Design method and appearance of aerodynamic layout of plane-symmetric concave curved surface standard model

Abstract

The invention discloses a design method and appearance of aerodynamic layout of a plane-symmetric concave surface standard model. The design method comprises the following steps: S1, designing a contour line of a head area of an aircraft; S2, designing a plane area contour line of the surface of the aircraft; S3, designing a concave curved surface structure of the aircraft; S4, performing curved surface fillet processing on the concave curved surface structure designed in the step S3 to obtain an aircraft structure appearance; the invention provides a novel aerodynamic layout design method for a flight test standard model with a plane-symmetric concave curved surface feature and a shape generated based on the aerodynamic layout design method, and an optional standard model scheme can be provided for research on boundary layer transition.

Description

technical field [0001] The invention relates to the field of aerodynamic layout design of aircraft, and more specifically, relates to a design method and shape of an aerodynamic layout of a symmetrical concave curved surface standard mold. Background technique [0002] Boundary layer transition research is an unresolved world problem in fluid mechanics. Carrying out research on the hypersonic boundary layer transition problem, improving the understanding of the mechanism of boundary layer transition and transition prediction ability technology, has a great impact on the aerodynamic performance and propulsion of hypersonic vehicles. The improvement of the combustion efficiency of the system and the refined design of the heat protection system are very important. [0003] Boundary layer transition research methods include wind tunnel experiments, numerical analysis and model flight tests. At present, there is no wind tunnel that can fully reproduce the flight conditions, maki...

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Problems solved by technology

At present, there is no wind tunnel that can fully reproduce the flight conditions, making it a difficult problem how to extrapolate the transition data from the wind tunnel to the flight data. Due to the unknown conditions of the incoming noise of the flight, the numerical simulation still cannot fully simulate the real flight conditions. The boundary layer transition case under

Therefore, at the current level of research, only relying on wind tunnel experiments and numerical calculations cannot fully reveal the transition mechanism of the boundary layer on the surface of real aircraft. It is necessary to use flight tests to study the transition of aircraft under real flight conditions and background disturbances.

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