Numerical simulation method of flight icing

A numerical method, aircraft technology, applied in the field of aeronautical engineering, can solve problems such as not considering the influence of water droplets

Inactive Publication Date: 2012-09-19
TIANJIN AEROCODE ENG APPL SOFTWAREDEV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, this calculation method does not consider the influence of water droplets on air flow when solving the control equations of air movement and flow. Obviously, certain errors will occur

Method used

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  • Numerical simulation method of flight icing
  • Numerical simulation method of flight icing
  • Numerical simulation method of flight icing

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Embodiment Construction

[0086] Further illustrate the present invention with a specific embodiment below, a kind of numerical simulation method that is used for aircraft flight icing, this numerical simulation technology can realize with Fortran90 computer high-level programming language, and simulate two-dimensional NACA0012 wing by computer operation The state when encountering icing during airflight.

[0087] The conditions for the numerical simulation are:

[0088] Flow speed: 57m / s

[0089] Incoming temperature: 243K

[0090] Atmospheric pressure: 100kPa

[0091] Angle of attack: 0°

[0092] Liquid water content: 2.58g / m 3

[0093] Ultra-cold water droplet diameter: 50μm

[0094] Density of ice: 917kg / m 3

[0095] according to Figure 5 The detailed steps of the numerical simulation method calculation process of the aircraft flight icing that the present invention proposes are,

[0096] 1. Generation of computational grids around uniced aircraft. First generate a computational grid ar...

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Abstract

The invention discloses a numerical simulation method for aircraft flight icing, which simulates the state of an aircraft encountering icing during flying. The method is mainly characterized by comprising an algorithm of the velocity resolution and the water film thickness of a wall surface water film surface in a single-fluid model used for simulating two phase flow flowing of air-ultracold water drop, an algorithm for tracking an icing interface through mesh refinement method in a water film icing state model for calculating ice layer shape and internal temperature, and a flow based on fixed computational grids and used for performing flight icing numerical simulation calculation through the models and the algorithms.

Description

technical field [0001] The invention relates to the field of aeronautical engineering, and is the application of computational fluid dynamics in the field of aeronautical engineering, in particular, a numerical method for simulating flight icing of aircraft. This numerical simulation technology can be implemented with a high-level computer programming language, and simulate the state of the aircraft when it encounters icing during the air flight through the operation of the computer. Background technique [0002] When the aircraft passes through the clouds within a certain flight altitude range, the ultra-cold liquid water droplets in the atmosphere (the temperature is below freezing point, but exists in the form of liquid water droplets) will collide with the surface of multiple parts of the aircraft to form water films, such as wings, aircraft, etc. The surface of the body, cockpit, empennage, engine air intake and other parts are prone to form a large amount of accumulate...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 路明
Owner TIANJIN AEROCODE ENG APPL SOFTWAREDEV
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