Axial Flow Propulsor for Small Aircraft
Computational Fluid Dynamic Simulation (CFD) and Experimental Study on Wing-external Store Aerodynamic Interference
Design of Carbon Composite Driveshaft for Ultralight Aircraft Propulsion System
Flying Wings. A New Paradigm for Civil Aviation?
Rapid Prediction of Configuration Aerodynamics in the ConceptualDesign Phase
Design of a Three Surfaces R/C Aircraft Model
Response of a Light Aircraft Under Gust Loads
FEM MODELLING OF COMPOSITE STRUCTURES AND EXPERIMENTAL COMPARISON
www.vgtu.lt/english/editions/aviation/dokumentai/Nr_01.pdf
3 comments:
Hello:
My name Is Jesús, and I´m a aeronautics engineer student. I´m going my end of degree project, but I have a problem, I need to know the laminar flow lenght of my fuselage, anybody know a method to calculate this?
Thanks
Jesús
You can do for example this:
- Model the fuselage with an airfoil program (e.g. X-foil) as an airfoil and estimate the boundary layer transition points with that. Obviously if it is not symmetrical in shape to all directions, obviously you have to do the analysis for the shapes that are projected to side and to the top. Not very accurate if you deviate very far from a completely symmetrical and completely airfoil shape fuselage.
- XFLR5 might have something that might help a little on that (not sure though, I am not that far with that). It is made for Windows, but I discovered that I can run it with wine on Linux. It crashes frequently though.
- CFD analysis to the fuselage (I have not yet done that, so I can not say too much about that, but you can try by yourself, http://www.opencfd.co.uk/openfoam/ )
By the way, some rules of thumb for the extensive laminar flow of the forward fuselage:
- There must not be any protrusions, pitot tubes, antennas, landing gear, landing gear doors, propeller, engine cooling holes, air vents, intersections or rivets in the section you want to have sustaining laminar flow. This means that the forward fuselage must be one piece composite part with completely smooth surface.
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