ADA AMCA - Advanced Medium Combat Aircraft

[Sixer]

Isn't 10.5kw cooling capacity for 5th gen radar a bit less ??

F-35 has much higher, specially block 4(current one).

It is good enough. F-35's new cooling capacity is for all the electronics onboard, not just for the radar.

Let's say, AMCA's GaN TRM has 20 watts peak power. So at 300khz PRF (highest for the radar) with a pulse width of 1 µs it will have average power of 6 watts. So with 1530 active TRM, the aperture will have 9.1 KW of average power. And if assumed DRDO managed to achieve overall TRM efficiency (not PAE of GaN amplifier) at 20%, you will end up with 7.2kw of wastage. Which is well within the capacity of 10.5kw cooling system.

Rest can be used to cool back-end processor and other LRUs.

PS: afaik, radars barely operate at such high PRF. Though you can have lower PRF and higher pulse width.

Also not all TRM transmit at the same power. TRM at the edges of aperture area operate at lower power than those in the middle to optimise beam forming and suppress sidelobes. This is called amplitude windowing. So there is that.

 

[screambowl]

As general citizens we can observe that it's happening in all stealth jets, manned & unmanned.

I am not sure if F22 or F35 have any sort of such edged elevation in the inlet duct. But there is a possibility of a slope which could be observed along with the curved surface area at the rear near the cylindrical segment like in the picture below, with a non uniform width and shape throughout to slow down the air speed as you mentioned.

A curved surface area will make the collision with air molecules less non elastic and bend the incoming air smoothly, curved surface with an elevation/slope .

https://www.aerospacemanufacturinganddesign.com/article/technology-for-complex-advanced-materials-structures/

Inside the inlet duct you can observe the grooves to optimize the airflow.

 

[Bhartiya Naagrik Sainik]

I am not sure if F22 or F35 have any sort of such edged elevation in the inlet duct. But there is a possibility of a slope which could be observed along with the curved surface area at the rear near the cylindrical segment like in the picture below, with a non uniform width and shape throughout to slow down the air speed as you mentioned.

A curved surface area will make the collision with air molecules less non elastic and bend the incoming air smoothly, curved surface with an elevation/slope .


View attachment 53800

https://www.aerospacemanufacturinganddesign.com/article/technology-for-complex-advanced-materials-structures/

Inside the inlet duct you can observe the grooves to optimize the airflow.

View attachment 53801

By edged elevation if you mean straight duct segments instead of curve, then i already mentioned "theoretical straight segments"

Theoretical straight segments

I can also make the duct more curvy but it'll create more polygons which is good for realistic design but bad for old computer.

The grooves are probably to handle the boundary layer air of the duct.

 

[screambowl]

By edged elevation if you mean straight duct segments instead of curve, then i already mentioned "theoretical straight segments"

Okay I ignored that point , appologies, but overall these are pure experimental physics. You design a model and then you simulate fluid dynamics and then calculate pressure at every point.

The grooves are probably to handle the boundary layer air of the duct.

Yes at super sonic speeds and hypersonic speeds, and for acoustic suppression.

 

[Bhartiya Naagrik Sainik]

Okay I ignored that point , appologies, but overall these are pure experimental physics. You design a model and then you simulate fluid dynamics and then calculate pressure at every point.

Yes, today's 3D CAD S/w have got features of simulating physics, particles, fluids, collision, etc. Then industrial grade custom manufacturing S/w have much better capabilities.

Yes at super sonic speeds and hypersonic speeds, and for acoustic suppression.

At every speed.
Hypersonics IDK but for supersonic jets the air needs to slow down below Mach 1 before entering intake if possible, so inside duct it'll be subsonic.