Confusion ( conclusion of gas-gun series )

After looking over some of what I've been writing about recently, with respect to the gas gun, I'm confused.

The numbers don't add up.  I'm looking up stuff, but what I see doesn't make sense.

Anyway, that explains what I've been doing.  Nothing to write about until I get an answer.


Update:

Let's look at the equations:

1. The thrust equation:  Thrust equals Isp * g0 * mass flow rate.  An observation:  this looks like momentum.  Momentum equals mass * velocity.  Substitute mass for mass flow rate, and Isp* g0 for velocity.  This makes sense since Isp * g0 equals effective exhaust velocity of a rocket.  Thrust could be said to be nothing more than the momentum of the rocket's exhaust.  Note that g0 is constant, and Isp has a short range of between 200-450 for chemical rockets.  
2. The energy equation:  Kinetic Energy equation is : 1/2 mv squared.  What jumps out at me is the similarity between the two equations.  
3. Acceleration is what we measure with thrust:  the Acceleration is equal to Force divided by Mass. The acceleration constant is gravity at 32 ft/sec²    Therefore,  1 pound of thrust is equal  32 lb-ft/sec²   and substituting 1.5 million pounds of thrust for 1 in the equation gives 48,000,000 lb-ft/sec²    of acceleration.  How much force is that in watts?  How do we get from there to 12 gigawatts from an F1 Saturn V engine? 

Still confused.

Update:

Okay, now if you take the thrust of 1.5 million pounds and divide it by the mass flow rate of the F1, which is 5569 lb-sec obtain the ratio I obtained here of 269.   Multiply that number by the 48,000,000 lb-ft/sec² number and we get 12,928,712,515, but I don't know what the dimension is of that number.

Could be just a coincidence.  However, using the energy content, I obtained much lower energy numbers.  Other means of calculation were also less than the 12 gigawatts per F1.

Update:

Okay, I think I've got it now.   Since  Thrust equals Isp * g0 * mass flow rate, dividing it by mass flow rate again yields Isp*g0, or what is known as effective exhaust velocity.  Multiplying it by thrust itself gives the following:  Isp*g0*  Isp * g0 * mass flow rate, or just old mv ² as in #2 equation above.

So, what does it all mean?  It means that energy requirements are what drives thrust.  The energy requirements are increasing exponentially while thrust increases only linearly.  In other words, you need a lot more energy than what we know we can deliver from chemical means.  We need nuclear energy for large amounts of energy.  Can't get around this.  Chemical energy isn't good enough.

That concludes the series on the space gun.  Without a nuke, you ain't going nowhere.

The previous post in the series was here.