Recent content by wav3 r1d3r

Yea Waikiki is the big tourist/modern busy spot. I'm guessing that's why AIAA chose the spot.

I hate leaving the island for school, if I could I'd spend my time at the beach with my board. That's a bummer chilling on the beach is the best

Mahalo to the both of you! You helped a great deal. Thanks for helping me see that the throat condition can be M>1 but only with the supersonic inlet condition. I can definitely study for my upcoming test a little easier :smile: Thanks again!

Ok the question reads: For the system Ma=2.0, Aa= 20cm2, Throat Area= 15cm2, Shock Area= 22cm2, and exit Area= 25cm2. With the working fluid behaving as a perfect gas with constant γ=1.3, find the following: Mach at Throat Exit Mach Number Ratio of exit static pressure to static pressure at...

Ok well I resolved the problem again and showed my professor the answer in which M=1.662 at the throat and he validated my answer. So, based on that I can say Mach number at the throat can be greater then one but it depends on your initial conditions

Does that mean M=1 is the max that can be seen at the throat?

ok so Mach at the throat will always be 1 no matter what. This also includes the initial conditions? Because by using the above initial conditions I found Mach to be equal to 1.662 at the throat, but this goes against what you and my professor have defined. Would the problem then be...

I have a question on Gas Dynamics, we were going over a problem in class in which the problem asks to solve for the Mach number at the throat of a converging-diverging nozzle. I assumed that the Mach at the throat should be equal to 1 since the professor said it was impossible to have a Mach...