Harvard student? Good at the interwebz? need help finding a paper.. +k

Nah, unfortunately I don't have anything good to offer.

I can offer you my friendship and some vibes toward finding what you need. Unfortunately that's all I got :(
 
yeah it's just tough getting anything here, even with full access. Anything NASA or US govt. related is pretty much impossible unless you're a US citizen/enrolled at a US uni
 
Bringing this back as I need this god-forsaken article ASAP!

I'm pretty sure a Harvard account should be able to access it!

Here's the full citation: J.M. Seiner, M.K. Ponton, B.J. Jansen, and N.T. Lagen, "The Effects of Temperature onSupersonic Jet Noise Emission," DGLR/AIAA 92-02-046, DGLR/AIAA 14th Aeroacoustics Conference, May 11-14, 1992, Aachen, GERMANY
 
I can't help you but you could try emailing someone at Harvard or even the author of the paper if you can find their email. If you bug enough people you will probably get your paper. Make up some BS about being an aspiring student if you have to.
 
sorry, but i didnt find your exact article. i dont know if you needed that specific one, or just needed the subject matter its on and thought by the title that it was promising, but i found plenty of other good stuff on that topic. lemme know if you want any
 
sorry, none of the engineering journals/databases I have access to have that paper, I even checked my old high school's because ProQuest has a copy of it, but their license doesn't seem to cover that section
 
Do you need a source for a paper or is this for a project? For most noise pollution analysis we model the dissipation as damped harmonic wave propagation. Temperature increase will have an exponential decrease dampening, the sound wave will travel further.

Honestly, humidity will have a much larger affect.
 
I'm modelling a supersonic axisymmetric jet in OpenFOAM and I want to check their nozzle geometry. My supervisor gave me the stagnation pressures and a few other key values from that study but he won't, or can't give me the full paper.
 
Use your stagnation pressures, and other data to calculate the Mach before and after the shocks, and use those to find the turn angle. Write a script using MATLAB or the equivalent to run the limit of these, and you will be able to get a good approximation of your nozzle.

If you need to determine the expansion section of the nozzle, assume isentropic conditions and run in reverse. You can then use this as a base and adjust it as you see fit based on your calculated errors.
 
I've already made my nozzle using MoC, but I need to make some comparisons to widely accepted papers, which this is, it's just not widely available apparently!
 
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