Fairing device, design method and wing-body fusion device for airfoil wind tunnel test
A rectification device and wind tunnel test technology, which is applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc., can solve problems such as tunnel wall interference and inaccurate test data acquisition
Active Publication Date: 2020-10-23
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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Problems solved by technology
[0004] The purpose of the present invention is to overcome the deficiencies in the prior art, to provide a rectifying device, a design method and a wing-body fusion device for the airfoil wind tunnel test, which can solve the problems caused by the tunnel wall, etc. during the current airfoil wind tunnel test. Technical problems such as inaccurate test data acquisition caused by large interference
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[0032] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0033] It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit t...
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The invention provides a rectifying device for an aerofoil wind tunnel test, a design method thereof and a wing-fuselage fusion device. The method includes the following steps: step 1, selecting an aerofoil profile, obtaining relevant parameters of the aerofoil profile, and connecting upper surface nodes of the aerofoil profile in order based on the relevant parameters to obtain an aerofoil profile curve; step 2, taking a connection line from a leading edge point to a trailing edge point of the aerofoil profile as an axis, rotating the aerofoil profile curve into a body along the axis to obtain a rotating body; step 3, obtaining a semi-mode model of the rotating body along the axis; step 4, reducing the size of the semi-mode model in three direction of an X-axis / Y-axis / Z-axis with a designtarget that the rectifying device can wrap an aerofoil joint to obtain a rectifying device solid model; step 5, carrying out solid shell pulling on the solid model to obtain an open shell model; andstep 6, arranging an insertion through hole of the aerofoil joint on the open shell model; The rectifying device for the aerofoil wind tunnel test, the design method thereof and the wing-fuselage fusion device can solve the technical problem of inaccurate test data acquisition caused by large interference such as a tunnel wall in a current aerofoil wind tunnel test.
Description
technical field [0001] The invention relates to the technical field of aircraft aeroelasticity, in particular to a rectifying device, a design method and a wing-body fusion device for wing surface wind tunnel tests. Background technique [0002] With the development of aircraft design towards light weight, high flexibility, and high maneuverability, the amount of deformation of the wing surface is increasing, and the impact of deformation on aerodynamic performance is becoming more and more serious, which puts forward higher requirements for aircraft design. In order to ensure the data accuracy of the design, it is usually necessary to carry out wind tunnel force testing to obtain accurate and reliable aerodynamic data. For the static aeroelastic wind tunnel model, due to the similarity in shape and structure, the design of the model is much more difficult than the conventional force measurement model. Usually, in order to reduce the difficulty, only the elastic model force...
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IPC IPC(8): G01M9/06
CPCG01M9/065
Inventor 许云涛吴志刚何海波操小龙
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH