F-11a adopts a cantilever upper wing with variable sweep, and there is no dihedral angle. The airfoil is NACA64A series, and the conventional wing is negatively twisted (washed externally to reduce the attack angle towards the wing tip). There are five internal beams, with integral panel skins between the front and rear edges and from the wing root to the wing tip, and a honeycomb sandwich between the front and rear edges. There are full-span leading-edge slat and trailing-edge double-slit flap on the outer wing. The D6AC special steel box-shaped long beam, with a center of 4.2m, is connected with two outer wings by a pivot with a diameter of 2 1.6cm and a length of 50cm. The sweep angle is changed by a hydraulic actuator. After more than ten years of research by NASA, the variable swept wing has been applied in F-11. The wing sweepback angle ranges from16 to 72.5, and it is16 at take-off, 26 at landing and subsonic cruise, and the appropriate sweepback angle below 72.5 can be selected at high altitude and supersonic speed. The fuselage is a semi-hard shell all-metal aluminum alloy structure with honeycomb sandwich panel skin. Some key components are alloy steel and titanium. The structural core is a T-shaped longitudinal beam, and the engine is hung on the arm of the longitudinal beam.

The f-11a adopts a common cantilever swept tail. Except for the wingtip of the flat tail and the middle section of the vertical tail, honeycomb panels are used. Differential full-motion horizontal tail synchronization can play the role of aileron and elevator. The horizontal tail and the wing form a triangular wing at full sweep, with a gap of about 25.4 cm. The full-motion horizontal tail can not only control the pitch, but also cooperate with the spoiler for lateral control. The landing gear is hydraulically operated at the front three points. The two-wheel front landing gear retracts, and the single-wheel main landing gear adopts tripod structure. When retracting, the left and right wheel carriers rotate 90 degrees downward around the fulcrum, then merge with the wheels and enter the machine forward. The main wheel is a low-pressure tire with acceleration slip adjustment and disc brake. The door of the main landing gear is folded down at the bottom of the fuselage, which plays the role of speed brake in flight.

The f-11a is equipped with two TF30-P-3 afterburning turbofan engines, with a single thrust of 55.4 1KN/5650kg and afterburning thrust of 93. 16KN/9500kg. The total fuel volume of the fuel tank is 145 15 kg, and the aerial refueling port is behind the cockpit. The inlet is equipped with 1/4 conical adjusting cone, which is adjusted by computer, and is equipped with boundary layer baffle and spoiler. Two TF30-P- 100 engines were modified for Type F, with single afterburner thrust of11.80 KN/11400 kg, equipped with hydro-mechanical control intake system and adjustable shock cone.

F-11has many unique features. A plastic shield will pop up in the cockpit of F- 1 1 to "wrap" the pilot and the ejection seat like an egg. This kind of shield can effectively protect the pilot from the strong oncoming high-speed airflow during ejection. This design ensures that F-11pilots can parachute safely at zero altitude, zero speed or M2.5 Supersonic skydiving is a thorny problem in the aviation industry when it just breaks through twice the speed of sound, so it is so complicated on F-11 This system can even eject after the plane falls into the water, and there are examples of successful ejection from underwater 15 meters. Because of its complicated structure, this design is no longer used in the later ejection technology. For example, in some jet technologies, a net cover is used to block the oncoming airflow. Later F- 1 1 1 parachutes have replaced the earlier parachutes with a diameter of 2 1 m with a multi-parachute system consisting of three small parachutes with a diameter of 15.9 m..