As part of the R.A.E.‘s critical study of the aero‐isoclinic principle of wing design, a detailed examination was made of high‐speed aeroelastic effects on manoeuvre point, with special reference to the effect of rearward movement of local aerodynamic centres at super‐critical Mach numbers. From the results of calculations, using the method of R.A.E. Report No. Aero. 2320, it is concluded that as regards possible shifts of manoeuvre point, the aero‐isoclinic wing is generally superior to the conventional wing. For tailless aircraft, application of the aero‐isoclinic principle makes it possible to employ wings of an aspect ratio much larger than is considered practicable with conventional design. Structural design of a flutter‐free aero‐isoclinic wing entails radical departures from orthodox procedure, and with tailed aircraft it is therefore probably preferable to adapt the design of the tail plane and its attachment, to cope with the destabilizing deformability effects of a conventional wing, than to eradicate such effects at the source by aero‐isoclinic design of the wing.
Taylor, A.S. (1952), "Manoeuvre Point Properties of the Aero‐Isodinic Wing: A Comparative Study of the Manoeuvring Stability of Aircraft with Aero‐Isoclinic and Conventional Wings", Aircraft Engineering and Aerospace Technology, Vol. 24 No. 9, pp. 257-262. https://doi.org/10.1108/eb032201
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