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A hybrid model and design method for icing wind tunnel test of high-lift airfoil

A hybrid model, high-lift wing technology, used in aerodynamic testing, machine/structural component testing, instrumentation, etc., can solve the problem of inability to apply stall alarms in anti-icing wind tunnel tests, small wind turbine lift coefficients and Problems such as low lift-to-drag ratio, to achieve the effect of solving the difficulty of model design, easy implementation, and great technological progress

Active Publication Date: 2021-07-16
HARBIN
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Problems solved by technology

[0016] For analysis: In this invention, the airfoil with little distribution in the spanwise direction of the blade is suitable for the hybrid airfoil whose lift coefficient and lift-drag ratio of small wind turbines are lower than that of traditional blade airfoils, and cannot be used for stall alarm anti-icing wind tunnel test

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  • A hybrid model and design method for icing wind tunnel test of high-lift airfoil
  • A hybrid model and design method for icing wind tunnel test of high-lift airfoil
  • A hybrid model and design method for icing wind tunnel test of high-lift airfoil

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Embodiment Construction

[0050] In order to make the purpose, technical solution and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. For simplicity, some technical features known to those skilled in the art are omitted from the following description.

[0051] Taking the Y12F aircraft as an example below, the icing wind tunnel test model for verifying the anti-icing capability of the stall warning device is designed using the hybrid model of the present invention.

[0052] see also figure 1 and figure 2 The icing wind tunnel test hybrid model of the high-lift airfoil of the present invention is designed based on the 1:1 original airfoil section, and the shape is reconstructed, which includes a front section, a middle section and a rear section. Among them, the shape and size within the range of 15-25% chord line of the leading edge are consistent with the original ai...

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Abstract

The invention belongs to the design technology of an icing wind tunnel test model of a deicing and anti-icing system of an aircraft stall warning device, and in particular relates to a high-lift airfoil icing wind tunnel test mixing model and a design method thereof. The present invention takes the stall alarm at the leading edge of the real aircraft wing as the center, intercepts a section of 1:1 original wing section along the span of the wing, and the section of the wing section is a high-lift airfoil with post-loading, and then the aircraft The shape of the wing section is reconstructed, and the chord length is shortened to 45-60% of the chord length of the original model while ensuring that the shape and size of the chord line within 15-25% of the leading edge are consistent with the original wing airfoil. The shape of the middle and rear sections of the airfoil makes the pressure distribution within 10% of the chord line of the leading edge basically consistent with the pressure distribution of the corresponding parts of the original wing, and the pressure distribution of the whole model has no sudden change, which has greater practical application compared with the existing technology value.

Description

technical field [0001] The invention belongs to the design technology of an icing wind tunnel test model of a deicing and anti-icing system of an aircraft stall warning device, and in particular relates to an icing wind tunnel mixed model suitable for the icing wind tunnel test of the deicing and anti-icing system of an aircraft stall warning device. Background technique [0002] In order to prevent the civil aircraft from accidentally entering a stall state during flight, a stall warning device is generally installed. General-purpose aircraft that are applicable to CCAR23 airworthiness regulations usually use a windvane stall warning sensor as a stall warning device. Since this type of sensor needs to be installed on the leading edge of the wing, it is easily affected by external weather conditions, such as icing weather. Therefore, the stall warning device of civil aircraft generally adopts electric heating measures to make it have anti-icing function. According to the req...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/08G01M9/00
CPCG01M9/00G01M9/08
Inventor 乔伟王洪伟王强董振林郑亚飞杨欢霍燃
Owner HARBIN
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