaluate the quality of wind tunnel test data. At present, the quality assessment of wind tunnel test data has changed from the early evaluation of data repeatability accuracy to the evaluation of data uncertainty. [0003] It can be seen from the published literature that NASA, AEDC and Boeing have carried out uncertainty analysis on typical tests completed in multiple wind tunnels. It was found that the main factors affecting the uncertainty of wind tunnel data come fr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/08G01M9/06
CPCG01M9/08G01M9/06
Inventor 谢飞郭雷涛许晓斌孙鹏
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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