u/Himiko_S_Blackflower

Prototype aircraft meets STOL, TWR, sustained turn rate, top speed, and post-stall capabilities excellently but fails in endurance, roll authority, Pugachev manoeuvre, and aerial refuelling. The airframe cannot handle more than an instantaneous 22 g. Aircraft is semi-carrier capable but arrestor structure is still being designed. The aircraft meets unpaved runway and crash landing requirements exceedingly well.

Note that this version of the airframe features a significantly shortened fuselage and lifting-body profile more in accordance with its Su-30 design heritage than the F-15 or EF2000. The vertical stabiliser is changed for a splayed V-tail for reduced RCS with added benefit of authority in pitch and yaw axes. Internal weapons bays are not yet modelled. Additionally, rearwards RADAR/IR/ECM pods on the tips of the Vstabs and within the tail boom are not modelled, but will be integrated in a similar fashion to the Su-30 and Su-57.

In summary, the craft will be powered by 3 LP, 8 IP, and 3 HP stages, with a target TWR stationary of 1.16 and a target ability to take off with reduced fuel load within 600 m. The engine manifolds are equipped with partial-S duct and variable-geometry shock ramp/cones with internal bleed inlets for low-speed flight. An upcoming version may feature upper surface inlets for high-AoA post-stall flight, but this will further complicate the vortex lift provided by the strakes. The primary inspiration for the powerplant is the GE F110.
The wing sweep is increased to 55 degrees and the CoM is shifted rearwards. The canards are moved rearwards and angled up 35 degrees to be coplanar with the leading edge of the wing. The wing area is increased by 2 m^(2) and the yaw control surfaces on trailing edge of the wing are simplified.
A defining aspect of the craft's characteristics are its large, lifting strakes which counterbalance its far-back CoL, augmented by high control authority one-profile slab canards. These features were more prominent in earlier designs, though once vortex geometry and area ruling around the nose is resolved, the strakes are intended to create a significant amount of total lift, enabling the wing to be swept further back and the canards further forwards.
To compensate for the loss of control authority, small slab elevators are mounted at 45 degrees near the end of the engine nacelle, intended to provide multielement lift following the elevons' deflected air. These are a temporary solution as they increase RCS geometry, though stealth was never the first priority of the design; they will not be moved coplanar to the main lifting surfaces.
At the cost of copilot visibility, the copilot's seat was lowered so the cockpit bears a closer resemblance to that of the F/A-18D rather than its major Su-30SM inspiration. The geometry of the strakes is also reshaped to be more similar to that of the F/A-18D rather than the E/F variants or MiG-29.
The airframe is being continuously improved for a target top speed of Mach 3.1 at altitude; the current airframe is largely incapable of breaking Mach 2 due to wave drag. Earlier concept art was not simulated or modelled due to aerodynamic issues with wing sweep.
Suggestions on improvements are welcome but please be constructive.

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Later designs will feature reduced RCS, kamikaze/decoy drones integrated into the airframe, and an updated wing dogtooth and canard geometry. The wings feature a distinctive lambda configuration and multi element trailing edge flaps inherited from B-21 Raider and Shenyang J50. Aerodynamic data for the dogtooth (incorporated in versions with leading edge control surfaces) will be sourced from MiG-23 and F-15 Fighting Falcon or more suitable aircraft.

Placement of main gun is difficult due to interactions with wing strake vortex and intake geometry when supersonic (even accounting for the internal geometry of intake manifolds not shown).