Designing a MATLAB Lunar Lander: Finding v

[negatifzeo]

Homework Statement

The task is to design a MATLAB program reminiscent of the text-based lunar lander games. Ol, that's not that bad. My problem comes from the research, specifically determining what thrust will be provided from what rate of fuel burned. I know that thrust=(dm/dt)v where v is the relative velocity of the exhaust. I know the max thrust the lunar lander was capable of was 44.4 kN and the min was 4.7 kN. I know the lander had 8165 kg of N204/Aerozine-50 as fuel. Does anyone have any idea what v is or how I can find it?

 

[Filip Larsen]

Several sources specifies the specific impulse to 311 sec which gives an exhaust speed of around 3050 m/s.

 

[negatifzeo]

Thank you so much. Do you think you could post a link to one of these sources? Normally I'm capable when using the google; I don't know why this information has been so difficult for me to find.

 

[Filip Larsen]

The top hits of http://www.google.dk/search?q=lunar+lander+descent+stage+specific+impulse gives the number without reference.
From the third link on http://history.nasa.gov/alsj/alsj-LMdocs.html you can find a lot more details on the DPS but it doesn't quote the exhaust velocity or Isp directly.