How much cost gasturb licence?

Hi everyone, I’m a final year undergrad aerospace engineering student. I was wondering if I could get some advice please on how to properly do a literature review for a dissertation ?

Workign at Lilium

Throwaway account because i have collagues in this sub.

I am working in an aerospace company (more than 10k employees) as a senior engineer. I signed a job contract with Lilium Gmbh in Germany (i am living in a different country outside EU) and i am supposed to start as a senior engineer but as some of you might know Lilium has filed for insolvency and is in a cash crisis.

Lilium HR told me that they would like to continue hiring process but if i want to cancel the contract that will be alright.

I want your opinion about the matter. Do you think Lilium is doomed? Should i take the risk and work there? My salary is not increasing much actually, i mostly want to work in Lilium because of the eVTOL product and better work conditions. If there is any Lilium employess out there an insight would be much appreciated.

i need matlab code to optimize a supersonic airfoil withing some givin constraints. i have a function clcdcms that takes imputs Minf alphad nsu (number of segments upper surface), nsl (number of segments lower), xu (array nsu+1 x-coordinate points of uppper surface (x/cord) yu( array nsu+1 y coordinate points of upper surface (y/chord), xl, and yl, abd oriduces iutputs Cl, Cd Cm, xmu (array of nsu elemnts; x coord(along chord direction) of Cp on upper surface), xml, cpu (array of nsu elementss; Cp on upper surface) and cpl. This airfoil design is to maximize the L/D ratio while having a min thickness of 10% of the chord, an angle of attack anywhere between 0 and 10 degrees, a pitching moment about the leading edge equal to or less than 0.1 in magnitude, and a coefficient of lif of equal to or greater than 0.3. the geometry of the biconvex airfoil is a parameterized Piecewise Cubic Hermite Interpolating Polynomial I would like for the code to use an exhaustive search method with the necessary nested loops. I would like for the end of the code to display the output variables and plot the shape of the airfoil. Where 0< x u,l < 1 and 1/3< x tu,til < 2/3, where, tu and tℓ are respectively upper surface thickness and lower surface thickness; xtu and xtℓ are respec- tively the location at which tu and tℓ occur, which are the shape control parameters. It is okay for the code to accept more than one airfoil as long as I am able to see the results to determine which has the best L/D ratio.

I have done some coding and I believe I’m getting an airfoil just not the optimized one. I’m not sure where my mistake is, although probably in the exhaustive search. With M=3, My airfoil has an aoa of 9.3, cl 0.3, cm 0.0979, and L/D of 3.11, which does not align with typical optimizated supersonic airfoil values.

Any helpful advise or links or instructions on any information about such a project or the exhaustive search method would be great, thanks.

I'm soon starting work within the UK's Royal Navy. Despite being listed as an Aircraft Engineer, my role is essentially a lead aircraft mechanic/ technician on a supersonic Jet.

I'd like to work as a Test Engineer on supersonic+ aircraft (or even rockets), where I can conduct engine performance tests on afterburning turbofan, ramjet, and scramjet engines and/or wind tunnel testing at companies like NASA, and Concorde project startups for example. A career goal e.g. would be a test engineer on experimental aircraft like NASA's X-43 (I know it's old, just an example).

The intention of this post is that I'm unsure as to whether the Navy role is going to be useful for where I'd like to end up. I would have a minimum Return of Service upon employment; I'd like to be sure of this job's utility before accepting my offer. What type of experience/ jobs and education combination would be most advantageous?

I hold an HNC in Aerospace Engineering from a top 100 global university. In the next few years, or immediately, subject to whether or not I accept the job, I will complete a BEng in Aerospace Engineering through the military (funded) or otherwise.

I am a pilot who is also into 3D printing, and would love to start designing/printing RC plane models. I do have a subscription to Fusion AutoCAD 360, I was wondering if anyone would know how effective this software would be in helping me accomplish my hobby RC plane ventures? If you have a better software platform you would recommend, I’d be open to hearing about it. Any tips are appreciated

I am a third year bachelor's student studying aerospace engineering. I am quite lost as to what I am passionate about in the field or even outside of the field. I do not enjoy the design, manufacturing, and testing phases I have done on project teams, and feel that my current part time employment in operations does not have enough problem solving on the day to day job. I believe my greatest strength to be analyzing large amounts figurative or literal variables at once and figuring out what to do first, what to tackle, all the way down to the small details.

Does anyone have any advice on any specific roles, or niches I should look into and be more aware about? I am very open minded and am not opposed to switching fields at this point.

And if you wanted to settle into the GCC countries, what certifications or experience would you be aiming to get during your years in university in order to cater for the GCC market in the years that you’ll be graduating? Would you be looking to do a PhD to help you in that?

I'm an Aerospace Engineering student responsible for the Aerodynamics portion of a Quadrotor drone project. After searching for BEMT software to analyze rotor options for our drones, I found JBlade, which has a graphical interface and includes XFLR5 integrated within it (or so I thought). However, I haven't been able to compile it on my Debian 12 system due to issues with lgqlviewer.

I'm using this GitHub repository - https://github.com/MrTypename/jblade-code. Has anyone worked with JBlade before? Any suggestions are welcome!

on podcast Cleaning Up #121, Prof Rob Miller from Cambridge's Whittle Lab talks about how a hydrogen airplane might be feasible. He says that retrofitting an existing aircraft wouldn't be economical. However, if you redesigned the plane to have a much longer fuselage, you could store sufficient hydrogen as a gas, adding drag. You could redesign the wings to have less drag. overall this increase and decrease in drag would cancel out.

I can't find any more details on the internet. what are your thoughts?

Hey everyone! I have a balloon project idea I've been working on for a couple of months, but I’m not sure how to get started and keep it low-cost. The goal is simple (well, sort of!): launch a balloon, have it float up, and then land it back in the exact spot it took off from.

Here’s the idea so far:

1. Preventing Over-Expansion: To stop the balloon from bursting as it ascends, I’m thinking of connecting it to a nozzle that can release gas if pressure builds up too much. This vented gas could even be ignited to produce a tiny bit of thrust (nothing huge) to help guide the balloon back horizontally.
2. Fuel for Extra Thrust: I’m considering storing some kind of fuel on the balloon to create additional horizontal thrust, but I’m worried it might make the balloon too heavy to carry any other load.
3. Using Wind for Drift Control: If the balloon drifts eastward on the way up, my thought is that, with a bit of help from a westward wind during descent, it could get closer to the launch site.

The big question: where do I start testing? I’m looking for a low-cost, step-by-step path to bring this idea to life.is is it feasible idea to work on? Thanks for any guidance!

Sorry as this is more of a legal/political question, but I figured someone here would know as it pertains to the space.

I'm applying in the U.S. to be either an aerospace engineer or a mechanical engineer.

However, I visit Russia every year, since my extended family lives there, and have done so since I was 10. I do not(and never have) have Russian citizenship(only a Visa for "tourism"/туризм), although one of my parents in America does, I was born in America, and have not spent longer than 3 weeks in Russia.

My question is that if I worked at a facility/company with sensitive information, or was given security clearance, especially as it relates to government information/documents, especially as an aerospace engineer, would my connection to Russia prevent me from getting a government(or government-adjacent) job in Aerospace, or once I got the job, would I be permitted to visit Russia(which is of course considered an "unfriendly nation") as I continue to do, for the same amount of time?

Therefore if I don't decide to do an aerospace engineering degree and instead go for a mechanical degree, would this be (more)advisable for this situation?

Thanks a bunch.

For background i am talking about a UAV with a micro-jet engine with high rpms. All i can find is that for propeller aircrafts the precessional effect is large but for jet engine it is negligible. But if a UAV rolls/yaws after takeoff can we say it can be due to gyroscopic precession?

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Mi-26 (20 tons max payload)

The two biggest helos are the Mi-26 and the CH-53E/K, which can respectively lift 20 and 16 tons. One has two engines and eight blades; the other has three engines and seven blades. What determines the payload a helo can lift? Do power-to-weight ratio and the number of blades matter the most?

Bonus question: Just for fun. If I were a crazy Russian engineer and wanted the Mi-26 to lift 200 tons instead of 20, what could I do?

By popular demand, proposed aircraft or spacecraft designs, 'will it fly', etc. posts will now be removed and directed to r/ImaginaryAviation per new Rule 3. This seems like a good way to encourage people to still be curious but better direct these types of posts.

Hi all, I’m curious about the biggest challenges currently facing A&D Industry. From what I’ve gathered, complex supply chain and high production costs seem to be the more prevalent issues.

1. A&D industry relies heavily on complex global supply chain for specialised parts and materials. Disruption (like pandemic) can halt production and delay projects

2. A&D industry incurs high production costs due to the safety standards, long development cycles and complex process.

But what do you think? I’m sure there are more more problems I haven’t mentioned, Look forward to hearing everybody’s thoughts

How does aircraft design and its performance parameters are influenced by air traffic control requirements in its preliminary or conceptual design phases?

context: I have a glider with a delta wing design where the wing tips have vertical tails pointing downwards.

My question is what softwares can I use to simulate the glide performance of my design? The parameters I am most interested in are the CL, CD, glide speeds/angle!

furthermore, how does trimming the control surfaces affect these values? and how does varying the wing loading for my glider such as by increasing the mass or wing area affect the parameters mentioned above!

Right now based off a quick search on the internet I found that the most user friendly (for a beginner me with limited experience and knowledge) could be XFLR5.

Thank you for the help! Do correct me if I am misinterpreting any aerodynamic concepts!

I come here as an aerospace engineer interested in serious aero engineering topics, news, information, and discussion. Instead, I feel like the average age of this sub must be 14, given the number of basic airplane doodles showing up in my feed with a caption asking if this design will work. It’s great that kids are interested in the topic, but I don’t feel like this is the right place for that level of discussion. Or maybe limit it to once a week or something. It’s just hard to take this sub seriously anytime I see one of this posts pop up. Sorry for the old person rant!

From what I understand, the aggressive sweep that delta wing aircraft generally have, help with lift at low speeds due to vortices at the leading edge helping maintain favourable airflow over the wing's upper surface at high AOAs.

After going through Polhamus' papers, I want to know if this concept could be applied to an aircraft that has a span of 50 to 150 centimetres.

1. What were the steps you took?
2. How long did it take?

Hi everyone! I got a job as a couple months back after graduating to work on manufacturing aerospace structures for ~$70k/year. I figured it was probably because I'm entry level atm, so I was wondering what kind of salary I should expect once I get some years of experience in the industry.

I really love my job, but I'd like to ideally hit six figures at some point (especially considering how much time and money I put into my education for aero/mechanical engineering), but idk if I'm being overly optimistic about this or if I'm selling myself short with my starting salary. Any help to get a general idea would be nice. Thanks!

https://preview.redd.it/9yb1lmlzzcxd1.png?width=2576&format=png&auto=webp&s=be0496552098b46ed96c7b4dd11c0209ec3e2b98

Hello! I'm a bit confused about these tail configurations in aviation. Some sources refer to them as inverted-U, some as boom-mounted, and others as H-Tail. Is there a generally accepted term for this? I'm researching for an assignment, so I need to be certain about the accuracy. Could you please share sources if you have any?

https://preview.redd.it/hyk4lsz41dxd1.png?width=375&format=png&auto=webp&s=e93fe8465533cbdf828f7d8af88706c9de986464