What type of engineering considerations (corrosion prevention, electrical conductivity,...(?) ) needs to be made when approving particular painting materials, e.g. paint stripper, filler, primer, topcoat, etc.
1) Story going around of a private owner who used automotive wax for buffing his a/c...
How come the propeller arc is behind the pilot in high wing twins (MU-2, Partnavia, Aerocommander) and in front of the pilot in low wing twins (Cessnas and Pipers).
Cheers,
Timbo
Maybe I asked the wrong question.
What is the simplest way to justify the remanufacture of a rolled thread bolt/stud, where the remanufactured bolt/stud does not have rolled threads.
I am aware of the advantages of using rolled threads.
nashjp,
Remanufacture does mean replace with an improved part. The trouble being that the old parts are really strong, or more specifically, we don't know how strong.
Israelkk,
We don't have to design to the federal spec, we only have to show that the stud remanufacture meets or exceeds...
Hello all,
I have a specially made bolt/stud that requires remanufacture. A materials analysis of the bolt indicates that the threads have been rolled. A quick search on the internet indicates that rolled threads offer 30%-70% improvement in fatigue stress or a ten-fold increase in service...
Hello all,
Consider a crack in the middle of large sheet of metal, about the same dimensions as, say, the sidewalls of the engine bay mount for the Cessna 210. The crack was probably initiated by a tool scratch, falling screw driver, whatever. There is now a crack that runs at approximately...
Although I'm not familiar with what you would term "low flow rates" as opposed to "high flow rates", this is the first thought that occurs to me. At low flow rates the noise in the flow is of the same order of magnitude as the eddy amplitude.
Consider a flow barely...
"open the door on every aerodynamic topic I can think of..."
Does it have anything to say on diffusers? This is a topic I found particularly difficult to find information on. Especially trying to optimise the pressure recovery versus the drag increase. (For example, some of the...
As standard practise, we specify the cad-plate of all steel parts we design to QQ-P-416F. However, it has come to our attention that this may dramatically reduce the fatigue life.
On page 287 of "Mechanical Engineering Design" by Shigley and Mischke it states "Metallic coatings...
This question is a bit off engineering, but maybe interesting none the less.
The Beechcraft Baron has an "aft cabin door ajar" warning light. Where do you think that this should appear in the ATA code?
a) 52 : Doors
b) 33 : Lighting
c) 31 : Indicating and recording systems
Have fun...
Offhand, the Eagle-X has flaps on both the fore plane and the aft plane. The pilot has only one flap control. Also the aft plane has a wing fence and vortex generators immediately ahead of the ailerons. The wing section outboard of the wing fence has a drooped nose. The FAR certification...
Hello,
Does anyone know how to derive the pressure distribution of a body of revolution given the geometric section properties. Kind of have the feeling that it is equivalent to the 2-D flow pressure distribution, if the thicknesses were sqrt'ed.
Timbo
Eagle-X, orginally designed in Australia and now owned by the Malaysians is also a three surface configuration. The Eagle-X is certified to FAR-23 standards.
I will say no more.
Timbo
Load direction? Sorry, this was not a question specifc to any application just in general, is it better to have rivets (single shear or double shear) lined up in a "square"pattern (upper) or in a "triangular"(or "stitched") pattern (lower). Not necessarily the...
dy / dx means rate of change of y with respect to x.
(Ignore "daccuracy / dcomplexity > 0
d^2accuracy / dcomplexity^2 > 0 ( allitle bit more accurate means a lot more complex.)" It was my attempt at humour.)
Take out a sheet of paper and draw a set of axes on it. Label the horizontal...
If you want a quick method that gives reasonable accuracy then I would probably recommend doing as PJA has suggested. (Although PJA prefers R.T Jones, Iam going to go back to Prandtl).
L = (1/2) * rho * V^2 * S *CL
CL = dCL/dalpha * (alpha - alpha0)
alpha0 == Zero lift line for an aerofoil...
