IT was now evident that some other effect would have to be taken into account to obtain a more exact agreement between theory and experiment, and it was fairly obvious that the non‐rigidity of the wing root attachments was the chief cause of the discrepancy. The method of dealing with this is given below, while the numerical results are plotted as curves C in Figs. 7 and 8. It will be seen from these curves that the modification to the theory, which is merely a modification to detail, has the desired effect.
Goodey, W.J. (1949), "Two‐Spar Wing Stress Analysis: A Method Taking into Account the Finite Spacing of the Ribs, with Detailed Numerical Calculations and Test Results for a Model Wing Test Specimen", Aircraft Engineering and Aerospace Technology, Vol. 21 No. 11, pp. 358-361. https://doi.org/10.1108/eb031830
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