The transition area between the wing and fuselage of the aircraft obviously adopts the wing-body fusion design, which not only has small "penetration" area, small resistance and small radar cross-sectional area, but also greatly strengthens the structure and expands the internal volume of the aircraft. It can be seen that the fuel load coefficient in the aircraft is high, and the range and operational radius should be large.
Therefore, it can be inferred that the penetration performance of the aircraft at high altitude, high speed and low altitude should be very good, which is obviously superior to the aircraft schemes of F- 16 and F/A- 18M with fixed and non-adjustable inlets.
The main landing gear of J- 1 10 is the "outer splay" fuselage landing gear. Compared with the scheme using wing landing gear, the lower surface of the main wing is "clean" and is not affected by the retraction of the main landing gear, so more pylons can be arranged. Moreover, some longer, larger and heavier loads can be installed at the wing root. This can be seen. Its plug-in ability is strong.
The main landing gear of the aircraft is relatively backward, and the tail wiping angle is relatively large. According to the photo analysis, during take-off and landing, the front wing is tilted upward and the flap is tilted downward. Compared with foreign gusts and eurofighter typhoon's related wing deflection during take-off, it can be inferred that the short-range take-off and landing performance of J- 10 is better than that of foreign fourth-generation fighters under the same conditions.
There is a certain relationship between the tail wiping angle of aircraft and "anti-chamfering". Through "reverse chamfering", the position of the center of gravity of the whole machine can be basically determined. According to the setting of J- 10 main landing, the center of gravity of the aircraft is relatively backward, far away from the position of the canard front wing. There is only one explanation: the aircraft is statically unstable, and the aircraft that relaxes the static stability redundancy must be equipped with a fly-by-wire control system.
There is no doubt that the J-10 fighter with tightly coupled canard layout, wing-body fusion, fly-by-wire control system, adjustable abdominal inlet and other advanced technologies will be an excellent aircraft with large maximum lift coefficient, large available trim lift coefficient, small wing loading, low supersonic drag, good maneuverability in middle and low altitude, strong external storage capacity and short take-off and landing distance only from the point of view of aerodynamic characteristics.