In recent years, with the rapid developments of technologies such as adaptive technology, intelligent materials, miniature high-energy actuators, and flexible skins, many studies have been conducted on the variable swept wing. Of course, there is also a great part of research dealing with the morphing of wing control surfaces like ailerons and flaps. Most studies related to morphing aircraft have focused on the morphing of wings, as the wing is the primary source of lift and handling force. Thus, it is necessary to investigate further the morphing aircraft’s configuration and morphing mode to better balance adaptability to environments and flight performance. defined the objectives of morphing aircraft as efficient flight and multipoint adaptability to macro- and microenvironments, implying that morphing is the bridge between flight mission and flight performance. Further, it is also featured by economic cruise, surveillance, rapid arrival, and penetration in modern warfare. As for the transonic intelligent morphing combat aircraft, the advantages are focused on short take-off and landing distances, good acceleration performance, and supersonic flight capabilities. In military application, its good performance is mainly reflected in the cross-speed domain, cross-media, and other aspects. Morphing aircraft is one of the most important development directions of advanced aircraft in the future and is at the forefront of innovative research in the aerospace area. The influence from upstream components is proven to improve the aerodynamic characteristics of the rear wing, especially at.
![aerodynamic aspect ratio calculator aerodynamic aspect ratio calculator](https://wingsofaero.in/calculator/wp-content/uploads/sites/8/2021/06/cropped-TEMS-Calculator_transparent-300x250.png)
The increase in the angle of attack, incoming flow velocity, and distance between the front and rear wings can reduce the interference between front and rear wings. Meanwhile, the flow field characteristics and interference characteristics of the front and rear wings are studied. The lift ratio of the front and rear wings shows a good similarity at different Mach numbers, especially for the 15° model, and the value eventually tends to be 1.3 at. Compared with traditional morphing aircraft, the main advantages of this configuration include better transonic and supersonic performance, better lift characteristics in the state of a high-aspect ratio, and lower zero-lift drag in the supersonic state.
![aerodynamic aspect ratio calculator aerodynamic aspect ratio calculator](http://vashivisuals.com/wp-content/uploads/2016/02/ShootingRatiosC3.jpg)
The maximum lift-to-drag ratio is about 13.5 at and, 12.8 at and, and 3.4 at and, respectively. The compressible Navier-Stokes equations in the conservative form are solved to analyze the configuration characteristics and the aerodynamic benefits of this aircraft with different values of sweep angle (15°, 60°) and Mach number. This paper presents a new-concept aircraft with a diamond joined-wing morphing configuration, which simultaneously adjusts the sweep angles of both the front wing and rear wings by a telescopic support rod.