Method for quickly determining installation angle of aircraft wing

Abstract

The invention belongs to the pneumatic layout technology of a conventional pneumatic layout aircraft, and relates to a method for determining an installation angle of a conventional pneumatic layout aircraft wing. The method for quickly determining the installation angle of the aircraft wing comprises the following steps that a preliminary wing installation angle is firstly given, and only a knownpitching moment coefficient of a zero angle of attack wing and fuselage combination body is needed, a horizontal tail lift force coefficient is calculated through a whole-aircraft pitching moment balance condition, and in the case that the horizontal tail lift force coefficient and a wing and fuselage combination body lift force coefficient are known, a whole-aircraft lift coefficient is obtained; a series of wing installation angles are given, and the relationship between the whole-aircraft lift coefficient and the wing installation angle is obtained under conditions that the angle of attackof the fuselage is zero and the whole-aircraft pitch moment coefficient is zero; and based on the cruise design point condition, the final wing installation angle is determined by interpolation according to the cruise whole-aircraft lift coefficient. The method has the advantages that the calculation amount is small, the size of the installation angle of the traditional pneumatic layout wing canbe directly and rapidly determined, the aerodynamic property calculation or wind tunnel test workload is effectively saved, and the method has relatively large practical application value.

Description

technical field [0001] The invention belongs to the aerodynamic layout technology of conventional aerodynamic layout aircraft, and relates to a method for determining the wing installation angle of conventional aerodynamic layout aircraft. Background technique [0002] When designing the aerodynamic layout of an aircraft, it is necessary to determine the installation angle of the wing, which is the angle between the chord line at the root of the wing and the horizontal line of the aircraft fuselage. Wing installation angle is a basic parameter of aircraft aerodynamic layout design, which has an important influence on aircraft aerodynamic layout. [0003] Usually, there are two ways to determine the wing installation angle: (1) directly determine the wing installation angle by counting the wing installation angles of the same type of aircraft; Hole test to determine the wing installation angle. [0004] The advantage of the first method is that it is simple, and the disadva...

AI Technical Summary

Problems solved by technology

[0004]The advantage of the first method is that it is simple, and the disadvantage is that it does not consider the specific influence of the aircraft design parameters, and is determined by the statistical average

The advantage of the second method is that it takes into account the influence of aircraft design parameters on the installation angle of the wing, but the disadvantage is that the aerodynamic calculation or wind tunnel test has a large workload and a long cycle

This invention is to calculate the aerodynamic characteristics of the entire amphibious hovercraft. Since the trim lift and resistance of the horizontal tail will affect the lift-drag ratio of the entire hovercraft, the installation angle of the wings should be determined iteratively. The overall program is complicated, the calculation amount is large, and the calculation cycle is long.

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