So I did this today and now I'm starting to think the J-36 MTOW may be much higher than 50tons. Has this possibility been discussed here?
Note that the measurements on the first photo need to be scaled using the J-20's real dimensions.
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How do you know the J-20's distance in relation to the camera vs the J-36's distance in relation to the camera, and their angles, which affect perceived length when measured? You cannot assume that they are equidistant to the camera and at the same angle, allowing for direct comparison.
You missed my point. I was referring to available volume not automatically translating into usable space that you can go ahead and populate with whatever you want and how there are other limiting factors such as MTOW and structural loads that have to be considered. You are correct about using other aircraft designs as a reference point in order to calculate the range of another aircraft, however, I wasn't using the J-20 as a reference point, but rather as a best case scenario to make a point.
How is the J-20 a best case scenario? Aren't we moving forward and improving?
The canards on the J-20 are not there to help with dogfighting. They are there because the J-20 wouldn't function without them. The wings of the J-20 are pushed back and the span is kept narrow in order to conform to the supersonic area rule and keep the wings from interacting with the nose cone shock to increase supercruising speeds. Because of that, the center of lift is so far from the center of gravity, that the plane needs the canards to shift the center of lift forward. Elevons might not have enough pitching authority during takeoff and landing due to low air speeds, so the canards step in to keep the nose up. Lift is directly proportional to the surface area of a wing and the area of a delta wing gets larger towards the back, so the center of lift will also shift rearwards as the speed increases. The canards on a J-20 are large and have a long moment arm (long distance from the center of lift), which means they can provide high lift at high speeds without deflecting too much in order to keep the drag as low as possible.
I didn't say they added canards to make it dogfight; I said that they chose a root design with canards in order to confer dogfighting maneuverability. So of course it won't function without canards but it doesn't mean they couldn't have designed a jet without them from the start if they weren't concerned about maneuverability.
Your statement regarding the J-36 being more aerodynamically efficient than the J-20 is absolutely incorrect. Just because the J-20 doesn't look as clean and minimalistic as the J-36, doesn't mean it will generate less drag than the J-20 at supersonic speeds. The J-20 is an aerodynamics masterpiece, but it is not easy to see. Compared to the J-36, the J-20 is significantly smaller and lighter. It has a lower aspect ratio and is more biased rearwards. The designers went to great lengths to push the weapon bay as forward as possible and placed the wing as far back as possible in order to be able to trim the fuselage where the wing grew to reduce wave drag, which wouldn't have been possible with the weapon bay in the way.
So as you can see, the J-20 is designed for serious speeds. Once you venture outside of subsonic flows, the subject of aerodynamics becomes a bit counter intuitive.
I love the J-20. But I don't know what aerodynamically efficient means. Does it mean overall flight envelope superiority or does it mean efficiency in long distance high altitude high speed straight flight? If the former, then I would maybe agree; I still hope that Chinese aerodynamics has made significant progress in these decades but the latter, I see a J-36 superiority. You can optimize J-20 all you want, but it's not going reduce drag to below not having anything there. In any case, to the eye, J-36 looks cleaner, stealthier, more optimized for distance, speed and altitude, but less maneuverable. Of course, we will need numbers to say anything for sure.
This doesn't mean the J-36 won't be able to go faster, it will have more thrust after all. It just means the J-36 will be consuming far more fuel at speeds the J-20 is designed for. It is however likely the J-36 will be far better optimized for high subsonic flow than the J-20.
I'm not so sure about that. If it's a design optimization specific for it, J-36 could be consume less fuel to just glide forward quickly than J-20.