This is just a master's thesis. It is hard to believe that the author's supervisor would allow the use and disclosure of unencrypted data.
Shenyang next gen combat aircraft thread
- Thread starter Blitzo
- Start date
Lots of advanced research are outsourced to universities which in turn becomes some poor overworked postgrad's research topic
Yes and no. Even if it is handed over to postgrad, they will not be allowed to publish the results without authorization.
True, nonetheless this paper’s intake design deviates from the prototypes quite significantly so let’s not jump to conclusions with its results
the m1.8 supercruise is huge if true. Also, could this special intake be the reason for the groove?
EDIT: oh my god r/aviation is straight up crashing out over this photo right nowI have never seen this much cope
What would I give to be a fly on the wall when they test the top cruise speed of this thing, not that it is all that important in modern air combat but still it gives me the shivers. Clean profile, no verts, novel intakes, 2D nozzle, adaptive-cycle engine.... man
Not really "huge." The F-22 can supercruise at at least M1.76 and I expect that the J-20A can too. What would be more impressive is if it can sustain it for much longer.
Yes.
Very interesting design choice, boundary layer suction here could possibly keep flow from seperating at higher AoA. The forebody of this aircraft may work as a less energy efficient strake to generate vortices, if so, the more energy taken away means eaiser for flow seperation to happen at high AoA, so thise device is needed. It could also be that this body's aerodynamic is closer to a flying wing and flow seperation above fuselage is a great loss of reference wing area, and therefore enough to be considered a stall situation. Either way, this is likely to be used to delay stall at low speed, so it's an emphasize on agility at low speed, consistent with the TVC design choice.
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Firstly I think the porous section on the back is likely used as a “exhaust”, if you will, of the boundary suction plate on the intake wall, and doesn’t suck BL from the back of the aircraft.
Also if you manually remove BL on the top of the fuselage in a high AoA case the low-pressure region becomes worse no? I’m a bit rusty on aerodynamics but iirc boundary layer suction on fuselage or aerodynamic surfaces is primarily to improve cruise efficiency and not high AoA performance (as laminar flow tends to detach sooner than turbulent flow)
It is possible it act both as an exhaust and helps delay flow separation. As it suck air from the intake lips and pump them out the back can increase air pressure on the topside. Not sure how much it is helping though or whether flow size matters
Was not aware that it can supercruise that fast. I gotta admit, that thing is a force to be reckoned with. I wouldn't wanna mess with it even if I was in a J-XDS