Recent content by nakas12

Unforunatley no I can't use that system. It's been used before too many time apparently.

Umm I guess. Now I'm a little confused about what you mean. A system that was applied a force such as a car would have a certain velocity that it would to reach like cruise control.

Ok sorry about that. But I'm thinking of having a system with either 1 or 2 degrees of freedom. I was thinking of a simple system where the input would be a force or torque and the output could be some kind of velocity or position. The transfer function our professor wants though is a 3rd...

Homework Statement Hello everybody I was hoping some of you could give me some some examples of some closed feedback loop mechanical systems. This is for my controls class where we have to design our own control system. I'm having trouble trying figure out some systems. I know one would...

But if you see the polynomial equation of A(x) = 1 - 0.8x + 0.8x^2; where the cross sectional area varies with the equation given. I already figured out A/A* which gives me an entirely different value from the ratio at the throat. The length of the nozzle is 1 meter and the throat area from this...

Ok I think I understand now. I just have one last question if you guys don't mind answering. I'm going to assume M = 1 at the throat. The area ratio for that is 1. A/A* =1. Would the ratio be referring to the area at the inlet over the throat area? Just want to make sure I'm doing this correctly

When I saw this problem though it said to assume isentropic flow except across the normal shock. Really the only problem I'm having is understand how to find the mach number at the inlet

Hmm ok. Well the problem I have been looking at involves a subsonic inflow and subsonic outflow. At the throat I am sure the Mach number will be 1 and will increase until the shock. After the shock the flow will be subsonic.The problem I am having is that I've been given the outflow and inflow...

Hey guys I was wondering if a symmetric C-D nozzle has the same area at the inlet and exit, can the mach numbers at both points be the same? This situation would involve a normal shock which would be near the exit as well. I would assume the Mach number at the throat would be 1. With that...

Homework Statement A system containing 10kg of water undergoes a reversible isothermal process. The initial state can be characterized as saturated vapor at 300°C. The pressure in the final state is 1MPa. The heat transfer during the process in (inKJ) Homework Equations Q = m(U2-U1)+W...