To get the airfoil characteristics (CL, CD, COP, pressure distribution) use a software like Xfoil...
If the structure is very rigid you could get the pressure or forces and apply it to your structure.
If you have a quite slender, flexible wing, then you need to do an aeroelastic analysis, this...
This is a homework question, please post in student forum.
I second rb1957, make the assumptions of simply supported edges, pressure only, and then look Roark for the solution.
MS for buckling? do you have any shear or compression load? In a real wing panel you have, but not from the loading...
Hi,
Does anyone know if there is a way to use openradioss with Femap as a pre-post processor (Femap can translate to ? Or if there a way to circumvent this without buying another pre-post processor?
Maybe a translator from Nastran to Openradioss if this exists...
Thanks!
The model is a bit more complicated than that haha but of course FEM connections tend to rely in a lot of assumptions to simplify the model itself.
Thanks for your help, I appreciate it!
yeah that is what I thought... I can't redesign but I think for now I'll need to figure out if the moment is real or if is just because of the way I modelled it.
Thanks for your answer!
Hi,
I wanted to know if there is any bending test for sandwich CFRP/honeycomb structure insert.
Basically I have an insert on the middle of a CFRP sandwich panel which is introducing quite a big bending moment to the panel itself due to the boundary conditions of the structure.
I know that...
Oh yeah, sorry I checked the wrong qrg (Altair). But then, it seems that your output is in global coords, at least in Simcenter Nastran (I'm more familiar than with MSC Nastran) you use SDISPLACEMENT in the case control to ask for the modal displacement output.
In your code you're using DISP...
Hi,
From a quick check of your code I see that the DOF entrance for the initial condition card (TIC) is -1, and it should be a number between 1 to 6 (1,2,3 --> tx, ty ,tz 3,4,5 --> rx,ry,rz), what if you change it to:
TIC, 20, 1, 1, 0.3914, 0.9071
TIC, 20, 2, 1, 0.4950 , -2.1213
TIC, 20, 3, 1...
Are you using MSC Nastran? I think what you're looking for is the command PARALLEL which allows you to use SMP in the different solvers.
It is also important to notice that performance varies with solver and is not always convenient to put more cores.
Check this article for more info :)...
Thanks for the answers, it's funny that you mentioned that rb1957, it is literally how the conversation went. But then I thought to myself, well it does trigger my mind a bit and I could ask for an external opinion to verify I'm not missing something
I totally agree with you guys, you confirmed my thoughts. I just wondered if there was a reference for it, even though that from experience is not used and it has never been a problem in industry as rb1957 mentioned.
It came today in a discussion with a colleague but I said I didn't not have a...
Hi all,
Out of curiosity, in general when you evaluate a joint, in general you check ultimate strength of fasteners, plus limit/ultimate of the connected parts.
Why limit load of the fastener itself is not checked? Do you have any reference explaining this?
My thought is the following:
Most of...
Thanks for the answer! That makes sense, but as you said except when secondary bending plays a bigger role. In my case I'm installing a blade antenna with an inner profile attached to the stringers. I was evaluating aero load using the dive speed, and the resultant side force is considerable...
Hi,
I'm doing a project about an aircraft skin modification, and my client has some guidelines about the FE model that I would like to discuss with you.
Do you know why for a thin metallic structure as the skin, that are mostly modelled as shell elements (linear static) it is allowed to take...
