Yes. I remember a certain (unidentified) payload that was attempted to be integrated, caused wing fluttering and the crash.
Flutter exists due to either the wing's structural integrity issues ( less likely) or
it exists due to the control surfaces whacking out ( most likely).
So does Mirages and our F-16 (older one) have same aluminum airframe, they can go supersonic but JF-17 can't, what a logic you have sir, I am sorry to say
No it is not like that, the air-frame is an alloy, pure aluminum is too soft.
and as I have mentioned before the chances of the airframe structure restricting speed is unlikely; it's the control surfaces which are to be blamed mostly.
Aren't the JIGS and procedure provided by CAC ? or are you implying that PAC is not following the proper procedures set forth to produce the modules / parts ?
At the end these are same folks that have kept the M-III/V flying for so long.
Also on side note, weren't the wings strengthen for B-III, could be the reason that Block-I & Block-II may have had wing structural issues due to loading ? I am just grasping for straws here though, as the saying goes ' too thin.'
A Jig is only responsible for making sure the different parts of the fuselage are put together properly. It has nothing to do with making sure the aircraft will handle the load once it is built up right.
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So here goes, you can actually put the aircraft together and test the G limits ( which is in principle weight ) without it flying.
So for example if the wing spar structure are designed for handling 9G, that means 9 times the normal weight. This can be tested on ground.
What cannot be tested are the aerodynamic characteristics.
Tran-sonic - Supersonic and then back creates a whole new dimension both for the aircraft and the weapons. There is very little you can do except for trial and error and then building a huge knowledge base on those experiments.
Rest assured the JF-17 can do all the things you want it to , and there is nothing wrong with the design and engineering.