Specific Impulse: Physical Meaning and Rocket Implications

AI Thread Summary
Specific impulse (ISP) measures the efficiency of rocket engines, defined as thrust divided by the propellant mass flow rate and gravity. Higher ISP indicates greater efficiency, allowing rockets to achieve faster speeds, though it does not solely determine top speed, as fuel ratio also plays a crucial role. Chemical rockets have an ISP of around 450, effective for launch but inefficient for deep space travel, while advanced concepts like nuclear pulse rockets and antimatter engines have much higher ISP values. Actual ISP is influenced by factors such as ambient pressure and nozzle design, differing from theoretical ISP values. The discussion also touches on interest in the X-33 project and its scramjet engine design.
Clausius2
Science Advisor
Gold Member
Messages
1,433
Reaction score
7
What is the physical meaning of the specific impulse?. All i know is what I've read in rocket informations. Its dimensions are s^(-1), and appear as one of the principal variables in rocket engines.

Thanks.
 
Physics news on Phys.org
I think it means, "The speed and how effeciently the exhaust of a rocket helps you."

The higher the specific impulse, (ISP) the faster you can go. Chemical rockets (ISP = 450) are relatively ineffecient for going to stars, but highly effective for getting off the planet. With the exception of nuclear pulse rockets (ISP = 10,000), acceleration is faster with lower ISP. Thus, an antimatter-matter annihilation rocket will take centuries just to accelerate to near the speed of light, as it's ISP equals around 280,000.

Glad to be of service.
 
You're sort of right, LF.

It is the efficiency of the rocket, but it doesn't define top speed. The combination of Isp and the fuel ratio of the rocket determine your final speed.

Specific Impulse is defined as:

\frac{T}{dm/dt * g_0}

where
T is the rocket's thrust
dm/dt is the propellant mass flow
and
g0 is the acceleration of gravity at Earth sea level.

The units are 'seconds', not s-1

The term basically sums up how efficient a rocket engine is. For any specific propellant combination, you can make a different engine which produces more thrust, but the mass flow will increase proportionally.

The theoretical Isp, which is what is listed for propellant combinations is a function of the propellants alone. Actual Isp is lower, and also depends on ambient pressure and the geometry of the expansion nozzle. The actual Isp is what is listed if you're looking at specific motors.

Isp * g0 is also the velocity of the exhaust plume relative to the rocket in units defined by g0
 
Semi-mea culpa. *grins*
 
Good explanations, guys.
Thanks.
 
And congratulations for the record of velocity of the X-33 proyect(is this its name?. I've watched it today on the TV. USA is USA, as we say here.

I could question this in the article of the hypersoar program, but since I'm here now: in which web page i could see the internal design of the X-33? I'm referring to Scramjet engine. I haven't had success in looking for one really good.
 
Due to the constant never ending supply of "cool stuff" happening in Aerospace these days I'm creating this thread to consolidate posts every time something new comes along. Please feel free to add random information if its relevant. So to start things off here is the SpaceX Dragon launch coming up shortly, I'll be following up afterwards to see how it all goes. :smile: https://blogs.nasa.gov/spacex/
Back
Top