enter image description here

How is shear centre of a wings calculated? i.e. how can I calculate the wing shear centre of a two spar wing with main spar at 0% of wing chord and rear spar at 75% of wing chord? (Assuming the two spars have the same stiffness.)


I implemented a program using Matlab for S.C calculus purposes (I'm actually involved in an aircraft project and, fortunately (or not), I'm the structures guy. I have based the code and the theory in a PDF bibliography that is linked w/ the .zip folder. You'll notice two matlab codes:

-One is named "Load_Airfoil_Coordinates_using_MATLAB.m". It loads any .dat file (i.e., if you have your airfoil points, you can plot it using this code);

-Another is named "Matlab_script_for_the_shear_center.m". It calculates, beyond your airfoil's C.G (Xcg,Ycg), the shear center (Xsc,Ysc) - probably you'll need to change some of the inputs to agree with your problem, specifically. Despite I've commented the most part of this code, I recommend you to follow Perini's theory (PDF bibliography) to understand the steps.

To download the .zip folder, please click my OneDrive link: https://1drv.ms/u/s!Aqqj-vTtH2vbomM9cVTInsHp7dbn?e=PMFudZ.

If you're just focusing on the theory, I recommend you some bibliographic references, such as:

  1. T.H.G. Megson - Introduction to Aircraft Structural Analysis

  2. David J. Peery - Aircraft Structures

  3. B. K. Donaldson- Analysis of Aircraft Structures

    Hope I was helpful.

Best regards, João Cioffi

| improve this answer | |

Your Answer

By clicking “Post Your Answer”, you agree to our terms of service, privacy policy and cookie policy

Not the answer you're looking for? Browse other questions tagged or ask your own question.