Lift distribution
Hi there,
I am fairly new to CFD so please be nice :) I am looking to plot lift distribution over my wing, to help me predict initial spanwise stall point so I can adjust wing parameters (mainly twist and tip airfoil characteristics, the rest is fixed), the reason I want to use CFD as opposed to other well documented methods is that my wing is quite "dirty", I have 3 engine nacelles on the leading edge and a retractable float which fits under the wing at about 60% span though not flush with the surface, all that I'm sure will affect the results. my questions are : - How do I plot lift distribution along span ? I've played around with overall wing lift coef and section pressure coefs but would like to see some kind of spanwise lift curve, local Cl etc - What would typically be mesh requirements for "good enough" spanwise lift distribution results ? I'm not looking into accurate drag or even lift values, just the distribution of it. thanks all for your help ! |
Split the surface up in a upper and lower wing. Make an X-Y plot and plot Span - Pressure. Later you should export the file and do a regression analysis in your preffered data manager (Igor or etc..).
There is no good answer to what is fine enough mesh, but you should check that the Wall y+ values are within the correct value for the turbulence modle you are using. An general answer is that the more complex geometry requires finer mesh. |
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Tip: Rather than comment on 6 year old threads asking for help, you should post a new thread.
To answer your question, it really depends on your input geometry. Can you give some clues as to how your wing is modeled? |
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I have attached the image in the design modeler. Fyi, I used half model to analyse the aircraaft and now I need to find out the lift distribution curve along the wingspan of my aircraft. Do you have any idea on this? |
You should post this question in an ANSYS forum. You will get better responses. This is a Star-CCM forum.
http://www.cfd-online.com/Forums/ansys/ I am not sure on how to approach this in ansys, but in Star-CCM I would either divide the surfaces up into a series of spanwise sections before meshing/running then extracting surface forces for each or define some probe points where you can get static pressure distributions at various locations along the span and integrate to get lift. |
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