The SC
ELITE MEMBER
- Joined
- Feb 13, 2012
- Messages
- 32,233
- Reaction score
- 21
- Country
- Location
1. Wing loading is a very important factor. No need to split hair about whether wing surface area is 'only' one consideration. This just shows ignorance of engineering principles.
2. Engineering Factor is a routine methodology. Things are 'over-designed' for a purpose. For example for elevators the engineering factor is 10; meaning that an elevator cleared to carry 1000 Kg weight is designed to carry 10,000 kg. Similarly though JF-17 structure is designed to match its performance, the design limit would be significantly higher than the allowable max weight. 200% wing loading test just shows that the engineering factor is at least 2 in case of JF-17 wings. We can be confident that a higher thrust engine could certainly help carry higher weight.
3. If anyone recalls Dubai airshow demo of JF-17, towards the end the high angle of attack slow pass followed by a turn and steep climb shows that the aircraft is not under-powered as such. With a single RD-93 powering the aircraft, one can indirectly tell that the 'over-design' does not impact its performance in any apparent negative way.
4. As I observed earlier, if PAF thought that the aircraft had lesser range or too little loiter time, the last redesign could have lengthened the fuselage a little to improve fuel capacity. That did not happen and it clearly shows that there are no serious issues as such. JF-17 has had at least 2 redesigns (maybe 3) if I am not wrong. I do not think that the air-frame has any glaring deficiencies.
5. @VCheng , the day you can prove that the JF-17 airframe is 2nd generation will be the day I will take you seriously. You are wasting people's time by engaging in senseless discussions for the sole purpose of deflecting criticism of your statements. A couple of pages back I asked you to provide reference for your assertions ( JF-17 Thunder Multirole Fighter [Thread 5] | Page 272 ) just because you seemed to be pulling stuff from thin air. Your very inadequate reply only confirmed my suspicion. I decided not to embarrass you (whether you could possibly feel embarrassed is a valid question) and did not press the issue ( JF-17 Thunder Multirole Fighter [Thread 5] | Page 272 ). I would now very much like you to provide valid references for your questionable claims, which are:
a) "The initial planes had 4,000 lbs of internal fuel and the newer ones are closer to 5,000 lbs." Post #4065 made by you. My question about planes 'initial' and which planes 'newer' remains unanswered.
b) You seem to be implying that RD-93 is quite like old RD-33, ignoring obvious differences such as control over smokey trails, indicating better fuel usage and probably better fuel efficiency. (My post #4063 vs your post #4065)
c) Your assertion that "The construction techniques used for the JF-17 are a generation or two older than the ones used for the Gripen" (post #4101). It is well known that Gripen is fourth generation, by Western classification. So you are saying that JF-17 airframe is possibly 2nd generation. Saying such a thing takes some guts. You make it sound so casual. Let us see you just as casually substantiate your claim.
Is it its delta wing configuration and the canards that gives the Gripen its load capacity or is it the whole configuration design of the airplane, like its thin central body?