A flying object needs 1G of lift to stay in the air. Divide 1G by the lift-drag ratio and you get the amount of thrust-weight ratio that the missile has to maintain to keep going. Fuel consumption is proportional to thrust. At least as a first order approximation, fuel consumption rate is constant regardless of how fast you fly. Thus, the flight time of the missile is a function of fuel fraction. By flying faster during this flight time, you go farther.
It's simple physics, and it's absolutely correct.
That is exactly what is called as bullcrap and misrepresenting science to suit your agenda.
An flying object requires 1g of vertical acceleration to remain steady.
If an object is moving in a vertical plane it has to accelerate more than 1g.The drag force is proportional to square of velocity and as the velocity of missile increases,drag force on missile increases.An hypersonic missile attains more velocity then a supersonic one.The missile has to exert more force to overcome air drag.Thrust requirement of a hypersonic missile is more not only because of higher acceleration that the missile would be have to partake but also because it has to overcome much more air drag compared to a supersonic missile.
In it's flight mode,a missile not only have to apply a force of vertical force of 9.8m[SUP]2[/SUP] to remain aloft but also has to apply an horizontal force whish is proportional to square of velocity
.Velocity of hypersonic missile is more than that of supersonic missile thus is a direct deduction from common sense that drag force being applied on an Hypersonic missile would be more than that of supersonic missile.Thus more thrust force would be required in case of hypersonic missile than that of supersonic one.
The thrust could be increased by following methods
1.By increasing the amount of propellent in a missile.This would lead to lower thrust/weight ratio.Increase in weight also increases the thrust required for acceleration of missile and could not be taken up if there are size constrains.
2.By increasing the efficiency of propellent.Very difficult.
3.To increase the efficiency of Engine.Most probable.
This is simplest of physics of motion of a body in fluid.
As the missile moves forward,it would use up fuel thus reducing it's weight.The missile would require lesser thrust to accelerate but it would not lead to reduction in drag force acting on it.The missile if moving at constant spped would require to produce same amount of thrust.
PS.Do not think that everyone else except you is stupid.You ignored a lot of variables in your assessment and tried to slip through using confusing jargons and self contradicting statements.
Obviously, going faster while generating only 1G of lift without lowering your lift-drag ratio requires you to fly at higher altitude, where the lower density makes up for the higher airspeed. But a hypersonic scramjet can do exactly this.
LOL
Scramjet engine is an air breathing Engine,it is not a rocket engine that could escape atmosphere.It needs to remain within stratosphere thus air drag cannot be neglected.
And anyway even in vacuum,Hypersonic missile would require more fuel than supersonic missile thus having more weight.
Consider that a missile is fired in vacuum.Thus air drag is not acting on that missile.Now compare a supersonic missile with a hypersonic one for same range.
The thrust required in this case by a missile would have zero horizontal component and would be equal to weight of missile in vertical direction when it is in cruise mode.Thus both missiles are equal on this front.But for these missiles to attain their respective velocities which in case of hypersonic is higher than supersonic,the hypersonic missile would require higher acceleration for same amount of time or similar acceleration for extended time.If the missiles are using same engine,hypersonic missile would require more fuel thus increasing it's weight.
The real problem is making a scramjet that compares in efficiency to an ordinary turbofan or turbojet. Obviously, this is no easy thing. But there is nothing in basic physics that rules this out.
The real problem with scramjet engine is that in order for scramjet engine to start,the body need to be travelling at supersonic velocity.Along with that a scramjet has lower thrust/weight Thus one always need to strap booster rocket to a missile in order to start scramjet.Efficiency of scramjet has to be compared with rockets as turbofan or turbojet engines are incapable of attaining hypersonic speed and scramjet engines come out with flying colours in that comparision because Scramjet engines does not have to carry oxidiser thus reducing their overall weight.
http://en.wikipedia.org/wiki/Scramjet
