I've been looking everywhere for a formula on how to work out a thrust-to-weight ratio, to help with working out the thrust-to-weight ratio of a U-2
recon aircraft. If any of you know anything about this, then please reply.
Off topic here, how can a thrust-to-weight ratio of 0.8 - 1 power an aircraft to take-off speed? Wouldn't the thurst need to be above the weight to
get the plane fast enough to T/O? Or am I missing something?
I know that such variables as air-pressure need to be controlled to give an accurate reading, but all I need is a roughly approximate answer.
Just divide the engine thrust by the aircraft weight (making sure to keep your units consistent!).
As for the aspect ratio, a higher aspect ratio wing will produce less induced drag, thus allowing a smaller powerplant to be used. Its limitation is
mostly structural, forcing the aircraft to operate at slower speeds and lower g-limits.
A thrust to weight ratio in excess of 1:1 is only required for vertical take off. As conventional planes use wings for lift rather than engines most
aeroplanes don't come anywhere near 1:1. The engine only has to move it along the ground fast enough to induce wing borne flight. Think of yourself
and a heavy object, like maybe a car thats broken down. It is much easier for you to push it along the ground, which you can do by yourself, than it
is to lift it up, which you can't. If that doesn't help just ignore my ramblings
Yes that is correct, some fighter aircraft which have a higher T/W ratio of 1:1 will accelerate even if they go straight vertical. Most other planes
would loose speed if they did that and then they would eventually stall.
Now even fighter aircraft that have a high T/W ratio will stall if they continue to go vertical because the higher they go the thinner the air and
their engine performance will decline, this in turn would reduce thrust.
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